Models For The Dynamic Simulation of Tank Track Components: Cranfield University

CRANFIELD UNIVERSITY
Paul Allen
Models for the Dynamic Simulation of Tank Track Components
Defence College of Management and Technology

CRANFIELD UNIVERSITY
ENGINEERING SYSTEMS DEPARTMENT
PhD THESIS
Academic Year 2005-2006
Paul Allen
MODELS FOR DYNAMIC SIMULATION OF TANK TRACK COMPONENTS
Supervisors
Dr Amer Hameed
Dr Hugh Goyder
Date of original submission

January 2006
© Cranfield University 2005. All rights reserved. No part of this publication may be
reproduced without the written permission of the copyright owner.
Acknowledgements
The author acknowledges the excellent support and guidance he has received
throughout this project from his supervisors, Dr Amer Hameed and Dr Hugh Goyder.
They have both given many hours of their time to the project. Dr Hameed has been an
outstanding supervisor, always supportive and encouraging. Dr Goyder has given
specialist support and expert advice freely. The contributions made by both Dr Amer
Hameed and Dr Hugh Goyder has been invaluable and I owe them many thanks.
I must acknowledge the support provided by Cranfield University, Engineering

Systems Department (ESD) and the staff at the Defence College of Management and
Technology (DCMT). The University and College have provided excellent facilities.
Members of staff have been helpful and professional throughout their standard of
work has also excellent. Particular departments at DCMT which have provided
support for this project are the Engineering Dynamics Centre, Library Resources,
Reprographics and the Mechanical Workshop.
I also wish to acknowledge the Engineering and Physical Sciences Research Council
(EPSRC), QinetiQ Limited (QinetiQ)and Cranfield University DCMT, for providing
financial support for this project and specifically, Dr Mark French of QinetiQ’s Future
Systems Technology division and Professor John Hetherington of DCMT, who have
both been supportive throughout.
A final thanks to David Boast of AVON Materials Development Centre who has
freely given advice and information which cleared much of the fog.
MODELS FOR THE DYNAMIC SIMULATION OF TANK TRACK
COMPONENTS
ABSTRACT
This project has been sponsored by QinetiQ Limited (QinetiQ); whose aim it is to
model the dynamics of a prototype high-speed military tracked vehicle. Specifically
their objective is to describe the mechanism by which force inputs are transmitted
from the ground to the vehicle’s hull.
Many track running gear components are steel and can be modelled as simple lumped
masses or as linear springs without internal damping. These present no difficulty to
the modeller. However tracked vehicle running gear also has nonlinear components
that require more detailed descriptions. Models for two rubber components, the road
wheel tyre and track link bush, and a model for the suspensions rotary damper, are
developed here. These three components all have highly nonlinear dynamic responses.
Rubber component nonlinearities are caused by the materials nonlinear elastic and
viscoelastic characteristics. Stiffness is amplitude dependent and the material exhibits
a significant amount of internal damping, which is predominantly Coulombic in
nature but also relaxes overtime. In this work, a novel method for measuring the
elastic and viscoelastic response of Carbon Black Filled Natural Rubber components
has been devised and a ‘general purpose’ mathematical model developed that
describes the materials response and is suited to use in multibody dynamic analysis
software.
The vehicle’s suspension rotary damper model describes three viscous flow regimes
(laminar, turbulent and pressure relief), as a continuous curved response that relates
angular velocity to damping torque. Hysteresis due to the compression of entrapped
gas, compliance of the dampers structure and compression of damper oil is described
ii
by a single non-parametric equation. Friction is considered negligible and is omitted
from the model.
All components are modelled using MSC.ADAMSTM multibody dynamic analysis
software. The models are shown to be easily implemented and computationally
robust. QinetiQ’s requirement for ‘practical’ track running gear component models
has been met.
iii
Lists of contents
Index
Models for the Dynamic Simulation of Tank Track Components ------------------------b
Acknowledgements-------------------------------------------------------------------------------i
Abstract--------------------------------------------------------------------------------------------ii
List of Contents----------------------------------------------------------------------------------iv
List of tables -------------------------------------------------------------------------------------ix
List of Figures -----------------------------------------------------------------------------------x
List of abbreviations--------------------------------------------------------------------------xvii
Nomenclature for Chapters 1 to 8 ----------------------------------------------------------xvii
Nomenclature for Chapters 9 to 13--------------------------------------------------------xviii
Chapter 1: The background and objectives of this study ------------------------------1
1.0 Introduction -----------------------------------------------------------------------1
1.1 The Warrior APC---------------------------------------------------------------- 3
Chapter 2: Literature review of high-speed tracked vehicle dynamic models ----5
2.0 Introduction -----------------------------------------------------------------------6
2.1 Robertson, B.----------------------------------------------------------------------6
2.2 Ma, Perkins, Scholar and Assanis et. al.,--------------------------------------7
2.3 Ryu, Bae, Choi and Shabana----------------------------------------------------8
2.4 Slattengren ------------------------------------------------------------------------9
Chapter 3: The characteristic behaviour of Carbon Black Filled Natural rubber-
-------------------------------------------------------------------------------------11
3.0 Introduction ---------------------------------------------------------------------11
3.1 Frequency and temperature dependence-------------------------------------11
3.2 Stress relaxation (Viscous flow)----------------------------------------------15
iv
3.3 Characteristic hysteresis loop shape------------------------------------------16
3.4 Summary-------------------------------------------------------------------------17
Chapter 4: Literature review of models developed for Carbon Black Filled
Natural Rubber----------------------------------------------------------------18
4.0 Introduction ---------------------------------------------------------------------18
4.1 Descriptions for the Elastic stress component ------------------------------19
4.2 Descriptions for the viscous stress component------------------------------24
4.3 Summary ----------------------------------------------------------------------- 38
Chapter 5: Test rig design, experimental procedure and measurement for rubber
components ---------------------------------------------------------------------40
5.0 Introduction----------------------------------------------------------------------40
5.1 Warrior APC track rubber components--------------------------------------42
5.2 Test rigs design and experimental procedure -------------------------------44
5.3 Measurement I: Low amplitude displacement with various preloads, 1Hz
sinusoidal displacement--------------------------------------------------------47
5.4 Measurement II: Constant preload at various amplitudes,1Hz sinusoidal
displacement---------------------------------------------------------------------56
5.5 Measurement III: Constant amplitude and constant preload at various
frequencies-----------------------------------------------------------------------58
5.6 Measurement IV: Stress relaxation: Force response to a stepped
displacement over time---------------------------------------------------------60
5.7 Track bush torsional response at various radial loads----------------------62
5.8 Track bush torsional response to duel-sine displacement -----------------63
Chapter 6: Development of a model for rubber components -----------------------64
6.0 Introduction----------------------------------------------------------------------64
v
6.1 The simplified Haupt and Sedlan model-------------------------------------65
6.2 The time dependent viscoelastic element -----------------------------------67
6.3 Stress relaxation and the response to duel-sine motion--------------------75
6.4 Final model for carbon black filled natural rubber components----------83
6.5 Summary ---------------------------------------------------------------------- 86
Chapter 7: Comparison between measured and simulated rubber component
response -------------------------------------------------------------------------87
7.0 Introduction----------------------------------------------------------------------87
7.1 Implementation of the final model in ADAMS software------------------87
7.2 Comparison between measured and simulated response plots------------89
7.3 Summary-------------------------------------------------------------------------96
Chapter 8 Summary of the rubber components investigation --------------------97
8.0 Summary-------------------------------------------------------------------------97
Chapter 9: The Warrior APC rotary damper --------------------------------------100
9.0 Introduction--------------------------------------------------------------------100
9.1 Design of the Warrior APC rotary damper --------------------------------101
Chapter 10: Literature review of automotive suspension damper models ------107
10.0 Introduction--------------------------------------------------------------------107
10.1 Linear equivalent models ----------------------------------------------------107
10.2 Restoring force maps---------------------------------------------------------109
10.3 Parametric or physical models ----------------------------------------------110
10.4 Spring and dashpot models --------------------------------------------------112
Chapter 11: Rotary damper test rig design and experimental procedure -------113
11.0 Test rig design and instrumentation -----------------------------------------113
11.1 Data processing-----------------------------------------------------------------114
vi
11.2 Test settings---------------------------------------------------------------------117
Chapter 12: Measured damper response and model development ---------------118
12.0 Measured damper response---------------------------------------------------118
12.1 Friction and laminar flow-----------------------------------------------------120
12.2 Laminar to turbulent flow transition----------------------------------------121
12.3 Pressure relief valve characteristics (Blow-off)---------------------------123
12.4 Hysteresis due to entrapped air, oil compression and chamber
compliance ---------------------------------------------------------------------125
12.5 Model implementation--------------------------------------------------------128
12.6 Damper rotor inertia ----------------------------------------------------------129
Chapter 13: Comparison between measured and modelled rotary damper
response ---------------------------------------------------------------------- 130
13.0 Introduction---------------------------------------------------------------------130
13.1 Measured and modelled results for the rotary damper--------------------131
13.2 Predicted response at high velocity------------------------------------------133
Chapter 14: Rotary damper: Conclusion and Further work ----------------------135
14.0 Conclusion and further work -------------------------------------------------135
Chapter 15: Conclusion and further work ---------------------------------------------137
15.0 Overview------------------------------------------------------------------------137
15.1 Rubber component models ---------------------------------------------------137
15.2 Suspension damper model ---------------------------------------------------139
15.3 Further work--------------------------------------------------------------------139
References-------------------------------------------------------------------------------------142
vii
Appendix 1: Time independent force-displacement relationship for the Haupt and
Sedlan viscoelastic element --------------------------------------------------1
Appendix 2: Response of the Haupt and Sedlan viscoelastic element to a stepped
input -----------------------------------------------------------------------------4
Appendix 3: Test rig frequency response for rubber component measurement ------6
Appendix 4a: The ‘Four viscoelastic element’ model
Values for the track bush torsional model -----------------------------------------11
Appendix 4b: The final ‘three viscoelastic-element’ model
Values for the road wheel tyre model-----------------------------------------------12
Values for the track bush torsional model------------------------------------------13
Values for the track bush radial model ---------------------------------------------13
Appendix 5: Compression of damper oil, entrapped air and compliance of oil the
chamber -----------------------------------------------------------------------14
Appendix 6: Torque-Angular velocity relationship for the Warrior APC rotary
damper model (excluding hysteresis) -------------------------------------19
Appendix 7: Test rig design and instrumentation --------------------------------------22
viii
List of tables
Table 4.1-1: A Summary of recent Elastic Stress models developed for Carbon
Black Filled Natural Rubber -----------------------------------------------23
Table 10.3-1: A summary of the various physical phenomena that are described in a
selection of parametric models ------------------------------------------111
Table 11.2-1: Rotary damper test settings -----------------------------------------------117
Table A6-1: Numeric data for the damper torque verses angular velocity response
----------------------------------------------------------------------------------20
Table A7-1: Data acquisition channel assignment for both random and sinusoidal
drive signals-------------------------------------------------------------------23
ix
List of figures
Figure 1.0-1: Qinetiq’s prototype plastic tank, The Advanced Composite Armoured
Vehicle Platform (ACAVP) ---------------------------------------------------2
Figure 1.1-1: The Warrior Armoured Personnel carrier (APC) ------------------------3
Figure 1.1-2: Warrior APC running gear: Track, road wheels and support roller --4
Figure 3.1-1: Relationship between, In-phase modulus and Tan delta ----------------12
Figure 3.1-2: Effect of temperature on in-phase modulus. Avon Rubber [2] ---------13
Figure 3.1-3: Tan delta over the temperature range -80 → +40°C showing different
glass transition temperatures for various polymers
Avon Rubber [2] -------------------------------------------------------------13
Figure 3.1-4: Frequency dependency of in-phase modulus for a variety of
compounds at 20°C. Avon Rubber [2] ------------------------------------14
Figure 3.1-5: Frequency dependency of tan delta for a variety of compounds at
20°C. Avon Rubber [2] ------------------------------------------------------14
Figure 3.2-1: Typical stress relaxation response for Carbon Black Filled Natural
Rubber (CBFNR)- ------------------------------------------------------------15
Figure 3.3-1: Characteristic CBFNR hysteresis loops. Reproduced from Coveney
and Johnson [8] --------------------------------------------------------------16
Figure 3.3-2: Typical response for CBFNR. Showing amplitude dependent stiffness
(a) and amplitude independent loss angle (b). Reproduced from
Coveney and Johnson [8] ---------------------------------------------------17
Figure 4.2.1-1: Schematic representation of Berg’s model ------------------------------24
Figure 4.2.2-1: Schematic representation of the Triboelastic model -------------------26
x
Figure 4.2.3-1:Schematic representation of the Rate Dependent Triboelastic (RT)
model --------------------------------------------------------------------------28
Figure 4.2.3-1: Illustration showing the requirement for a linear viscous relationship
at low velocity to prevent rapid changes in the force vector -----------29
Figure 4.2.4-1: Schematic representation of the Bergstrom and Boyce model -------30
Figure 4.2.5-1: Schematic representation of the Miehe and Keck model --------------31
Figure 4.2.7-1: A one-dimensional and simplified schematic representation of the
Haupt and Sedlan model (with a single viscoelastic element only)----34
Figure 4.2.7-2: A one-dimensional schematic representation of the Haupt and Sedlan
strain-history dependent viscosity model (with a single viscoelastic
element only) -----------------------------------------------------------------37
Figure 5.1-1: Warrior APC rubber track components; (A) A single Track link (B)
Track bush sections removed from the track link casting (C) Road
wheel tyres --------------------------------------------------------------------42
Figure 5.2-1: (A) Measurement of track bush torsional characteristics by rotation
about the track bush axis (B) Measurement of Track bush radial force
and displacement (C) Measurement of road wheel tyre radial force and
compression ------------------------------------------------------------------44
Figure 5.3.1-1: Track bush torsional elastic-force response -----------------------------50
Figure 5.3.1-2: Track bush radial elastic-force response --------------------------------50
Figure 5.3.1-3: Road wheel tyre elastic-force response ----------------------------------51
Figure 5.3.2-1: Track bush torsional geometric factor -----------------------------------53
Figure 5.3.2-2: Track bush radial geometric factor ---------------------------------------53
Figure 5.3.2-3: Road wheel tyre radial geometric factor --------------------------------54
xi
Figure 5.4-1: Track bush torsional force-displacement response --------------------56
Figure 5.4-2: Track bush radial force-displacement response ------------------------57
Figure 5.4-3: Road wheel tyre radial force-displacement response ------------------57
Figure 5.5-1: Road wheel tyre force-displacement response at several
Frequencies ------------------------------------------------------------------58
Figure 5.5-2: Track bush radial force-displacement response at several
Frequencies -------------------------------------------------------------------59
Figure 5.6-1: Track bush torsional stress relaxation ------------------------------------60
Figure 5.6-2: Road wheel tyre stress relaxation -----------------------------------------61
Figure 5.7-1: Track bush torsional response at varying radial loads -----------------62
Figure 5.8-1: Track bush torsional response to duel-sine displacement --------------63
Figure 6.1-1: Schematic representation of the simplified Haupt and Sedlan carbon
black filled natural rubber component model ----------------------------66
Figure 6.2-1: Rising and falling exponential curves produced by
Equation 4.2-10 --------------------------------------------------------------68
Figure 6.2-2: Track bush torsional viscoelastic force. Modelled using a single
viscoelastic Element (Equations 4.2-10) ----------------------------------69
Figure 6.2-3: Track bush torsional viscoelastic force. Modelled using two parallel
viscoelastic elements (Equations 4.2-10) --------- -----------------------70
Figure 6.2-4: Track bush radial viscoelastic force. Modelled using two parallel
viscoelastic elements (Equation 4.2-10) ----------------------------------72
Figure 6.2-5: Road wheel tyre viscoelastic force. Modelled using two parallel
viscoelastic elements (Equation 4.2-10) ----------------------------------72
xii
Figure 6.2-6: Quarter model of the tyre contact showing von Mises strain. Tyre
compression is 8mm. Produced using ANSYS FEA software ----------74
Figure 6.3-1: Measured track bush torsional response to duel-sine displacement – 76
Figure 6.3-2: Simulation of track bush torsional response to duel-sine displacement
produced by ADAMS simulation of the simplified Haupt and
Sedlan -------------------------------------------------------------------------77
Figure 6.3-3: Four-element model: Two non-linear viscoelastic elements each with a
nested rapidly decaying non-linear stiffening viscoelastic element ---79
Figure 6.3-4: Simulated track bush torsional response to duel-sine displacement
produced by ADAMS simulation of the four-element viscoelastic
model --------------------------------------------------------------------------80
Figure 6.3-5: Measured and simulated track bush torsional stress relaxation
produced by ADAMS simulation of the four-element viscoelastic
Model --------------------------------------------------------------------------81
Figure 6.4-1: Final model containing three non-linear viscoelastic elements -------83
Figure 6.4-2: Simulated track bush torsional response to duel-sine displacement.
Produced by ADAMS simulation of the final three-viscoelastic element
model --------------------------------------------------------------------------84
Figure 6.4-3: Measure and simulated track bush torsion stress relaxation, produced
by ADAMS simulation of the final three viscoelastic element model -85
Figure 7.1-1: Implementation of the ‘final model’ in ADAMS software so that
x B ≈ x A -------------------------------------------------------------------------87
xiii
Figure 7.2-1: Simulated Track bush radial force-displacement ------------------------89
Figure 7.2-2: Simulated track bush torsional force-displacement response ----------90
Figure 7.2-3: Simulated road wheel tyre radial force-displacement response -------91
Figure 7.2-4: Simulated road wheel tyre displacement-force response ---------------92
Figure 7.2-5: Simulated road wheel tyre force-displacement response at several
frequencies --------------------------------------------------------------------93
Figure 7.2-6: Measure and simulated road wheel tyre stress relaxation -------------94
Figure 7.2-7: Measure and simulated track bush torsion stress relaxation ----------94
Figure 7.2-8: Simulated track bush torsional response to duel-sine displacement –95
Figure 9.0-1: Warrior Armoured Personnel Carrier running gear (Horstman
Defence Systems Ltd) ------------------------------------------------------ 101
Figure 9.1-1: Section through rotary damper -------------------------------------------102
Figure 9.1-2: Sectioned view of the rotary damper -------------------------------------102
Figure 9.1-3: Design specification showing the allowable range of damper
Torque ----------------------------------------------------------------------- 104
Figure 9.1-4: Characteristic graph of torque verses angular velocity, produced by
Horstman Defense Systems Ltd -------------------------------------------105
Figure 10.4-1: A physical damper model represented by non-linear dashpot and
nonlinear spring in series -------------------------------------------------112
Figure 11.0-1: Schematic drawing of the rotary damper test rig --------------------113
Figure 11.1.2-1: Comparison between normalised hydraulic ram and rotary damper
motion ----------------------------------------------------------------------115
xiv
Figure 11.1.3-1: Schematic drawing of rotary damper test rig mechanism ----------116
Figure 12.0-1: Torque verses angular displacement (Work diagram) ----------------118
Figure 12.0-2: Torque verses angular velocity (Characteristic diagram) ------------119
Figure 12.1-1: Torque angular velocity for the low frequency (0.1Hz) test ----------120
Figure 12.2-1: Torque angular velocity for the mid-range frequencies up to
0.5Hz -------------------------------------------------------------------------122
Figure 12.2-2: Laminar and turbulent flow regions of the viscous force -------------123
Figure 12.3-1: Data supplied by Horstman Defense Systems Ltd ---------------------124
Figure 12.3-2: Rotary damper torque-angular velocity response without
hysteresis --------------------------------------------------------------------125
Figure 12.4-1: Schematic diagram illustrating the compression and expansion of
entrapped gas ---------------------------------------------------------------126
Figure 12.5-1: The rotary damper, modelled by a non-linear dashpot and non-linear
spring in series --------------------------------------------------------------128
Figure 13.1-1: Modelled torque verses angular displacement (Work diagram) ----131
Figure 13.1-2: Modelled torque verses angular velocity (Characteristic
diagram) --------------------------------------------------------------------132
Figure 13.2-1: Modelled torque verses angular displacement in response to high
frequency sinusoidal motion ----------------------------------------------133
Figure 13.2-2: Modelled torque verses angular velocity in response to high frequency
sinusoidal motion -----------------------------------------------------------134
xv
Figure A1-1: The viscoelastic Sedlan and Haupt element--------------------------------1
Figure A2-1: Response to stepped displacement-------------------------------------------4
Figure A3-1a: Road wheel tyre test rig ------------------------------------------------------8
Figure A3-1b: Road wheel tyre test rig FRF-------------------------------------------------8
Figure A3-2a: Track bush radial force test rig ---------------------------------------------9
Figure A3-2b: Track bush radial force test rig FRF ---------------------------------------9
Figure A3-3a: Track bush torsional response test rig-------------------------------------10
Figure A3-3b: Track bush torsional response test rig FRF ------------------------------10
Figure A4a-1: Four viscoelastic element model ------------------------------------------ 11
Figure A4b-1: Three viscoelastic element model ------------------------------------------12
Figure A5-1: Schematic representation of the damper showing how entapped air is
compressed and expanded as oil flows from one chamber into the other
----------------------------------------------------------------------------------14
Figure A5-2: Response described by Equation A5-15 for C1 =1 and C2 =2 ---------18
Figure A6-1: The rotary damper viscous force-velocity response implemented in
ADAMS software as a splined curve --------------------------------------21
Figure A7-1 Test rig control and instrumentation set up for random drive signal
Figure A7-2 Test rig for the measurement of Track Bush Radial Response
Figure A7-3 Test rig for the measurement of the Track Bush Torsional Response
Figure A7-4 Test rig for the measurement of the Road Wheel Tyre Response
Figure A7-5 Test rig for the measurement of the rotary damper’s Response
xvi
List of abbreviations
ACAVP Advanced Composite Armoured Vehicle Platform
APC Armoured Personnel Carrier
CBFNR Carbon Black Filled Natural Rubber
LVDT Linear Variable Displacement Transducer
Tan Delta Tangent of phase angle between stress and strain
Nomenclature for Chapters 1 to 8
A, B, C, P, Q Constants (Units vary depending on function)
c Damping Coefficient. Units for this parameter vary depending on the
material model. The units are most often either (Ns/m) or (N), however
a power term may be require such as (Ns/m)n where n is the fractional
power term.
E Youngs Modulus (MPa)
F Force (N)
k Elastic stiffness (N/m)
t Time (s)
x Displacement (m)
x& Velocity (m/s)
β Constants (No units)
γ Strain
ε Strain
ε& Strain rate
η Coefficient of viscosity (Ns/m)
λ Ratio of deformed length to original length
xvii
ξ Constant (m/s)
σ Stress (MPa)
τ Time constant (s)
Subscripts
e Elastic
0 Absolute displacement of rubber component
K, N Integer
v Viscoelastic
Superscripts
n Power term
Nomenclature for Chapters 9 to 14
A Amplitude of linear displacement (m)
B, C, D Constants (NoUnits)
C1, C2 Constants (Units Vary depending on usage)
c Damping Coefficient (Ns/m)
F Force (N)
I Inertia (kg.m2)
k Elastic stiffness (N/m)
m Mass (kg)
P Pressure (N/m2)
R Gas Constant (J/kg.K)
r Radius arm length (m)
T Torque (Nm)
t Time (s)
xviii
V Volume (m3)
x Displacement (m)
x& Velocity (m/s)
&x& Acceleration (m/s2)
θ Rotary damper Angle (Rads)
Θ Amplitude of rotary motion (Rads)
φ Drive signal phase angle (Rads)
ω Frequency (Hz)
Subscripts
d Dashpot
eq Equivalent lineatized value
gb Gas bubble
gs Gas in solution
gt Total quantity of gas
oil Damper oil
s Spring
xix
Chapter 1
The background and objectives of this study
1.0 Introduction
The objective of the work presented here is to develop models for Warrior Armoured
Personnel Carrier (APC) running gear components for use in multibody dynamic
simulations.
There are two driving motivations for this work. Firstly; there is a requirement for
reduced vehicle weight to optimise the transport of armoured fighting vehicles by air
to regions of conflict. Secondly; there is a requirement to reduced noise and vibration
for the comfort of personnel within the vehicle. To these ends Qinetiq Limited is
investigating the practicality of replacing the Warrior’s aluminium hull with a
composite material. A prototype plastic tank has been built: the Advanced Composite
Armoured Vehicle Platform (ACAVP, Fig. 1.0-1). The hull is constructed from
moulded E-Glass fibre composite but the vehicle runs on standard Warrior APC
tracks. Qinetiq has initiated a study of running gear dynamics so that the transmission
of ground inputs to the hull can be modelled. The work presented here is part of this
study, it aims to measure the dynamic response and validate models for individual
components of the Warrior’s track running gear.
Models for three track running gear components are developed: these are the ‘road
wheel tyre’ the ‘suspensions rotary damper’ and the ‘track link bush’. Models for the
‘road wheel tyre’ and the ‘track link bush’ are developed jointly in Chapters 3-8, since
both are made from carbon black filled natural rubber (CBFNR). In chapters 9-14 a
model for the Warrior’s suspension rotary damper is developed. In each case
measurements show that these components have significantly nonlinear dynamic
1
response and it is important that these nonlinearities are described in the component
models if the full vehicle simulation is to be accurate. However it is also important
(for computational efficiency) that component models are no more detailed than is
necessary.
Fig. 1.0-1: Qinetiq’s prototype plastic tank, The Advanced Composite Armoured
Vehicle Platform (ACAVP)
With regard to implementation in the simulation software: component models should
be robust and should be compatible with the software’s algorithm. In the work
presented here models have been developed and tested using MSC.ADAMSTM 2003
software. This type of implicit algorithm finds the solution to initial value problems
by incrementing forward in time, making initial estimates of position, velocity, force
and acceleration then correcting these values by repeated iterations until the systems
equations of motion and geometric constraints equate to within a given accuracy. If
the algorithm fails to find a solution within a given number of iterations the time
increment is automatically reduced and another attempt made. However, the time
2
increment is also given a minimum value: so it is possible under certain circumstances
for the simulation to fail to find a solution. The Newton-Raphson Predictor-Corrector
algorithm is complex and is not discussed within the scope of this work; but detailed
descriptions can be found in the following references [41, 42, 43, 44]. The significant
point to appreciate when developing component models for use in this type of
software is that the algorithm is susceptible to discontinuities, multiple or ill-defined
solutions and sudden step changes, all of which may cause a simulation to fail [41,
44]. It is important therefore that component descriptions are ‘smooth’, continuous
and unambiguous. This point is restated throughout this report when discussing how
component models have been derived.
1.1 The Warrior APC
Fig. 1.1-1: The Warrior Armoured Personnel carrier (APC)
The Warrior Armoured Personnel Carrier (APC) is primarily designed as an armoured
troop carrier although variations for, recovery, reconnaissance, command post, etc.
are built. The Warrior is designed to have the speed and performance to keep up with
3
Challenger 2 main battle tanks, and the firepower and armour to support infantry in an
assault.
The Warrior runs on single pin rubber bushed track, driven by sprockets at the front of
the vehicle. A single roller supports the tracks top span. The twelve road wheels have
torsion bar suspension with rotary dampers at the 1st, 2nd and 6th wheel stations. Road
wheels, idler wheel and support roller all have moulded rubber tyres.
Fig. 1.1-2: Warrior APC running gear: Track, road wheels and support roller
As stated above; three components from the Warriors running gear are modelled in
this study. These are the track link bush, the road wheel tyre and the suspensions
rotary damper. These have been chosen because they have significant nonlinear
stiffness and damping characteristics and it is important that these nonlinearities are
described if a simulation of the complete vehicle is to be accurate. The suspensions
torsion bar is simply a linear elastic element with very little internal damping and so
does not require detailed study.
4
In summary the objectives of this work are:
1. Develop models for the Warrior APC track running gear components for use
in multibody dynamic simulation software.
2. Validate the models by comparing them with the measured response of
individual track components.
3. Describe significant nonlinear behaviour, but produce models that are no more
detailed then necessary for full tracked vehicle running gear simulation.
4. Develop models that are, robust, computationally efficient and compatible
with the software’s algorithm. Models that do not produce discontinuities,
multiple or ill-defined solutions or sudden stepped changes.
5
Chapter 2
Literature review of high-speed tracked vehicle dynamic models
2.0 Introduction
In this chapter a number of models developed for tank tracks and full tracked vehicle
simulation are reviewed. In each case discussion focuses on how the stiffness and
damping characteristics of the running gears nonlinear components (suspension
damper, track bush and tyres) are described.
2.1 Robertson, B.
Robertson, B. (1980) [1] built a full-scale tank track test rig (Scorpion) and developed
analytical models in an attempt to predict the transverse vibration of the tracks top
span. This work was done prior to the development of automatic dynamic analysis
software and high-specification personnel computers. The four models developed
were based on, a string with axial velocity, an elastic beam and a viscoelastic beam
with internal hysteretic damping and/or viscous damping. This work illustrates the
limitations of the analytical approach and why it is only now using numerical multi-
body dynamic analysis software that progress is being made. Robertson’s analytical
formula did not predict the resonant frequencies that he measured. The mechanical
system Robertson attempted to model was too complex to be described by the track
top span resonance alone. It was found that resonant frequencies occurred at multiples
of drive sprocket and track revolution speed. Resonance of the track span was not
detected by measurement. The dynamics of the system were a complex interaction
between track, test rig structure and drive system that could not be predicted by an
analytical track description alone. With regard to component descriptions for the
6
analytical model: the track was described as a continuous string or beam; Robertson
was aware that the internal damping of the rubber track bush was ‘hysteretic’ or
‘Coulombic’ in nature not viscous (that is; frequency independent not frequency
dependent. See section 3.1) but could not show that this type of damping best
described the frequency response when stationary track was excited by swept
sinusoidal motion. Robertson therefore concluded that viscous damping best
described the frequency response he measured.
2.2 Ma, Perkins, Scholar and Assanis et. al.,
Ma, Perkins, Scholar and Assanis et. al., [4, 38, 39] develop a two-dimensional full
vehicle model of the M1A1 tank. Here a hybrid model is used where the track span is
described as a continuous uniform elastic rod connected kinematically to discrete
models for sprocket, wheels and rollers. The objective is to model track vibration and
track interaction with other components but reduce the large number of bodies in the
model, thereby reducing the computational effort required.
Track response is linearized in the spans between wheels and rollers by assuming
small deformation. Track force-displacement and force-velocity response is therefore
described by parallel ‘linear stiffness’ and ‘linear viscous damping’ respectively.
Detailed measurements of and descriptions for components such as tyres, track
bushes, track footpads and suspension dampers are not included in this work because
it is the vehicles general overall interaction between engine, track, terrain and hull;
and the development of an efficient modelling algorithm that is of interest. Modelling
inertial interactions and improved computational efficiency by the development of a
hybrid model are the primary objectives. This approach developed by Ma, Perkins,
Scholar and Assanis et. al., [4, 38, 39] is successful in achieving its objective; track
7
vibration, track-terrain and track-discrete body interactions are described and over
limited frequency and amplitude range this may produce accurate predictions but
more comparison with experimental data is required to validate this approach.
2.3 Ryu, Bae, Choi and Shabana
Ryu, Bae, Choi and Shabana [40] (2000) develop a three-dimensional multibody
high-speed military tracked vehicle model with compliant track. That is; the joint
between each track link is described by stiffness and damping values. This lumped
mass model has 189 bodies and 954 degrees of freedom.
The suspensions torsion bar and Hydro-pneumatic unit are modelled as linear and
non-linear spring elements respectively but suspension damping is not described.
Contact stiffness between road wheel and track link and between adjacent track links
are described ‘for the sake of simplicity’ by a splined curve based on static tests.
Contact force damping is described as a linear viscous force where the ‘effective
damping coefficient’ is determined from measurements of the amplitude of hystersis.
This contact force model [40] is further developed by Ryu, Huh, Bae and Choi [5]
(2003) for a three-dimensional non-linear multi-body dynamic (MBD) simulation of a
military high-speed tracked vehicle for the particular purpose of studying the
feasibility and possible advantages of using an active track tensioner. This lumped
mass model has 191 ridged bodies and 956 degrees of freedom. In this model the
predominantly frequency independence characteristic of carbon black filled natural
rubber is appreciated and rubber components hysteresis are modelled using ‘Bergs’
method [6] (see section 4.2.1). However the hydro-pneumatic suspension unit and
torsion bar descriptions are unchanged from the earlier work [40] being described by
a splined curve only; suspension damping is not included. This is a more accurate
8
description of running gear components than the previous model [40] but Berg’s
method of describing rubber hysteresis requires the storage of force and displacement
values at turning points and how this was implemented is not described in detail.
2.4 Slattengren
Slattengren [41] (2000): ‘This paper describes the features and use of the commercial
multibody simulation program ADAMS (Automatic Dynamic Analysis of Mechanical
Systems) in the simulation of tracked vehicle applications.’
A tracked system created by the ADAMS add-on ‘Tracked Vehicle Toolkit’ (ATV)
can be modified/extended in anyway ADAMS allows. Parameters for each building
element in the tracked system are user defined. The building elements being: hull,
track, road surface, road wheel, suspension and idler/track tensioner. The user also
defines the description for compliance between elements such as track links and at
points of contact such as tyres. Compliance is described by a parallel spring and
damper (Kelvin) element, which may be either linear or nonlinear. Once all the
vehicle’s elements have been defined they are automatically assembled by the
software to produce the full tracked vehicle model.
Slattengren’s paper [41] is written as a guide to using the ATV software and offers
advice for running successful simulations. As a general rule Slattengren states that,
‘experience has clearly shown that it is extremely hard to get successful simulations
out from guessed data. The better the data is, the better the simulation will run’. This
comment emphasises the importance of using measured data for each component
description. But Slattengren also discusses special considerations concerning the
description of, damping, contact and friction, emphasising that modelling the contact
force and friction presented particular difficulty. ‘In order to be able to simulate the
9
type of complex systems which are not only dominated by contact phenomenon and
friction, but also show very large penetration due to the large masses and forces in
the system, certain special functions were developed. The most important changes
compared to the standard ADAMS functions are without question the impact and
friction formulations’.
10
Chapter 3
The characteristic behaviour of Carbon Black Filled Natural Rubber
3.0 Introduction
All rubber components of the Warrior APC track running gear are made from Carbon
Black Filled Natural Rubber (CBFNR). The benefits of using CBFNR in this
application are that it reduces impact forces, increases track-life, damps noise and
vibration and allows the track to run at higher speeds then is possible with metal-to-
metal contact. Specifically CBFNR is chosen for its durability and low heat build up
[2]. It is a material commonly used for high dynamic load applications such as truck
or aircraft tyres, engine mountings and machine isolation.
In this chapter the characteristic dynamic behaviour of CBFNR is discussed. Models
proposed by various researchers for describing this materials response are reviewed
and their suitability for use in the simulation of Warrior Armoured Personnel Carrier
(APC) running gear components assessed.
3.1 Frequency and temperature dependence
The first consideration when modelling an elastomeric component for dynamic
simulations is the materials variation in stiffness (material modulus) and damping
(phase or loss angle) over the relevant temperature and frequency operating range.
Precise data for the rubber compounds used in Warrior APC track components, (40
and 60 parts per hundred rubber by weight (pphr)) are not available but similar highly
filled natural rubber compounds are used in ‘Truck Tread’. Data for truck tread
(AVON rubber [2]) are presented in Figs. 3.1-2, 3.1-3, 3.1-4 and 3.1-5, which show
‘In-phase modulus’ and ‘Tan delta’ verses temperature and frequency. Where Tan
11
delta is the tangent of the phase angle (δ) between stress and strain when measured in
response to sinusoidal motion and in-phase modulus is the in-phase component of the
measured modulus, i.e. the dynamic modulus multiplied by the cosine of delta (Figure
3.1-1).
Out of phase
modulus Dynamic
modulus
Delta
In-phase
modulus
Fig. 3.1-1: Relationship between, In-phase modulus and Tan delta
Figures 3.1-3 and 3.1-5 show that for Truck Tread, Tan delta does not vary
significantly over the temperature range 0º-20ºC and the frequency range 1-100Hz.
Assuming that strain amplitude has been kept constant over this range; the
predominantly frequency independent loss angle of Figure 3.1-5 suggests that a
suitable damping model maybe a frictional or Coulombic description.
By contrast; the value of Tan Delta for unfilled Polyurethane Acoustic Absorber in
Figure 3.1-5 shows significant frequency dependence suggesting a velocity depended
(or viscous) damping model.
12
Various Compounds ≈ 0.2% peak-to-peak amplitude 10Hz
Log.
In-phase
Modulus
(MPa)
Temperature (°C)
Fig. 3.1-2: Effect of temperature on in-phase modulus. Avon Rubber [2]
Various Compounds ≈ 0.2% peak-to-peak amplitude 10Hz
TAN
Delta
Temperature (°C)
Fig. 3.1-3: Tan delta over the temperature range -80 → +40°C showing different
glass transition temperatures for various polymers. Avon Rubber [2]
13
In-phase
Modulus
(MPa)
Frequency (Hz)
Fig. 3.1-4: Frequency dependency of in-phase modulus for a variety of compounds

at 20°C. Avon Rubber [2]
TAN
Delta
Frequency (Hz)
Fig. 3.1-5: Frequency dependency of tan delta for a variety of compounds at 20°C.
Avon Rubber [2]
Figure 3.1-2 shows the in-phase modulus of Truck Tread varying between ≈32MPa
and ≈20MPa in the range 0°C to 20°C and figure 3.1-4 shows in-phase modulus
varying between ≈14MPa and ≈20MPa in the range 1Hz to 100Hz. These variations
in modulus are approximately 50% and maybe significant enough to be included in a
14
model of CBFNR. However as a first approximation frequency and temperature
effects over these ranges could be excluded for the sake of simplicity.
3.2 Stress relaxation (Viscous flow)
As mentioned in Section 3.1; the predominately frequency independent Truck Tread
plot (Fig. 3.1-5) leads us to conclude that a Frictional or Coulombic description would
approximate the damping force characteristic of CBFNR. However, when the material
is subjected to a stepped strain history the initial stress response reduces rapidly at
first then continues to decay slowly over time (Fig. 3.2-1). Measurements have shown
that the material has almost total stress relaxation at infinite time [19]. This ‘stress
relaxation’ is assumed to be equivalent to the viscous force component (out-of-phase
stress) and the stress at infinity equivalent to the elastic force component (in-phase
stress). However, relaxation (or viscous flow) is not described in a purely frictional
model and so presents a problem to the ‘modeller’, to produce a predominately
frequency independent damping force that also has stress relaxation.
250
Initial rapid Slow decay over

200 fall in force long time period
150
Force (N)
100
50
0
0 5 10 15 20 25
Time (seconds)
Fig. 3.2-1: Typical stress relaxation response for Carbon Black Filled Natural
Rubber (CBFNR)
15
3.3 Characteristic hysteresis loop shape
A further characteristic of CBFNR is that the response to steady state cyclic
displacement in the time domain produces hysteresis loops that are not elliptical, but
have an asymmetric shape. This characteristic is independent of frequency. The rate
of change of stress after a turning point is initially high but reduces to a lower level as
the strain amplitude increases. This characteristic response has been reported many
times by different researcher for both CBFNR material tests [7, 8] and CBFNR
component tests [6, 11]. The stress-strain plots of Fig 3.3-1 shows the typical
asymmetric hysteresis loop shape developing as amplitude increases.
Plot of shear stress (σ) against shear strain (γ) for sinusoidal strain history at 1Hz
Fig 3.3-1: Characteristic CBFNR hysteresis loops. Reproduced from Coveney

and Johnson [8]
This characteristic hysteresis loop shape results in amplitude-dependent stiffness
(since the major axis changes with amplitude) while maintaining an almost constant,
amplitude independent, loss angle (Fig 3.3-2).
16
Shear Loss
Stress Angle
(MPa) (deg)
Strain Strain
Fig 3.3-2: Typical response for CBFNR. Showing amplitude dependent stiffness (a)
and amplitude independent loss angle (b). Reproduced from Coveney
and Johnson [8]
3.4 Summary
To describe the dynamic behaviour of CBFNR a model should have the following
four traits:
1. Two independent components: one representing the in-phase elastic force, the
other representing out-of-phase damping force.
2. Predominately frequency independent hysteresis (Coulomic type damping).
3. The characteristic asymmetric hysteresis loop shape; resulting in amplitude
dependent stiffness.
4. Viscous damping that produces a rapid initial stress relaxation followed by
slow decay over a long time period.
17
Chapter 4
Literature review of models developed for
Carbon Black Filled Natural Rubber
4.0 Introduction
In this chapter various models that have been developed in recent years for modelling
the dynamic response of Carbon Black filled Natural Rubber (CBFNR) are discussed.
Beginning with the simplest ‘time independent models’ then describing the more
complicated ‘power’ and ‘exponential function’ models. All of the models discussed
describe total stress as the sum of an elastic (in-phase) stress and a damping (out-of-
phase stress) where each element responds independently of the other. Because the
two elements respond independently, discussion of each is presented in separate
subsections. In Section 4.1 the various types of elastic force description are compared.
In Section 4.2 the various types of damping force description are compared. Some
models have a third element, which is described as a, ‘plasto-elastic stress’ ‘weak
equilibrium hysteresis stress’ or a ‘friction force’. However, this element could also
be interpreted as a second ‘parallel’ damping element with very high viscosity and a
resulting long relaxation time and so will be included in discussion on the damping
component (section 4.2).
18
4.1 Descriptions for the Elastic stress component
Elastic stress (as described in Section 3.1) is the in-phase component of the materials
force response. This elastic component is also referred to as the ‘equilibrium stress’
by some researchers because it is the component of the force that remains at infinite
time when the viscous damping component has totally relaxed.
Here in Section 4.1 the functions used to describe the elastic stress in six different
CBFNR models are discussed. These models are: Berg [6], Triboelastic [8, 9, 12],
Bergstrom and Boyce [13, 14], Miehe and Keck [16], Lion [18], Haupt and Sedlan
[19]. The functions are not all dissimilar, so it is possible to group these models
together by the type of elastic function used. However it is also interesting to group
the models by the method used to determine the parameters that define their
respective functions. This is because determining parameters from experimental data
requires significant data processing techniques. Also, if a precise measurement of the
elastic component can be made independently of the viscoelastic component, it can be
subtracted from the total response and a model for the viscoelastic component
developed with confidence.
Firstly, if the models are grouped by the type of elastic function used, two groups
emerge. Berg’s model [6] and the Triboelastic model [8, 9, 12] are grouped together
because both have the simplest of constitutive relationships; a one-dimensional linear
Hookean model at the component level described by the function: F=kx, where F is
elastic force, k is a constant and x is displacement (extension or compression). In this
model, the coefficient ‘k’ may be linear because of the components geometry or it
may be an indication of relatively low strain (it is well documented that the elastic
modulus of CBFNR is non-linear above 1% strain [45, 46]).
19
Similarly, Bergstrom and Boyce [13, 14], Miehe and Keck [16], Lion [18] and Haupt
and Sedlan [19], are grouped together by the type of function used. All are three-
dimensional constitutive material models that use ‘finite strain energy functions’ to
describe the elastic element. These are functions that satisfy the following three
constraints:
1. They are invariant to the axis orientation (x, y & z) i.e. the material is isotropic
2. At small strains the function reduces to a Hookean description, i.e. σ = Eε
3. Strain energy = 0 when λx= λy= λz= 1
Where E = Young’s Modulus, σ = stress, ε = strain and λ = ratio of deformed length
to original length in each orthogonal axis x, y & z. The strain energy functions used in
these four models are the standard and modified, Neo-Hookean, Mooney-Rivlin and
Ogden types [47]. The purpose of these functions is simply to introduce into the
elastic description enough parameters so that the non-linear response of the elastomer
at high strain is described. These four material models describe the materials elastic
response up to 200% strain.
Alternatively, grouping the six models by considering the method used to determine
the coefficients for the elastic functions results in three distinct groups. Firstly we can
define a group that uses computer algorithms to determine coefficients from the total
hysteretic stress-strain response. Here the fundamental in-phase modulus and phase
angle are found by Fourier analysis of the response to sinusoidal strain histories at a
number of frequencies. A minimisation algorithm is then used matches the models
response to this result thereby determining values for the functions coefficients. In
this group we have the Triboelastic models [8, 9, 12].
20
A second group can be defined where coefficients are determined by extracting
‘specific points on’ and/or ‘tangents to’ the CBFNR’s characteristic hysteresis loop
(see Section 3.3). In this group we have, Berg [6], Bergstrom and Boyce [13, 14].
This leaves, Miehe and Keck [16], Lion [18] and Haupt and Sedlan [19] in a third
grouping where points on the elastic force response curve are determined by direct
measurement. Each element of the model (elastic, viscous and plastic) is described
independently and so each can be measured independently by performing suitable
tests. The coefficients for the strain energy function are found by a minimisation
algorithm fit to a measure of relaxed strain at a number of points. The material is first
strained by increasing deformation in steps, at each step the strain is held constant for
a long time period; the strain is then decreased in steps, again holding the strain
constant for a long period at each step. In this way the elastic stress response is
approached from a positive and negative value of visco-elastic stress. The
measurements made by, Miehe and Keck [16] and Lion [18] have a constant strain
hold time of one hour. Haupt and Sedlan [19] held strain constant for 20,000 seconds
(more then five hours). Haupt and Sedlan [19] assumed for their model that at a very
long time period the value measured for steps of increasing strain would be identical
to values measured for steps of decreasing strain, so the mean of the two values at
20,000 seconds is taken as a point on the elastic stress response line. Lion [18]
includes elastic hysteresis in his model, Miehe and Keck [16] include plasto-elasticity
in their model but both use stress relaxation to determine coefficient values for the
elastic strain energy function.
Finally it should be mentioned that three of the six elastic force models discussed here
include a description of the Mullins or Damage effect where the level of stress
21
decreases in successive cycles; rapidly for the first few cycles on virgin material then
by a small amount over many cycles asymptotically to a stable response. This effect is
described in, Haupt and Sedlan [18], Lion [17, 18], Miehe and Keck [16].
For comparison, the six CBFNR models discussed here are listed in Table 4.1-1 with
a brief description of the function used to describe elasticity and the method by which
coefficients for the function are determined.
22
Model name Type of elastic Method by which the coefficients for the
and Reference description elastic function are determined
Berg Approximated as being the tangent to a large

Linear coefficient
[6] amplitude-damping loop.
Dynamic stiffness and phase angle are

Triboelastic
Linear coefficient determining by Fourier analysis of response
[8, 9, 12]
to sinusoidal excitation
Neo-Hookean Three material coefficients are required for

Bergstrom and
based this model. They are estimated from ‘points
Boyce
hyperelastic on’ and ‘tangents to’ the hysteresis loop
[13, 14]
model. [14].
The elastic component for this model has 5

Two term Ogden
Miehe and Keck parameters, which are found by computer
strain energy
[16] minimisation algorithm, fitting the function
function
to relaxation points.
Modified 3 term
The three coefficients required are estimated
Lion Mooney-Rivlin
[18]. Relaxation points are used to
[18] strain energy
determine equilibrium stress.
function
The 5 coefficients are found by a least

Haupt and Generalised 5
squares fit to relaxation points. These points
Sedlan term Mooney-
are approached both by applying strain and
[19] Rivlin model
by removing strain [19].
Table 4.1-1: A Summary of recent Elastic Stress models developed for Carbon Black
Filled Natural Rubber
23
4.2 Descriptions for the viscous stress component
4.2.1 Berg’s model
Berg’s model [6] is predominantly time independent, the majority of damping loss
being described by a non-linear friction force. A time dependent Maxwell element is
used, but only to modify the models response to match small frequency dependent
changes in the hysteresis loop shape. The model replicates the amplitude dependent
stiffness (known as the Payne effect [17]) and the almost constant damping loss angle,
which are characteristic features of CBFNR. Total force is described as the sum of
three parts; an elastic force; a ‘viscous’ force and a friction force, shown
schematically in Fig. 4.2.1-1.
F = k x1+ c x 2+ FFriction
x1
x2
k F Friction
c
Fig. 4.2.1-1: Schematic representation of Berg’s model
The elastic force is described by a linear stiffness (k), the viscoelastic force is
described by a linear Maxwell element (dashpot and spring in series) and friction
force described by a function that is zero at turning points (where velocity is zero) and
increase non-linearly (taking the sign of velocity) to a constant value at infinity.
Damping loss is predominantly described by the friction force, which is time
independent and has the following basic form.
24
( x1 − xo )
FFriction ∝ . sgn( x&1 )
β + ( x1 − xo ) Equation 4.2.1-1
Where, FFriction is the friction force, β is a constant, xo is the displacement at the
previous turning point and x1 is the current displacement.
Berg’s function has an additional scaling factor not shown in Equation 4.2.1-1 that
changes the form of the friction function depending on the ratio of friction force at the
previous turning point (xo) to the maximum possible value of friction force at infinite
strain. This element of the function has been excluded in Equation 4.2.1-1 for
simplicity.
The benefits of using Berg’s friction force function are that the asymmetric hysteresis
loop shape commonly reported for CBFNR stress strain plots [6, 7, 8, 11] is easily
replicated and coefficients for the function are easily determined by comparison with
measured data by varying the constant β; but the model has limited application.
Hysteresis is predominantly described by the time independent friction force, which
means that realistic stress relaxation response is not well represented. Also, as Berg
mentions himself, at high frequency the viscoelastic force described by a single linear
Maxwell element tends to zero so that damping is described by the friction force
function only.
The difficulty with a model of this type, where damping is described by a function
that rises monotonically taking the sign of velocity, is its application in dynamic
analysis software that uses the implicit Newton-Raphson Predictor Corrector method.
The model requires storage of force and displacement values at each turning point.
Turning points must be detected and then new values must be ‘assigned’ as described
by Equations 4.2.1-2 and 4.2.1-3.
25
At a turning points; Fo = Fo + ∆F Equation 4.2.1-2
And; Xo = Xo + ∆X Equation 4.2.1-3
Where Fo and Xo are force and displacement at the previous turning point
respectively, ∆F and ∆X are change in force and displacement since the previous
turning point respectively.
Assigning values to variables is not a standard operation in dynamic analysis software
that uses the Newton-Raphson Predictor Corrector method and if attempted will cause
the algorithm to fail. It may be possible to overcome this difficulty by modifying the
algorithm but this would require advanced programming and mathematical
knowledge, and if it where achieved the result is likely to be inefficient; since turning
points must be detected and the simulation halted, then restarted with the reassigned
turning point values.
4.2.2 Triboelastic model
The Triboelastic model, introduced by Turner [7] and further developed by Coveney
and Johnson [8] is a time independent model.
F= k x + F 1 Damping
x 1
k F Damping
Fig. 4.2.2-1: Schematic representation of the Triboelastic model
26
Total force is described by the sum of two parts (Fig 4.2.2-1), a linear elastic element
and an element that describes the shape of a velocity independent hysteresis curve that
is zero at turning points (at zero velocity) and increases non-linearly (taking the sign
of velocity) to a constant value at infinity.
The Triboelastic model is based on a phenomenological description that ‘imagines’ a
large number of microscopic, one dimensional, Coulombic elements, linked by
springs, resulting in an square root relationship between force and displacement that
has the following form:
FDamping ∝ ( x − xo ) 2 . sgn( x& )

1
Equation 4.2.2-1
Where, FDamping is damping force, x is current displacement and xo is displacement at
the previous turning point.
The Triboelastic model however has the same limitation as Berg’s model. Being time-
independent stress relaxation is not modelled and the describing function requires
values of force and displacement at the previous turning point to be stored and
reassigned causing difficulty in implementation in automatic dynamic analysis
software.
4.2.3 Rate dependent Triboelastic models
Coveney and Johnson [9] explore two possible modifications to the Triboelastic
model described above. These are the ‘Triboelastic visco-solid model’ (TVS) and the
‘Rate dependent Triboelastic model’ (RT). For the TVS model a Maxwell element is
added to the standard Triboelastic model making it almost identical to Berg’s model
(described in section 4.2.1). Since the TVS model is very similar to the Berg model it
has the same limitations; limited ability to describe stress relaxation, no viscous
27
damping component at high frequency and a requirement for assigned variable values
at turning points.
The RT approach is to replace the Triboelastic element with a non-linear Maxwell
element that uses a ‘power’ relationship to achieve the predominantly rate
independent damping force; this is shown schematically in Fig. 4.2.3-1.
n
F = k x1+ c x 2 The value of ‘n’ is
approx. 0.11 to 0.15
x1
x2
k
c
Fig. 4.2.3-1: Schematic representation of the Rate Dependent Triboelastic (RT)

model
The RT model however has two failings; by describing damping with a power law the
Triboelastic inverse square relationship, which approximates the asymmetric
hysteresis loop shape of CBFNR, is lost and being a function of velocity only it does
not have the flexibility of Berg’s friction function which is easily adjusted, (by
varying the constant β) to describe the measured hysteresis loop. Secondly when ‘n’
has a low value, which is required to describe the materials almost time-independent
dF
damping, sudden changes in the force vector at zero velocity (where = ∞ ) causes
dx&
simulation difficulty. Numerical simulations using the Newton-Raphson Predictor
Corrector method require smooth functions for trouble free operation [41, 44]. To
achieve this in the RT model the power relationship must be changed to a standard
linear Maxwell element at low velocity, i.e. below some value of x&2 , n=1. Although
28
this is easily implemented the question of…‘at what velocity do we change the
function from linear to non-linear so that a given simulation does not fail but the
model still represents the components damping properties’…is an additional
complication for a modeller to consider. Fig 4.2.3-2 illustrates this problem. The
continuous line shows the form of a non-linear damping function dependent on xn
where ‘n’ has a low value. The dashed line represents linear damping where ‘n = 1’.
+Ffriction
-x2 +x2
-Ffriction
Fig. 4.2.3-1: Illustration showing the requirement for a linear viscous relationship at
low velocity to prevent rapid changes in the force vector
4.2.4 Bergstrom and Boyce model
Bergstrom and Boyce [13] discussed the micro-mechanical behaviour of CBFNR and
developed a constitutive model that is the sum of two parts, an equilibrium response
(elastic force) and a ‘time-dependent deviation from equilibrium’ (visco-elastic force).
This model is similar to the Triboelastic RT model (described above) with just two
differences; equilibrium response is described by a hyperelastic model (see section
4.1) and time dependent response is a function of both velocity and displacement
raised to a power; this is shown schematically below in Fig. 4.2.4-1.
29
Bergstrom and Boyce described the elastic force (FElastic) by a Neo-Hookean based
hyperelastic function (see section 4.1) and the viscous force by a function that has the
following form:
FViscous = c( x x& )
n
Equation 4.2.4-1
Where Fviscous is the damping force, x is displacement across the visco-elastic
element, x& is velocity across the viscoelastic element, ‘c’ is a damping coefficient
and ‘n’ the power term is approx. 0.25
F=F +F
Elastic Viscous
k
F Elastic
F
Viscous
Fig. 4.2.4-1: Schematic representation of the Bergstrom and Boyce model
In their report [13] Bergstrom and Boyce show good correlation with measured data.
The addition of displacement or strain dependence x may help with the functions
ability to fit measured data i.e. achieve the asymmetric hysteresis loop shape, but the
description suffers from the same drawback as the rate dependent Triboelastic RT
model regarding its application in dynamic analysis software. Where the Newton-
Raphson Predictor Corrector method is used a non-linear Maxwell element using a
power law with a value of n = 0.25 results in rapid changes in the force vector at low
velocity causing computational difficulties.
30
4.2.5 Miehe and Keck
A one-dimensional interpretation of the constitutive model developed by Miehe and
Keck [16] is shown schematically in Fig 4.2.5-1 with the relevant descriptive
functions (Equations 4.2.5-1 & 4.2.5-1). This is similar to the ‘Berg’ and ‘Triboelastic
viscous solid (TVS)’ models described above. Here though the visco-elastic and
plasto-elastic elements are described by exponential functions of strain, which have a
larger number of parameters and therefore give the model greater ability to match
trends in the measured data.
F
x1
Felastic Fplastoelastic x2
Fviscoelastic
Fig. 4.2.5-1: Schematic representation of the Miehe and Keck model
F visco-elastic = A exp [Bx 1 + Cx 2 ] x& 2 Equation 4.2.5-1
F plasto-elastic = P exp[Qx1 ] Equation 4.2.5-2
Where, Fvisco-elastic is the visco-elastic damping force Fplasto-elastic is the plasto-elastic
damping force A, B, C, P & Q are constants.
Miehe and Keck [16] showed good correlation between measured and modelled strain
responses up to 200% in their report. The model describes elasticity using a two-term
Ogden function, also ‘Mullins effect’: stress softening during the first loading cycles
31
is described, giving the model a total of 20 parameters. However, a description of
Mullins effect is not required in a vehicle model because the rubber components
undergo many strain cycles at all levels early in their long life, so that the stress
softening effect becomes insignificant.
The nonlinear plasto-elastic and visco-elastic stress descriptions give this model the
ability to match a wide range of data measurements, but the large number of
parameters means that a computer minimisation algorithm is required to determine
values for these functions.
4.2.6 Lion
Lion [18] presented a phenomenological model for carbon black filled natural rubber
that described, non-linear elasticity, non-linear elastic hysteresis (plasto-elasticity),
non-linear visco-elasticity and Mullins stress softening. This model has the same
modular components as the Miehe and Keck model described above (Fig. 4.2.5-1),
however the functions differ. Each element is described by a strain dependent
function. Polynomial functions that include ‘Neo-Hookean’ and ‘Mooney-Revlin’ as
special cases are used as non-linear multiplying terms in the description of each
component i.e., elasticity, plasto-elasticity and visco-elasticity are all non-linear
functions of strain. For the viscoelastic element this strain magnitude dependent term
is combined with an exponential relationship that describes non-linear rate
dependence, so that:
σ v = f( ε ,ε&) Equation 4.2.6-1
Where, σ v ,ε and ε& are viscoelastic stress, strain and strain rate respectively.
The constitutive equations and viscoelastic description for this model given by Lion
[18] are difficult to interpret and translate into a simple descriptive function that can
32
be implemented as discrete components in computer software or described by discrete
components in a schematic representation. Because of its complexity this model has
not been implemented and it is not possible to comment on its suitability for one-
dimensional modelling of vehicle components in automatic dynamic analysis
software.
4.2.7 Haupt & Sedlan
The model developed by Haupt & Sedlan [19] has elastic and viscoelastic elements
only (referred to as ‘equilibrium stress’ and ‘over stress’ elements respectively). The
Mullins effect is not described and experimental measurements show that plasto-
elasticity is not significant. The final Haupt and Sedlan constitutive model has 15
parameters describing non-linear equilibrium stress in parallel with three visco-elastic
elements that have strain-history dependent viscosity.
There are two features of this model that are not present in any of the models
described above. These are the viscoelastic element, which naturally produces an
asymmetric stress-strain response and is weakly time-dependent and ‘strain history’
dependent visco-elasticity. It was found that the non-linear Maxwell element used in
this model reproduces the basic features of CBFNR and is easily described by discrete
components and implemented in automatic dynamic analysis software. However, the
‘strain-history’ element of the Haupt and Sedlan model is complex and requires a
great deal of experimental data to determine values for its coefficients. An
interpretation of the ‘strain-history’ dependent function is given below in Equation
4.2.7-4 and a diagram showing how it could be implemented using discrete
components in automatic dynamic analysis software given in Fig.4.2.7-2. A
simplified model of the Haupt and Sedlan model with only a single visco-elastic
33
element and without strain-history dependent viscosity is shown schematically in Fig
4.2.7-1.
F
x1
Felastic x2
Fviscoelastic
Fig. 4.2.7-1: A one-dimensional and simplified schematic representation of the

Haupt and Sedlan model (with a single viscoelastic element only)
The elastic element is described by a five-term Mooney-Revlin function. The
viscoelastic force is described by the following function:
c x& 2
F viscoelastic =
x& 1 + ξ Equation 4.2.7-1
Where ‘c’ and ‘ξ’ are constants (the symbols used in this expression are not the same
as those used by Haupt and Sedlan [19]). Strain-history dependence is not described;
this function is a simplification of the Haupt and Sedlan model. The form used here is
simply a standard linear Maxwell element where the viscous force is divided by the
magnitude of strain rate ( x&1 ) plus a constant (ξ). In Haupt and Sedlan model ‘ξ’ is a
‘process dependent variable’ that has a low value at low strain rate and a high value at
high strain rate to simulate strain history dependent viscoelasticity.
34
For a small value of ξ and/or high value of x&1 Equation 4.2.7-1 produces an
exponential response described by the following function (derivation given in
Appendix 1):
⎛ k .sgn ( x&1 ) ⎞
F viscoelastic = c.sgn ( x&1 ) − (c.sgn (x&1 ) − F0 ).Exp⎜⎝ − c
.( x1 − x0 )⎟
⎠
Equation 4.2.7-2
And in response to a stepped input the visco-elastic element relaxes exponentially in
the following way, (derivation given in Appendix 2):
⎡ − ξ .k .t ⎤
F viscoelastic = F o . Exp ⎢ ⎥⎦ Equation 4.2.7-3
⎣ c
For Equations 4.2.7-1, 4.2.7-2 and 4.2.7-3, ξ is a constant, c is maximum possible
visco-elastic damping force, x&1 total strain velocity, x& 2 strain velocity across the
dashpot, Fo and x0 viscoelastic damping force and displacement at the previous
turning point respectively, x1 is displacement, k stiffness coefficient and t time.
Equation 4.2.7-2 and 4.2.7-3 show that at high velocity this viscoelastic element
produces a stable hysteresis loop enclosed by rising and falling exponential curves
(see Fig 6.2-1) and at zero velocity the damping force decays exponentially. Thus the
fundamental features of CBFNR are described. These are; an asymmetric hysteresis
loop, predominately frequency independent damping and stress relaxation. In addition
to this, the function is easily understood and easily implemented, it is also ‘smooth’
and continuous making it ideal for implementation in automatic mechanical system
simulation software that uses the implicit Newton-Raphson predictor corrector
method.
35
The Haupt and Sedlan model [19] uses three viscoelastic elements in parallel to
achieve the required fit to measured data and in addition to this, values for ‘ξ’ are
made ‘strain-history’ dependent so that stress relaxation measurements, (which
showed differing decay rates depending on preceding strain history) could be
modelled. We see in Equation 4.2.7-3 that rate of stress relaxation is partly
determined by the constant ξ. In the Haupt and Sedlan model ‘ξ' is made variable so
that when stationary the value of ξ decrease over time to a constant low value,
simulating high viscosity. As velocity ( x&1 ) increases the value of ξ increases to a
constant high value, simulating low viscosity. The model prevents maximum and
minimum values of ξ from being exceeded and the rate at which ξ changes depends
on an independent relaxation time. This behaviour can be described schematically as
discrete components by the use of an independent Kelvin element, which behaves as
an exponentially decaying memory of strain rate ( x&1 ). The visco-elastic function
(Equation 4.2.7-1) is modified as follows:
c x&
F viscoelastic = x& + Ax
2
Kelvin + ξ
Equation 4.2.7-4
1
Where c, A and ξ are constants, xKelvin is displacement of the Kelvin element to
which the force applied (Fk) is equal to x&1 ; x&1 is total strain velocity; x& 2 strain
velocity across the dashpot. This model is described schematically for a single
viscoelastic element in Figure 4.2.7-2.
36
Fk = x&1
F
x1 x Kelvin
Felastic x2 kK cK
Fviscoelastic
Fig. 4.2.7-2: A one-dimensional schematic representation of the Haupt and Sedlan

strain-history dependent viscosity model (with a single viscoelastic
element only)
In this interpretation (Equation 4.2.7-4) the viscosity variable has a range from ‘ ξ ’
minimum to ‘ A.xKelvin + ξ ’ maximum and the ‘rate of change of viscosity’ is
kk
determined by . To make this viscoelastic model identical to the Haupt & Sedlan
ck
model, force acting on the Kelvin element (Fk) would be given an upper limit thereby
limiting the lowest possible viscosity.
The concept of ‘strain history dependent viscosity’ is further developed in a second
paper by Haupt and Lion [20]; demonstrating that the description may need to be
more complex then is represented here by the single linear Kelvin element shown in
Fig 4.2.7-2.
37
4.3 Summary
1. Six models developed in resent years for modelling the dynamic response of
Carbon Black filled Natural Rubber (CBFNR) have been reviewed. These are,
Berg [6], Triboelastic [8, 9, 12], Bergstrom and Boyce [13, 14], Miehe and Keck
[16], Lion [18], Haupt and Sedlan [19]. All these models describe total stress as
the sum of an elastic (in-phase) stress and a damping (out-of-phase stress) where
each element responds independently of the other.
2. ‘Mullins’ or ‘Damage’ effect is included in some of the models discussed here
but this material behaviour is not relevant to vehicle components, which
undergo many cycles in their long life.
3. We are able to group the various descriptions for elastic stress described in these
six models in two ways. Either by the type of function used. Resulting in two
groups: Linear elastic, and Nonlinear strain energy function. Or by the method
used to determine coefficients for the elastic stress function. Resulting in three
groups: Fourier analysis, ‘Points on’ and/or ‘tangents to’ the hysteresis loop, and
a method where damping force is allowed to relax over a long period of time.
4. Models that describe damping by storing values of force and displacement at
turning points (Berg [6] and Triboelastic [8, 9]) are not suited to use in dynamic
analysis software simulations that use the Newton-Raphson Predictor Corrector
method, as the algorithm does not allow for this operation.
5. Models that use a ‘fractional power’ to describe the predominately rate
independent damping force of CBFNR (Triboelastic [12], Bergstrom and Boyce
[13, 14]), are also not suited to this type of software because the rapid change in
force vector at zero velocity can cause the algorithm to fail.
38
6. The models proposed by Miehe and Keck [16], and Lion [18] have a large
number of parameters in their descriptive functions and as a result measured and
modelled responses correlate over a wide range of strain (up to 200%). However
the large number of constants means that a computer minimisation algorithm is
required to determine their values. Also the descriptions can be complex and
difficult to implement as discrete components in multibody dynamic analysis
software.
7. Of the models reviewed here the most appropriate for the simulation of CBFNR
components is that proposed by Haupt and Sedlan [19], since it is easily
implemented as discrete components in dynamic analysis software and is
computationally robust. It also reproduces the fundamental features of CBFNR
which are; an asymmetric hysteresis loop, predominately frequency independent
damping and stress relaxation.
However, the strain history dependent viscosity described in this model is
complex and requires a great deal of experimental data to determine values for
its coefficients.
39
Chapter 5
Test rig design, experimental procedure and measurement
for rubber components
5.0 Introduction
The characteristics of two Carbon black filled natural rubber components (CBFNR)
from the Warrior Armoured Personnel Carrier (APC) Track Running Gear were
measured. These two components were the ‘road wheel tyre’ and the ‘track link
bush’. Road wheel tyre measurements are simply radial force-displacement responses
where the load is applied perpendicular to the wheel’s circumference by a ridged flat
steel surface to simulate contact with the tracks links. The wheel does not rotate;
measurement and analysis of a rolling solid rubber tyre would be the subject of further
work. The track link bush was measured in two directions, radial (perpendicular to the
bush axis) and torsional (about the track bush axis). Of the six degrees of freedom,
these two bush dimensions are the most relevant to the simulations of track motion
and frequency response. These two track bush dimensions (radial and torsional) are
treated here as two separate components; a three dimensional constitutive material
model is not developed. This simplification can be justified because the objective here
is to create a simple one-dimensional model that captures the components basic
stiffness and damping characteristics. Therefore the responses of three carbon black
filled natural rubber (CBFNR) components are investigated. These are; tyre radial
characteristics; track bush radial characteristics and track bush torsional
characteristics.
These three components have been chosen firstly because of their importance in any
track running gear simulation but also because they provide good data for developing
40
a generic model that could describe any other rubber component in the Warrior APC
running gear. Tyre measurements exercise the material in compression only but its
geometric cross-section changes considerably as it is compressed against the flat
surface. The track bush torsion measurement exercises the material predominantly in
shear and the track bush radial measurement exercises the material predominantly in
compression. A model that describes these three track components will be ‘general
purpose’.
The response of each component to steady sinusoidal displacements with small
amplitude and varying preloads, and with a varying amplitude and constant preload,
has been measured to determine parameters for, elastic, geometric and viscoelastic
descriptions. In addition to this, measurements were made at frequencies ranging from
0.1Hz to 20Hz to illustrate the components insensitivity to varying strain rate and
stress relaxation to determine values for time-dependent parameters. Also the track
bush torsional response to a dual-sine displacement history was measured for
comparison with the response reported by Coveney and Johnson [8] and to simulate
the type of strain history (combined high-frequency low-amplitude and low-frequency
high-amplitude displacement) a component might experience on the vehicle.
Temperature effects are not studied since Warrior APC track components operate well
above the materials glass transition temperature where modulus and loss angle are
almost constant. The glass transition temperature for carbon black filled natural
rubber occurs at around -40°C (see Figs. 3.1-2, 3.1-3).
41
5.1 Warrior APC track rubber components
A B
Fig. 5.1-1: Warrior APC rubber track components; (A) A single Track link (B) Track
bush sections removed from the track link casting (C) Road wheel tyres
5.1.1 Road wheel Tyre
Road wheel tyres are made from a solid layer of CBFNR moulded onto the wheel’s
aluminium wheel hub. Road-wheel tyre material is 60phr (parts per hundred rubber by
weight) N550 natural rubber (AVON compound code: 4X59). Tyre dimensions are;
inside diameter = 538mm; outside diameter = 613mm; width = 128mm. Figure 5.1-C
shows three road wheels on the vehicle. A wheel is made from an assembly of two
identical cast aluminium hubs each with a moulded rubber tyre. These ‘half-wheels’
are bolted back-to-back so that the tyres run either side of the track horn. It is the tyre
of one ‘half-wheel’ that is the subject of this study. The vehicle has twelve road
wheels and weighs approximately 27 tonne therefore when stationary each tyre carries
a load of around 11kN. The road wheel tyre measurements carried out in this study
range up to 40kN, more then three times the tyres static load.
42
5.1.2 Track bush
Track bush material is 40pphr N200 natural rubber and when fitted into the track link
casting its dimensions are; inside diameter = 31mm; outside diameter = 42mm;
combined length of all five bushes (i.e. joint length) = 425mm. The joint between
adjacent tracks links is made up of five individual sections of bush (Fig. 5.1-1B) each
moulded onto a steel sleeve with an octagonal centre that engages with the track pin.
The response of individual bush sections is not measured in this investigation; it is the
response of the joint assembly that is measured. Therefore for the purpose of this
study the term, ‘track bush’ refers to the assembly of five individual rubber sections.
Before being fitted to the track link casting the bush sections have an outside diameter
of 47mm. The material therefore has a high degree of pre-compression when the track
is unloaded, being compressed from its relaxed state of 47mm diameter to 42mm
diameter. It is assumed that the bush has been designed so that the material is under
compression even when it experiences the maximum amount of torsion (approx 23°)
when passing around the vehicles driving sprocket and idler wheel. This design
ensures that the outer diameter of the bush does not rotate relative to the track link
casting under normal operating conditions. Figure 5.1A shows the assembled track
link casting and bush sections. All motion between adjacent links (neglecting pin
clearance and small amount of strain in metal components) is possible only by
torsional, radial and longitudinal motion of the track bush rubber.
Track link joints have a designed static equilibrium angle of 10°; this is commonly
referred to as the tracks ‘live-angle’ and is the angle between adjacent track links at
which there is no torsional strain about the track pin. The purpose of the ‘live-angle’
is to minimise the maximum amplitude of torsional strain in the bush rubber. So that
maximum rotational amplitude occurs in one direction as the track joint passes over
43
drive sprocket and idler wheel, and in other direction as it is traverses the top span and
ground contact.
When the track is assembled on the vehicle it is tensioned to approximately 13kN.
Radial bush measurements carried out in this study range up to 50kN, more than three
times static bush load.
5.2 Test rigs design and experimental procedure
A B C
Fig. 5.2-1: (A) Measurement of track bush torsional characteristics by rotation about
the track bush axis (B) Measurement of Track bush radial force and
displacement (C) Measurement of road wheel tyre radial force and
compression
Test rigs were constructed to measure each of the three track components: track bush
torsion, track bush radial and road wheel tyre radial characteristic, shown above in
Figures 5.2-1 A, B and C respectively. Each component was exercised by a
displacement-controlled hydraulic cylinder. For drawings detailing test rig design,
data acquisition and control see Appendix 7. In each case the effect of four variables
were investigate, preload, amplitude, frequency and time. The four tests were as
follows:
(I) Low amplitude at various preloads, 1Hz sinusoidal displacement
(II) Constant preload at various amplitudes, 1Hz sinusoidal displacement
44
(III) Constant amplitude and constant preload at, 0.1Hz, 1Hz, 10Hz and 20Hz
sinusoidal displacement.
(IV) Stress relaxation: Response to a stepped displacement over time.
In addition to the tests listed above, two further measurements where taken. A
measurement of the track bush torsional response at various radial loads has been
made to investigate the degree of interaction between these two components, this
result is presented in Section 5.7. Also the track bush torsional response to dual-sine
displacement has been measured. This replicates the dual-sine test reported by
Coveney and Johnson [8]. The frequency ratio between secondary and primary sine
waves is 15:1, amplitude ratio 10:1. The dual-sine measurement is presented in
Section 5.8.
Before the time domain measurements described above where conducted, components
were allowed to normalise to room temperature (17° - 20°C).
Also the frequency response of each test rig was measured so that resonance effects
would be avoided. These test rig frequency response measurements (and a short
discussion of methodology and associated issues) are presented in Appendix 3. Track
components time domain response measurements are shown to be valid up to the
following frequencies:
• Track bush torsional force measurement (Fig. 5.2-1A) : 6Hz
• Track bush radial force measurement (Fig. 5.2-1B) : 75Hz
• Tyre radial force measurement (Fig. 5.2-1C) : 20Hz
45
5.2.1 Data Acquisition and Signal Processing
The following points cover the issues associated with data acquisition and signal
processing.
• Force is measured by strain gauge load cell, displacement by Linear Variable
Displacement Transducer (LVDT), acceleration by piezoelectric transducers.
• Calibrated force, displacement and acceleration signals were recorded to computer
memory via a standard data acquisition board that has a maximum acquisition rate
of 100kHz.
• Inline low-pass filters set to one quarter the sample rate frequency where used to
prevent aliasing. For example: A 1Hz strain cycle was collected at a rate of 400
samples per second and the low pass filters set to 100Hz.
• Five cycles where averaged to ‘smooth’ cycle-to-cycle variation and sample rate
set to collect 400 samples per cycle. Therefore the maximum sample rate required
was 8000 samples per second for a 20Hz strain cycle frequency; well within the
data acquisition board’s specifications.
• Particular care was taken to compensate for force due to the acceleration of test rig
components that connect load cell and track component. This source of error is
proportional to the amplitude of displacement and the square of acceleration. An
accelerometer was attached to the load cell. Then the true force applied to the
component measurement was found simply by subtracting the product of
acceleration and the mass of components connecting load cell and component.
• Before taking measurements, the components where exercised through 20-30
cycles at maximum load to remove the stress softening (Mullins effect) seen on
the first loading cycles of new unstrained rubber.
Attention to the above points enabled repeatable measurements to be made.
46
5.3 Measurement I:
Low amplitude displacement with various preloads, 1Hz sinusoidal displacement
The purpose of this measurement was to determine coefficients for polynomials that
describe, elastic force and visco-elastic force relative to absolute strain (or absolute
deformation) of the rubber component.
For a CBFNR model it is assumed that, in response to stable cyclic motion, the elastic
force lays equidistance between the maximum and minimum damping force values.
This assumption is best illustrated in the measured response of Figure 5.3.1-2, where
the elastic response is taken as the ‘mean’ of two lines drawn through the turning
points of small amplitude hysteresis loops of differing preload.
This assumption is common to all elastic stress models discussed in Section 4.1 and is
an outcome of their descriptions for viscoelasticity, which have the same magnitude
in both directions i.e. there are not differing damping coefficient depending on the
direction of motion since the previous turning point.
Here the experimental method used to find a function that describes the elastic force
differs from that used by, Mieche and Keck [16], Lion [18] and Haupt and Sedlan
[19], who found equilibrium stress by a series of stress relaxation measurements
(Table 4.1-1). It is assumed here that the effect of stress relaxation on the measured
mean position of a small amplitude hysteresis loops can be removed by first setting
the preload level then increasing the amplitude of a sinusoidal displacement so that a
high level of both increasing and decreasing viscoelastic force is generated, then
reducing the displacement to the small amplitude. It is assumed that this process
stabilizes the hysteresis loop so that its mean value is stable from cycle to cycles (does
not relax further) and lies on elastic force line. By this method the time required to
collect data to determine the elastic force response is reduced from more then a day to
47
less then 60 minutes. However, this method has not been thoroughly validated.
Validation would require careful measurement and would be the subject of further
study.
This method of determining a polynomial relating force to displacement by taking the
mean point through small amplitude hysteresis loops of varying preload has a
secondary benefit. The measurements also provided data that enables the
determination of a viscoelastic ‘geometric multiplier’ or ‘strain function’. Changing
geometry as in the case of the radial compression of a solid rubber tyre not only
produces a non-linear elastic component; viscoelastic force is also dependent upon
absolute deformation. It is assumed here that the change in viscoelastic force due to a
components changing cross-section can be measured by comparing the amplitude of
hysteresis loops that have the same displacement amplitude but have different
preloads. The effect of changing geometry is then modelled simply by multiplying the
viscoelastic elements response by a function of displacement.
The procedure for the low-amplitude, varying displacement measurement was as
follows:
• The preload was applied.
• The amplitude of a 1Hz sinusoidal motion was increased to a large value so
that the viscoelastic force approaches a constant value in both the forward and
reverse directions i.e. a fully developed hysteresis loop.
• Amplitude was slowly reduced to a low value and after a short settling time
the data for five cycles was recorded.
This sequence of operations was repeated at each preload setting, with care taken each
time to ensure that the low amplitude displacement was identical within the limits of
the measurement and control system.
48
5.3.1 Elastic force description
The elastic force is taken as the least mean square fit to the mean of two lines; one
connecting the maximum turning point of each low amplitude hysteresis loop, the
other connecting the minimum turning points (Figures. 5.3.1-1, 5.3.1-2 and 5.3.1-3).
Figures 5.3.1-1 and 5.3.1-2 show the track bush response in each of the two
dimensions, torsional and radial respectively. A linear fit has been used in both cases
as this gives a good approximation and is sufficient for vehicle component simulation.
Notice that the response in torsion (Fig.5.3.1-1) is close to zero at 10° as it should be
since the Warrior APC track links have a ‘live-angle’ (static equilibrium angle) of ten
degrees. Also notice that the least mean square linear fit to the radial response (Fig.
5.3.1-2) does not pass though zero force at zero displacement. A possible explanation
for this is that these measurements where taken early in the research before the ‘long
relaxation time’ behaviour of CBFNR was fully appreciated. The procedure described
above which removes this effect was not used in this case but it is expected that if
these measurement where repeated with care the linear fit would pass through zero
force at zero displacement.
49
400
200
Torque (Nm)
0 y = 12.4x - 130.4
-200
0 10 20 30 40
Track angle (Degrees)
Fig. 5.3.1-1: Track bush torsional elastic-force response
50000
40000
30000
Force (N)
20000
y = 8.18E+07x + 1.81E+03
10000
0
0 0.0001 0.0002 0.0003 0.0004 0.0005 0.0006
Displacement (m)
Fig. 5.3.1-2: Track bush radial elastic-force response
50
40000
y = 1.82E+11x3 - 2.14E+08x2 + 2.17E+06x + 1.21E-09
30000
Radial Force (N)
20000
10000
0
0 0.001 0.002 0.003 0.004 0.005 0.006
Tyre compression (m)
Fig. 5.3.1-3: Road wheel tyre elastic-force response
Figure 5.3.1-3 shows the road wheel tyre response to small amplitude sinusoidal
displacements at varying preload but identical amplitude. In this case the elastic force
response is described by a cubic polynomial. It is significant that the least mean
square fit does pass through zero, since this gives confidence in this method of
determining the elastic-force response.
In summary, from these measurements we have the following three functions, which
describe the elastic force response of each component:
1. For track bush torsional elastic Torque:
Fe = 12 .4 θ − 130 .4 Nm Equation 5.3.1-1
Where, Fe is the elastic torque component and θ is the angle between adjacent tracks.
51
2. For track bush radial elastic force:
Fe = 81.8 × 10 6 x N Equation 5.3.1-2
Where: Fe is elastic force and x is track bush radial displacement.
3. For road wheel tyre radial elastic:
Fe = 1.82 × 10 11 x 3 - 2.14 × 10 8 x 2 + 2.17 × 10 6 x N

Equation 5.3.1-3
Where: Fe is elastic force and x is tyre compression.
5.3.2 Geometric multiplying function
It is particularly noticeable in Figure 5.3.1-3 that the amplitude of the viscoelastic
response increases with preload (hysteresis loops are larger at higher preloads). This
is a geometric effect causes by the changing cross section of the tyre. A multiplying
function that describes this effect for each of the three components was found by
subtracting the elastic response (Equations, 5.3.1-1, 5.3.1-2, 5.3.1-3) from each low-
amplitude varying-preload measurement (Figures, 5.3.1-1, 5.3.1-2, 5.3.1-3) then
fitting a least mean square line to the maximum and minimum turning points. The
result is shown below in Figures, 5.3.2-1, 5.3.2-2, and 5.3.2-3.
52
100
y = 0.64x + 19.14
Torque (Nm)
-100
0 10 20 30 40
Fig. 5.3.2-1: Track bush torsional geometric factor
5000
2500
Force (N)
-2500
-5000
0 0.0001 0.0002 0.0003 0.0004 0.0005 0.0006
Displacement (m)
Fig. 5.3.2-2: Track bush radial geometric factor
53
4000
y = 3.24E+05x + 5.97E+02
2000
Force (N)
-2000
-4000
0.000 0.002 0.004 0.006
Fig. 5.3.2-3: Road wheel tyre radial geometric factor
We see from these graphs that the track bush radial response (Fig.5.3.2-2) does not
show any significant geometric effect but that both the track bush torsional response
and the road wheel tyre response do. To determine coefficients for these two
geometric functions the hysteresis loops have been simply bound by a linear function.
The multiplying function in each cases is therefore a linear scalar, so that
mx 0 + c
f (x 0 ) = , where f (x 0 ) is the multiplying function, x0 is the components absolute
c
displacement. ‘m’ and ‘c’ are constants. This function can be simplified to,
f (x 0 ) = h.x 0 + 1 ,
m
where x0 is the components absolute displacement and h = .
c
Therefore from the measurements shown in Fig.5.3.2-1 and Fig.5.3.2-3 we have the
following two functions describing change in visco-elastic force due to geometry:
54
1. Track bush torsional geometric multiplier.
f ( x0 ) = 0.033 x0 − 10 + 1 Equation 5.3.2-1
In Equation 5.3.2-1 the reference angle (x0 = 0) is taken as being the position where
adjacent track link castings are inline. The addition of ‘10’ in this equation is
therefore to correct the function for track bush ‘live-angle’.
2. Road wheel tyre geometric multiplier.
f (x0 ) = 543.x0 + 1 Equation 5.3.2-2
In both Equations 5.3.2-1 and 5.3.2-2, f (x 0 ) is the geometric multiplying function and
x0 is the components absolute displacement.
55
5.4 Measurement II:
Constant preload at various amplitudes, 1Hz sinusoidal displacement
Each of the Warrior APC components was exercised at various amplitudes but
constant preload by a 1Hz sinusoidal displacement. The purpose of this measurement
is to produce data from which coefficients for the viscoelastic elements of the
component model can be determined.
Measurements are presented below in Figs 5.4-1, 5.4-2 and 5.4-3. The elastic-force
line (as determined in Section 5.3.1) is show on these charts so that the relationship
between the viscous and elastic forces can be seen.
As was mentioned above, measurements of track bush radial response were carried
out early in this research before the ‘long relaxation time’ characteristics of CBFNR
where appreciated. It is believed that this is the reason that the measured response
plots of Figure 5.4-2 do not lie equidistant about the elastic-force line.
400
300
200
Torque (Nm)
100
-100
-200
-300
0 5 10 15 20 25 30 35
Fig. 5.4-1: Track bush torsional force-displacement response
56
50000
Force (N) 40000
30000
20000
10000
0
0 0.0001 0.0002 0.0003 0.0004 0.0005
Displacement (m)
Fig. 5.4-2: Track bush radial force-displacement response
50000
40000
Radial load (N)
30000
20000
10000
0
0.000 0.002 0.004 0.006
Fig. 5.4-3: Road wheel tyre radial force-displacement response
An important and consistent feature of these graphs (Fig 5.4-1, 5.4-2 & 5.4-3) is that
at high amplitude the viscoelastic force response is not parallel with the elastic force
line. The viscoelastic force continues to increase.
57
5.5 Measurement III:
Constant amplitude and constant preload at various frequencies
The object of this measurement is to demonstrate the insensitivity of carbon black
filled natural rubber components to frequency variation. Measurements at constant
amplitude and constant preload at 0.1Hz, 1Hz, 10Hz and 20Hz are presented in
Figures 5.5-1 and 5.5-2. Measurements at higher frequencies where not possible due
to the high force generated by accelerating test rig masses and test rig resonance.
Figures 5.5-1 and 5.5-2 show that the response of carbon black filled natural rubber
components do not significantly change over the frequency range 0.1Hz to 20Hz. This
is an expected result, agreeing with the frequency response of ‘Truck Tread’ shown in
Figures. 3.1-4 and 3.1-5. We see here though that in detail the characteristic
asymmetric shape shown in Figure 5.5-2 is unaltered by the changing frequency.
20000
18000
16000
Force (N)
14000
12000
10000 0.1 Hz
1.0 Hz
8000 20 Hz
6000
0.0025 0.003 0.0035 0.004
Fig. 5.5-1: Road wheel tyre force-displacement response at several frequencies
58
50000
40000
30000
Force (N)
20000
10000 1 Hz
10 Hz
20 Hz
0
0 0.0001 0.0002 0.0003 0.0004 0.0005
Displacement (m)
Fig. 5.5-2: Track bush radial force-displacement response at several frequencies
This result brings us to the conclusion that, as a first approximation damping would
be represented by a frictional description not a viscous (velocity dependent)
description. However, we will see in the next Section (5.6) that this material also
exhibits stress relaxation; a feature that contradicts the frictional damping model.
59
5.6 Measurement IV: Stress relaxation:
Force response to a stepped displacement over time
Figure 5.6-1 shows the track bush response to a stepped torsional displacement, both
total force and the elastic-force (determined by Equation 5.3.1-1) are shown for
comparison. Only a few stress relaxation measurements were made: a comprehensive
and detailed investigation of each track component’s response to a variety of stepped
inputs has not been undertaken. The reason for this is that it has been shown by Haupt
and Sedlan [19] that stress relaxation response depends upon strain history and a
‘strain history dependent viscosity model’ is needed to describe it. This level of
complexity is excessive for a Warrior APC track component model.
250
200
150
Force (N)
100
50
Total force
Elastic force only
0
0 5 10 15 20 25
Time (seconds)
Fig. 5.6-1: Track bush torsional stress relaxation
Figure 5.6-1 shows the characteristic features of a CBFNR stress relaxation response.
These are an immediate rapid fall in force in a short time followed by a slow fall in
force at long time. This response is not described by a single decaying exponential
function.
60
23000
21000
Force (N)
19000
17000
15000
0 20 40 60 80 100 120
Time (Seconds)
Fig. 5.6-2: Road wheel tyre stress relaxation
Figure 5.6-2 shows a stress relaxation measurement for the road wheel tyre, again a
typical carbon black filled natural rubber response
61
5.7 Track bush torsional response at various radial loads
600
400
Torque (Nm)
200
0
0kN
20kN
-200
30kN
46kN
-400
0 10 20 30 40
Fig. 5.7-1: Track bush torsional response at varying radial loads
Figure 5.7-1 shows the effect that changing track bush radial load has on the track
bush torsional response when subject to stable sinusoidal motion at 0.2Hz. At each
setting the radial load was applied with the bush stationary at a track angle of 10°; the
tracks ‘live-angle’ where the bush is not strained in torsion.
This measurement shows that although these two track link bush dimensions are
modelled and measured as independent components they do interact, but that the
interaction is not so excessive that its exclusion from the model will produce an
unrepresentative description. The measurement shows that for steady sinusoidal
motion and constant radial preload, torque about the bush axis decreases slightly by a
constant value as track tension (radial load) increases but also that stiffness and
damping are not significantly affected.
An equivalent measurement showing the effect on radial response of changing
torsional load has not been made but this could be the subject of further work.
62
5.8 Track bush torsional response to duel-sine displacement
300
200
Torque (Nm)
100
-100
5 10 15 20 25 30
Track link angle (Degrees)
Fig. 5.8-1: Track bush torsional response to dual-sine displacement
Figure 5.8-1 shows track bush torsional response to duel-sine displacement. The
amplitude and frequency ratios are taken from Coveney and Johnson [8] so that a
comparison could be made with this work. Secondary to primary frequency ratio is
15:1; secondary to primary amplitude ratio is 10:1.
Primary frequency = 0.1Hz, Primary amplitude = 7.5°, Secondary frequency = 1.5Hz,
Secondary amplitude = 0.75°.
The purpose here is to simulate the type strain history (combined high-frequency low-
amplitude and low-frequency high-amplitude) a component might experience on a
vehicle.
63
Chapter 6
Development of a model for rubber components
6.0 Introduction
The literature review of models developed for carbon black filled natural rubber
(CBFNR) components (Chapter 4) showed that a viscoelastic model based on the
work of Haupt and Sedlan [19] best describes the characteristics of (CBFNR) and is
suited to software that uses the Newton Raphson Predictor Corrector method. In
Chapter 5 functions that describe the elastic force and the increase in viscoelastic
force due to changing geometry where found.
The objective here in Chapter 6 is to develop a generic model that can describe the
behaviour of all CBFNR components in the Warrior Armoured Personnel Carrier
(APC) running gear by simulating one-dimensional force-displacement response. It is
important to note that the model developed here is a phenomenological description
and therefore cannot be guaranteed to simulate the response to stain rates or strain
amplitudes that have not been measured.
It is response at the component level that is described by the model; material is not
considered at the micro-mechanical level and constitutive equations are not
developed. Hyper-elastic constitutive models, which describe the nonlinear elastic
behaviour of rubber, are not used; elasticity is described by a polynomial fit to
measured data (Section 5.3.1). Damage; the reduction in viscoelasticity over time
(also known as the Mullins effect) is not modelled nor are thermal effects or plasto-
elasticity (also known as equilibrium stress hysteresis). The model is deliberately
simplified as far as possible but retains elements that are important for vehicle
64
component simulations so that it describes the force-displacement response to high
amplitude, low amplitude, multiple frequency and transient strain histories.
Coefficients for descriptive mathematical functions used in the model developed here
are found by manually changing their values and by visual comparison matching the
modelled response to the measured response. Computer algorithms are not used other
then ‘least mean square fit polynomials’ common to most standard graphical software
packages.
6.1 The simplified Haupt and Sedlan model
The viscoelastic elements of the CBFNR model developed here are based on the work
of Haupt and Sedlan described in Section 4.2.7. Haupt & Sedlan use three parallel
visco-elastic elements to describe the response of CBFNR in their model [19] but at
this stage (before comparing the models response with experimental data) it must be
assumed that any number of these elements maybe required for the Warrior Armoured
Personnel Carrier (APC) track components.
The simplified model used here differs from that used in the Haupt & Sedlan [19]
model in two ways. Firstly, the viscoelastic element does not including a description
of ‘strain history dependent viscosity’ and secondly; the elastic force (Fe) and a
viscoelastic geometric multiplying term f (x0 ) are described by polynomial fits to
direct measurements, whereas in Haupt and Sedlan’s model, elasticity is described by
a strain energy function and geometric effect by a three-dimensional constitutive
material model.
The use of a geometric multiplier means that the model developed here has two parts
(Fig 6.1-1), one part that sums the elastic and viscoelastic force (Equation 6.1-1), the
other that models viscoelastic behaviour only. The reason for this is that the geometric
65
multiplier multiplies the viscoelastic force (Equation 6.1-3) before it is added to the
elastic force (Equation 6.1-1). The total response (F) is constructed in reverse to the
way that it was deconstructed in the measurements of Sections 5.3.1 and 5.3.2.
F
x0 x0
k 1 k 2
k K
x1 x2 xK
Fe Fv
η 1 η 2 η K
Fig. 6.1-1: Schematic representation of the simplified Haupt and Sedlan carbon
black filled natural rubber component model
F = Fe + Fv Equation 6.1-1
cK
ηK =
x& 0 + ξ K Equation 6.1-2
( )∑ η
N
Fv = f x 0 K x& K Equation 6.1-3
K =1
Where, K = 1, 2, …N and f ( x0 ) is the geometric multiplying function
Fe = Ax03 + Bx02 + Dx0 + x0

Equation 6.1-4
Where, A, B and D are coefficients for the elastic force polynomial. η is the
coefficient of viscosity, ξk and ck, are the viscoelastic element constants, x0 is
displacement across the component and ‘F’ is applied and reaction force, Fe is elastic
force and Fv is viscoelastic force.
66
6.2 The time dependent viscoelastic element
The non-linear Maxwell element use to describe time depended viscoelastic response
is a simplified version of that used by Haupt and Sedlan [19]. Viscoelasic force is
described by the following function:
F viscoelastic =
c x& 2
Equation 4.2.7-1
x& 1 + ξ
Where ‘c’ and ‘ξ’ are constants, x&1 is strain rate across the viscoelastic element and
x& 2 strain rate across the dashpot (see Fig 4.2.7-1).
It was shown in Sections 3.3, 5.4 and 5.5 that CBFNR components produce an
asymmetric hysteresis loop in response to stable cyclic strain and although the
material has almost total stress relaxation at infinite time [19], it is insensitive to
frequency and velocity variation over a wide range (Figs. 3.1-4, 3.1-5, 5.5-1 and 5.5-
2). A Maxwell type element where the viscous part is described by Equation 4.2.7-1
has these same features when ‘ξ’ has a low value. But for a small value of ξ or a high
value of x&1 a Maxwell element where the viscous force is described by Equation
4.2.7-1 produces a time-independent exponential response of the following form
(derivation given in Appendix 1):
⎛ k sgn(x&1 )
F viscoelastic = c sgn(x&1 ) − (c sgn(x&1 ) − F0 ).Exp⎜ − (x1 − x0 )⎞⎟
⎝ c ⎠
Equation 4.2.7-2
Where, ‘c’ is maximum possible viscoelastic damping force, ‘Fo’ and ‘x0’ viscoelastic
damping force and displacement at the previous turning point respectively, ‘k’ is the
stiffness coefficient for the Maxwell spring, x1 displacement and x&1 velocity of
displacement.
67
Equation 4.2.7-2 produces a loop enclosed by exponentially rising and falling curves
centred about the, zero displacement, zero viscous force point (Fig 6.2-1).
+ve
80.0
Visco-elastic force
0
0.0
-ve
-80.0
-ve
-17.0 0.0
+ve17.0
0
Displacement
Fig. 6.2-1: Rising and falling exponential curves produced by Equation 4.2.7-2
Coefficients ‘c’ and ‘k’ in Equations 4.2.7-1 and 4.2.7-2 are determined by comparing
measured data (where the elastic and geometric components of the response have
been removed) with a plot produced by Equation 4.2.7-2 (Fig 6.2-2).
This method of determining ‘c’ and ‘k’ is evidently an approximation because it is
assumed that ξ is small, but if it were not then Equation 4.2.7-1 becomes time-
dependent and simple visual comparison between the measured and modelled
viscoelastic force component would not be possible. Also the integration required to
determine Equation 4.2.7-2 (see Appendix 1) would be far more complex.
When the predominately time independent behaviour of carbon black filled natural
rubber is considered the additional accuracy achieved by developing a ‘true’
descriptive time dependent function and the effort required to measure and match data
to this type of function cannot be justified since some approximation is adequate for
vehicle component simulation.
68
The coefficient ξ is determined separately by comparing Equation 4.2.7-3 with stress
relaxation measurements.
⎡−ξ k t⎤ Equation 4.2.7-3

F viscoelastic = F o Exp ⎢ c
⎥
⎣ ⎦
In figure 6.2-2 the viscoelastic response of four track bush torsional measurements of
constant preload and varying amplitude (see Fig 5.4-1) are compared with plots
produced by Equation 4.2.7-2. Viscoelastic response has been determined by
removing the elastic component and the geometric multiplying component then
offsetting the hysteresis loops so that their mean displacement and viscous force are at
zero.
100.0
Viscoelastic damping force (N)
0.0
Measured response
Modelled response
-100.0
-20.0 0.0 20.0
Anglular displacement (degrees)
Fig. 6.2-2: Track bush torsional viscoelastic force. Modelled using a single
viscoelastic Element (Equations 4.2.7-2)
The values of constants ‘k’ and ‘c’ are the same in each of the four plots and have
been adjusted by visually comparing the measured and modelled response to achieve
the ‘best fit’ to both small and large amplitude displacements.
69
Figure 6.2-2 illustrates two difficulties that are encountered when trying to match the
function for a single viscoelastic (N=1) element to measured hysteresis loops of
varying amplitude. Firstly, the modelled response is a compromise between
describing a ‘rounded loop’ at small amplitude, which requires a high stiffness
coefficient (k) value and a ‘flatter loop’ at high amplitude, which requires a low
stiffness coefficient value. Secondly, it is qualitatively evident that the measured
viscoelastic damping force continues to increase as amplitude increases and is not
constant relative to the X-axis at high amplitude, but the modelled response does
approach a constant value at high amplitude. These two points are important if we are
to develop a general purpose CBFNR model for vehicle components that describes
damping and stiffness over a range of amplitudes.
A better fit is possible by the addition of a second (parallel) viscoelastic element of
(the same non-linear type described by Equation 4.2.7-2) but that has lower stiffness.
The result is shown in Figure 6.2-3.
100.0
0.0
Measured response
Modelled response
-100.0
-20.0 0.0 20.0
Anglular displacement (degrees)
Fig. 6.2-3: Track bush torsional viscoelastic force. Modelled using two parallel
viscoelastic elements (Equations 4.2.7-2)
70
With the additional viscoelastic element the model has twice as many coefficients;
two stiffness values (k), two damping force values (c) and two time-dependent
parameters (ξ). Again these values have been found by manual adjustment and visual
comparison between modelled and measured hysteresis loops. The values found by
this method are subjective but the method is not excessively time consuming, values
that produce a ‘good’ match are easily found. The result achieved by using two
parallel viscoelastic elements (Figure 6.2-3) are qualitatively an improvement over
those in Figure 6.2-2, representing the measured response much better over the range
of amplitudes measured. The additional complexity is justifiable but adding further
parallel elements would not significantly improve the match. Two parallel time-
dependent viscoelastic elements are sufficient to model the response to steady cyclic
motion. Therefore for the proposed model (Figure 6.1-1), the value of ‘N’ in
Equations 6.1-3 is two.
Equivalent two-element viscoelastic force response plots are presented for the track
bush radial and road wheel tyre, Figures 6.2-4 and 6.2-5 respectively.
71
10000
Measured response
Modelled response
-10000
-0.0003 0.0000 0.0003
Dislplacement (m)
Fig. 6.2-4: Track bush radial viscoelastic force. Modelled using two parallel
viscoelastic elements (Equation 4.2.7-2)
2000
Measured response
Modelled response
-2000
-0.003 0.000 0.003
Fig. 6.2-5: Road wheel tyre viscoelastic force. Modelled using two parallel
viscoelastic elements (Equation 4.2.7-2)
It is evident that at large amplitudes the modelled road wheel tyre viscoelastic force
(Fig. 6.2-5) represents the measured response less well then either the track link bush
72
torsional or radial viscoelastic force models (Figs. 6.2-3 and 6.2-4, respectively). The
reason for this is likely to be due to one of the following characteristics, which are
unique to the tyre.
1. The tyre is unique among the components investigated here because of its
‘contact’ with the flat steel surface. The track bush is compressed into the track link
casting so that its outer diameter cannot slip under normal operating conditions and its
inner surface is moulded to a steel insert, whereas contact between the tyre and the
flat steel surface compressing it is likely to have some slip. As the tyre is loaded and
unloaded the contact patch size and the distribution of stress in the tyre depends on
the coefficient of friction between the two surfaces. Slip and stiction between these
surfaces may explain the change in hysteresis loop shape at large amplitude
displacement.
2. The tyres highly non-linear geometric shape may also contribute to the changing
hysteresis loop form.
3. Also compression between the rigid round wheel hub and rigid flat steel surface
cause some regions to be highly strained while others are unstrained. The track bush
is compressed into the track link so that is it highly strained before any load is
applied. The tyre is not preloaded; the tyre is totally unstrained before it makes
contact with the ridged flat surface so that the relative change in strain is large.
It should be emphasised though that it is only at the very larges amplitude
displacement that the tyres damping loop is poorly represented in its detail. In general
and over a wide range of amplitudes, the damping loops are well represented. At
maximum amplitude displacement the tyre load varies from approximately 1,300N to
45,000N (see Figure 5.4-3). This is large variation in load but the method being used
to describe damping is simply the sum of two exponential curves.
73
To study tyre contact and material strain a simple finite element analysis (FEA) was
undertaken. For simplicity hyper-elasticity strain energy material functions, which
describe non-linear elastic behaviour at large strains, were not used. The material is
simply described by a constant modulus, E = 20Mpa. Poisson ratio (ν) = 0.499
(G=6.67) and coefficient of friction between steel and rubber (µ) = 0.8.
Fig. 6.2-6: Quarter model of the tyre contact showing von Mises strain. Tyre
compression is 8mm. Produced using ANSYS FEA software.
Figure 6.2-6 illustrates the type of tyre deformation we might expect at high load
(approx 60kN). Strain within the tyre ranges from zero to 60%. The FEA model has
not been investigated in detail, its purpose here is to aid understanding, but it is clear
that the contact patch size and consequently the stress-strain relationship are partly
dependent on the contact surface coefficient of friction.
74
6.3 Stress relaxation and the response to dual-sine motion
Introduction
In Section 6.2 a time-independent approximation (Equation 4.2.7-2) was compared
with the response to stable sinusoidal motion to determine stiffness and damping
coefficients k and c for the model. This was possible because of the predominantly
time-independent behaviour of CBFNR. Here in Section 6.3 the model is further
developed to describe the materials response to stepped displacement and duel-sine
motion. These very different strain histories are discussed together because it was
found that the variable ‘ξ’, that partly determines the rate of stress relaxation
(Equation 4.2.7-3) is also important in the description of duel-sine response.
It is shown that it is possible to closely simulate the response to both duel-sine motion
and a stepped displacement (stress relaxation) by momentarily stiffening each of the
parallel viscoelastic elements of the simplified Haupt and Sedlan model (Fig. 6.1-1)
using ‘nested’, rapidly decaying, viscoelastic elements of the same type. But by doing
this the models response to stable sinusoidal motion developed in Section 6.2 is
compromised. The solution to this problem would be to introduce a ‘strain velocity
dependence’ that describes; high viscosity at low velocity and low viscosity at high
velocity similar to that used by Haupt and Sedlan [19] (see Section 4.27). It is
suggested here though that this complexity is not necessary for the simulation of
Warrior APC CBFNR track components in a full vehicle model, where the individual
component models should be simple track and easy to apply and some approximation
to real behaviour can be justified. Therefore the final model presented in Section 6.4
is a compromise. It has only a single stiffened viscoelastic element that is not strain
history dependent. This model approximates the response to, sinusoidal, dual-sine and
stepped displacements.
75
To study time dependence, the model was implemented in dynamic analysis software.
Measurements of the CBFNR response to dual sine and stepped displacement motion
were compared with equivalent simulations using MSC.ADAMSTM (Automatic
Dynamic Analysis of Mechanical Systems). The details of how the model was
implemented in this software are discussed in Section 7.1.
Model development
Fig 6.3-1 shows the measured track bush torsional response to a stable dual-sine
displacement history (see Section 5.8).
300
200
Torque (Nm)
100
-100
5 10 15 20 25 30
Fig. 6.3-1: Measured track bush torsional response to dual-sine displacement.
This response (Fig 6.3-1) agrees (qualitatively) with measurements reported by
Coveney and Johnson [8]. The loops produced by the secondary sinusoidal waveform
are a feature of carbon black filled natural rubber that cannot be describe by the
simplified Haupt and Sedlan model.
76
300
200
Torque (Nm)
100
-100
5 10 15 20 25 30
Fig. 6.3-2: Simulation of track bush torsional response to dual-sine displacement

produced by ADAMS simulation of the simplified Haupt and Sedlan
Figure 6.3-2 shows the response of the Simplified Haupt and Sedlan model
(developed in Section 6.2) when simulating the dual-sine measurement of Fig. 6.3-1.
Evidently the correlation between Figs. 6.3-1 and 6.3-2 is poor. It is not possible for a
model that has viscoelastic elements of the type used in the proposed model, to
produces the characteristic enclosed loops we see in dual-sine measurements. The
model must be modified. This becomes evident when considering Equation 4.2.7-2.
⎛ k sgn(x&1 )
Fviscoelastic = c sgn(x&1 ) − (c sgn(x&1 ) − F0 )Exp⎜ − (x1 − x0 )⎞⎟
⎝ c ⎠
Equation 4.2.7-2
Where, ‘c’ is maximum possible viscoelastic damping force, ‘Fo’ and ‘x0’ viscoelastic
damping force and displacement at the previous turning point respectively, ‘k’ is the
stiffness coefficient for the Maxwell spring, x1 displacement and x&1 velocity of
displacement.
77
The first term in Equation 4.2.7-2, (c sgn( x&1 ) ) , determines maximum possible
damping force and has constant magnitude. The multiplying term; (c sgn( x&1 ) − F0 ) ;
⎛ k sgn( x&1 )
and the exponential, Exp⎜ − (x1 − x0 )⎞⎟ , are both variable, dependant on F0
⎝ c ⎠
and x0 respectively. This dependence on F0 and x0 ‘scales’ the exponential so that
this function (Equation 4.2.7-2) could not produce the loops that we see in the dual-
sine measurement. The only possible solution is to make the coefficient ‘k’ variable
so that the exponentially described viscoelastic force increases more rapidly under
certain circumstances. This can produce the loops we see in Figure 6.3-1 and to do
this additional nonlinear viscoelastic elements have been introduced into the model;
the same type as those used in the simplified Haupt and Sedlan model where
viscoelastic force is described by the following function:
c x& 2
F visco-elastic =
x& 1 + ξ Equation 4.2.7-1
‘c’ and ‘ξ’ are constants, x&1 is the magnitude of velocity across the Maxwell element
and x& 2 is velocity across the dashpot.
A simple dashpot and a linear Maxwell elements were also considered as possible
ways to increase the stiffness coefficient momentarily. However the same type of
nonlinear viscoelastic element has been used because it is limited to a maximum
possible force (unlike a simple dashpot), it does not reduce to a spring element at high
frequency (like a linear Maxwell element) and its decay rate is controllable by ‘ξ’.
These additional stiffening elements are placed in parallel with each spring and are
given a relatively high value of ‘ξ’ so decay is rapid and its influence has short
78
duration. A schematic representation of this ‘four-element model’ for duel-sine
simulation is shown below in Figure 6.3-3.
Fig. 6.3-3: Four-element model: Two nonlinear viscoelastic elements each with a
nested rapidly decaying nonlinear stiffening viscoelastic element
As for the Simplified Haupt and Sedlan model (fig. 6.1-1) the following equations
apply:
F = Fe + Fv Equation 6.1-1
cK
ηK =
x& K + ξ K Equation 6.1-2
( )
Fv = f x 0 (x&1η1 + x& 3η 3 ) Equation 6.1-3
Fe = Ax03 + Bx02 + Dx0 + x0 Equation 6.1-4
79
Where, K = 1, 2, 3 and 4, x& K is the velocity across viscoelastic element K, f (x0 ) is the
geometric multiplying function. c K , ξ , A, B and D, are constants.
Tests have shown that this four-element viscoelastic model represents the response of
CBFNR to dual-sine motion and stepped displacement very well (Figures 6.3-4 and
6.3-5). Values for the variables used in these simulations are given in Appendix 4a.
300
200
Torque (Nm)
100
-100
5 10 15 20 25 30
Fig 6.3-4: Simulated track bush torsional response to dual-sine displacement

produced by ADAMS simulation of the four-element viscoelastic model
80
250
200
150
Force (N)
100
50
Simulated
Measured
0
0 5 10 15 20 25
Time (Seconds)
Fig. 6.3-5: Measured and simulated track bush torsional stress relaxation produced
by ADAMS simulation of the four-element viscoelastic model
The model has four stress relaxation variable parameters and is therefore able to very
closely simulate the stress relaxation plot but it is the nested element that has
produced the very rapid, almost instantaneous relaxation that is a feature of CBFNR,
being observed by Haupt and Sedlan [19] and Lion [18]. This stress relaxation
response is not so easily achieved if the nested elements are not used.
We have shown that the ‘four element model’ (Fig.6.3-3) simulates dual-sine
response and stress relaxation well but the model has a drawback that prevents its
implementation in this simple form. The same stiffening that produces the ‘looped’
response to dual-sine histories and rapid relaxation in response to stepped
displacement ‘corrupts’ the response to stable sinusoidal motion that was developed
in Section 6.2. By stiffening the viscoelastic elements at high velocity, the additional
nested elements change the models so that a simulation of the ‘constant amplitude
81
varying frequency’ measurement (Section 5.5) produces damping loops of changing
shape. Not the constant profiles shown in Figures 5.5-1 and 5.5-2.
It may be possible to produce a ‘compromise’ or ‘best fit’ to all data by determining
coefficients using a computer minimisation algorithm but it appears from tests that the
next step in the development of this model should be to make the coefficients k2 and
k4, in Figure 6.3-3, dependent upon stain rate. This is a process (or history)
dependence of the type suggested by Haupt and Sedlan [19]. This has not been
pursued however. A model of this type requires extensive development and would be
the subject of further work.
The approach taken here is to develop a compromise model. The final model
presented in Section 6.4 has a single stiffening element only, so that each of the strain
histories (dual-sine, single sine, and stress relaxation) is approximated. It is
considered that this compromise is sufficient for a vehicle component model where
each rubber component is a small part of a complex system. In addition to this an
effort has been made to simplify the model and make it ‘general purpose’ by using
constant ratios between variables in the viscoelastic force elements and by using
identical time constants in each of the three track components. This has reduced the
number of variables that have to be found for the viscoelastic component of the model
to just four. The final model for Warrior APC CBFNR components is presented in
Section 6.4.
82
6.4 Final model for carbon black filled natural rubber components
The final model (presented in Figure 6.4-1) describes viscoelastic damping using
three non-linear viscoelastic elements. Geometric non-linearity is described by a
multiplying function and elastic force by a polynomial. As for the ‘four-element’
model described in Section 6.3, Equations, 6.1-1, 6.1-2, 6.1-3 and 6.1-4 apply.
Fig. 6.4-1: Final model containing three non-linear viscoelastic elements
This model is a compromise between the simplified Haupt and Sedlan model
described in Section 6.1 and the ‘four-element’ model describe in Section 6.3 In this
model the coefficients, ‘k2’ and ‘η2’ are given the same values as ‘k1’ and ‘η1’
respectively. It was found that this allowed some stiffening so that dual-sine response
and stress relaxation are approximated but the effect is not sufficient to significantly
change the response to sinusoidal strains of differing frequency. Values for k1, k2, c1
and c2 are found by the method described in Section 6.2.
A further simplification has been achieved by giving the time constant of each
viscoelastic element an identical value in each of the three component models, i.e. the
tyre, the track bush radial response and the track bush torsional response.
83
c
Equation 4.2.7-3 shows that the time constant (τ) of the viscoelastic elements τ = .
k .ξ
By empirical investigation; comparing simulated relaxation and dual-sine response
with measured response it has been found that suitable values for τ1, τ2 and τ3 in each
of the models three nonlinear viscoelastic elements are 100, 0.1 and 1.0 respectively.
The result is that the number of variables in the viscoelastic model have been reduced
from nine to four: k1, c1, k3 and c3. Values for each of the three component models are
given in Appendix 4b.
300
200
Torque (Nm)
100
-100
5 10 15 20 25 30
Fig 6.4-2: Simulated track bush torsional response to dual-sine displacement.

Produced by ADAMS simulation of the final three viscoelastic element
model
84
250
200
Torque (Nm)
150
100
50
Simulated
Measured
0
0 5 10 15 20 25
Time (Seconds)
Fig. 6.4-3: Measure and simulated track bush torsion stress relaxation, produced
by ADAMS simulation of the final ‘three viscoelastic element’ model
Figures 6.4-2 and 6.4-3 show the final three-element model response to dual-sine
motion and stress relaxation respectively.
Evidently the three-element model does not describe the measured response to dual-
sine and stepped displacement as well as the four-element model. Large loops are not
formed in the dual-sine simulation and stress relaxation does not show the
characteristic initial rapid relaxation. However we do see a number of small loops in
Figure 6.4-2 and the dual-sine response is significantly ‘better’ then that produced by
the simplified Haupt and Sedlan model (Fig 6.1-1).
85
6.5 Summary
The model developed here for simulation of Warrior APC, carbon black filled natural
rubber components is a compromise between the simplified Haupt and Sedlan model
described in Sections 6.1 and the four-element model developed in Section 6.3 The
final model has three nonlinear Maxwell elements. These are two parallel elements
and one that is nested.
Parameters for the time-dependent viscoelastic component are found by the method
described in Section 6.2 where coefficients are adjusted to fit measured damping
loops by visual comparison.
The number of coefficients required for the three nonlinear viscoelastic elements in
the final model have been reduced from nine to four by two methods. Firstly, the
‘nested’ Maxwell element is given identical values to the element to which it is
applied. Secondly, the time constant of each nonlinear Maxwell element is
predetermined, having the same value in each component model.
Coefficients for the ‘four-element’ and ‘three-element’ models are given in Appendix
4a and 4b respectively.
86
Chapter 7
Comparison between measured and simulated
rubber component response
7.0 Introduction
Here the ‘final model’ developed in chapter 6 is implemented in MSC.ADAMSTM
software and simulations compared to the measured response for each of the three
Warrior APC CBFNR components. Parameter values for each of the component
models are given in Appendix 4b.
7.1 Implementation of the final model in ADAMS software
Various measured force-displacement graphs are presented in Section 7.2 with their
respective simulations. These simulations are produced by implementation of the
‘final model’ for CBFNR components (presented in Section 6.4) using
MSC.ADAMSTM software. However, because of a technical difficulty caused by the
software’s algorithm it is not possible to describe the ‘final model’ as show in Figure
6.4-1. Instead it is implemented as show here in Figure 7.1-1.
Fig 7.1-1: Implementation of the ‘final model’ in ADAMS software so that x B ≈ x A .
87
The model has these two separate parts because the viscoelastic response is multiplied
by a geometric factor (see Sections 5.3.2 and 6.1). The difficulty is that it is not
possible to describe a motion in ADAMS software as being equal to a variable. A
function that describes motion must be time dependent. This causes a problem
because the model is made up of two parts that have the same displacement, x A and
x B (Fig 7.1-1). But x B = x A , is not an allowable definition of motion.
The solution used here is to add an extremely stiff spring element (kP) in parallel with
the viscoelastic part of the model and apply a force equivalent to displacement x A
multiplied by this stiffness coefficient. The displacements of both parts are then the
k1 k
same to within a small error which depends on the ratio and 3 . For the
kP kP
simulations presented below in Section 7.2 the highest value ratio is 0.001.
88
7.2 Comparison between measured and simulated response plots
For all graphs presented in this section the grey line represents the elastic force (as
described in Section 5.3.1) and the black lines represent total force.
50000
40000
Force (N)
30000
20000
10000
0
0 0.0001 0.0002 0.0003 0.0004 0.0005
Displacement (m)
Fig 5.4-2: Measured track bush radial force-displacement response
50000
40000
30000
Force (N)
20000
10000
0
0 0.0001 0.0002 0.0003 0.0004 0.0005
Displacement (m)
Fig 7.2-1: Simulated Track bush radial force-displacement.
89
400
300
200
Torque (Nm)
100
-100
-200
-300
0 5 10 15 20 25 30 35
Fig 5.4-1: Measured track bush torsional force-displacement response
400
300
200
Torque (Nm)
100
-100
-200
-300
0 5 10 15 20 25 30 35
Fig 7.2-2: Simulated track bush torsional force-displacement response, (Several of

the loops have been omitted here for clarity).
90
50000
40000
30000
Force (N)
20000
10000
0
0.000 0.002 0.004 0.006
Fig 5.4-3: Measured road wheel tyre radial force-displacement response
50000
40000
30000
Force (N)
20000
10000
0
0 0.002 0.004 0.006
Fig 7.2-3: Simulated road wheel tyre radial force-displacement response
91
40000
30000
Force (N)
20000
10000
0
0 0.001 0.002 0.003 0.004 0.005 0.006
Fig 5.3.1-3: Measured road wheel tyre displacement
40000
30000
Force (N)
20000
10000
0
0 0.002 0.004 0.006
Fig 7.2-4: Simulated road wheel tyre displacement-force response
92
20000
18000
16000
Force (N)
14000
12000
10000
0.1 Hz
8000 1.0 Hz
20 Hz
6000
0.0025 0.003 0.0035 0.004
Fig 5.5-1: Measured road wheel tyre force-displacement response at several

frequencies
20000
18000
16000
14000
Force (N)
12000
10000
0.1Hz
8000 1.0Hz
20Hz
6000
0.0025 0.003 0.0035 0.004
Fig 7.2-5: Simulated road wheel tyre force-displacement response at several

frequencies
93
21000
19000
Force (N)
17000
Measured
Simulated
15000
0 5 10 15 20 25 30
Time (Seconds)
Fig. 7.2-6: Measure and simulated road wheel tyre stress relaxation
250
200
Torque (Nm)
150
100
50
Simulated
Measured
0
0 5 10 15 20 25
Time (Seconds)
Fig.7.2-7: Measure and simulated track bush torsion stress relaxation
94
300
200
Torque (Nm)
100
-100
5 10 15 20 25 30
Fig. 5.8-1: Measured track bush torsional response to dual-sine displacement
300
200
Torque (Nm)
100
-100
5 10 15 20 25 30
Fig. 7.2-8: Simulated track bush torsional response to dual-sine displacement
95
7.3 Summary
The comparisons between measured and simulated responses show that the model
closely approximates the response to steady sinusoidal motion and that damping and
stiffness are described sufficiently accurately for used in vehicle component models.
Stress relaxation and the response to dual-sine displacement are less well described
but this has been justified in Sections 6.3 and 6.4 by the requirement for a reasonably
simple model. A more precise simulation would require strain history dependence
(as described in Section 6.3), where the coefficients values k2 and k4 in Figure 6.3-3
would be variable. A model of this type would be the subject of further work if a high
degree of accuracy were required. The results presented here shows that the model is
satisfactory for simulation of Warrior APC CBFNR components in the first instance,
where the development of a full vehicle model is at an early stage.
96
Chapter 8
Summary of the rubber components investigation
8.0 Summary
A ‘general purpose’ time-dependent model for carbon black filled natural rubber
components has been developed for implementation in ‘dynamic simulation software’
that uses the Newton-Raphson Prediction Corrector algorithm. No attempt has been
made to describe the materials microstructure. Force-displacement measurements
have simply been deconstructed into three elements, an elastic force, a viscoelastic
force and geometric multiplier.
A number of models developed in recent years for carbon black filled natural rubber
have been reviewed and the response of three Warrior Armoured Personnel Carrier
components to various displacement histories presented. These components are, the
track link bush radial response, track link bush torsional response and road wheel tyre
radial response.
A novel method has been used to determine values for a polynomial that describes
elasticity and a function describing the effect of changing geometry. This depends
upon the assumption that by following careful measuring methodology; the magnitude
of viscoelastic force in response to small amplitude sinusoidal displacement lies
equidistant about the elastic force line.
It has been shown that for dynamic simulation software that uses the Newton-
Raphson Predictor Corrector algorithm; viscoelasticity is best described by a non-
linear Maxwell element based on that presented by Haupt and Sedlan [19]. Primarily
this is because values at turning points do not have to be stored, the element naturally
reproduces an asymmetric shape and the element has ‘stress relaxation’. The Haupt
and Sedlan model has been significantly changed though by the addition of a ‘stiffing
97
element’ producing a model that better describes dual-sine motion and stress
relaxation. The viscoelastic description developed requires only four parameter values
that are found simply by manually changing values of a time-independent function
and visually comparing the damping loop produced with measured data. Computer
minimisation algorithms are not used. The final model developed here is a
compromise. It is satisfactory for use in vehicle models, being able to describe the
three fundamental features of carbon black filled natural rubber response, these are
its; predominantly frequency independent damping, asymmetric hysteresis loop shape
and stress relaxation. Also viscoelasticity is described by a ‘smooth’ continuous
function that is easily implemented in automatic dynamic analysis software. The
model has been implemented using ADAMS software and results show good
correlation with the measured response to stable sinusoidal motion. However, dual-
sine motion and stress relaxation are less well described.
The model could be further developed by introducing ‘strain history dependent
parameters’ such as strain-rate dependence similar to that used by Haupt and Sedlan
[19] and Haupt and Lion [20] which would improve the dual-sine and stress
relaxation simulations but this would be the subject of further research. Other possible
areas for further work are:
• The development of a three-dimensional constitutive material model based on the
one-dimensional model developed here.
• An investigation into road wheels response when rolling over a surface.
• Further validation of the technique used here to determine the elastic force
response and a geometric multiplier by taking a line through the mean point of
small amplitude hysteresis loops.
98
• Investigate the effect of temperature on the dynamic response of CBFNR and how
the model developed here could describe this behaviour. For simplicity
temperature effects were not studied in this work; all measurements were made at
room temperature (approx. 20°C).
• Further work is required to determine whether the model developed here (for the
purpose of describing CBFNR components in simulation software that uses the
Newton-Raphson Predictor-Corrector algorithm) has wider range of applications.
Answering the following questions: Is the model suitable for use in other types of
simulation software? Does the model describe internal damping in materials other
than CBFNR?
• Another important area of study for further work is CBFNR response to transient
vibration. This has not been explored in depth in this study; only a few
measurements of the rubber component’s response to a stepped displacement
where made. This is an area where further work is required to developed the
model and understand the materials behaviour.
• The CBFNR component models developed here should be applied in a full vehicle
simulation and the results assessed by comparison with measured data to
determine whether the use of these models improves the accuracy of the full
vehicle simulation.
99
Chapter 9
The Warrior APC rotary damper
9.0 Introduction
The objective here is to develop a model of the Warrior Armour Personnel Carrier
(APC) suspension rotary damper for use in a full vehicle simulation. The model will
be implemented in multi-body simulation software such as MSC.ADAMSTM that
computes response by the implicit Newton-Raphson, Predictor-Corrector method. An
important feature for robust and trouble free operation in this type of software is that
the descriptive function produces smooth and continuous; force, displacement and
velocity responses. The damper model is one component in the complex multi-body
mechanical system and it is important that it functions well.
The Warrior’s rotary damper is designed and manufactured by Horstman Defence
Systems Limited and has been proven on test rigs and in the field to fulfil all
performance and endurance requirements. The damper has remained unchanged
throughout the Warrior’s production history from 1979 to the present day. In general
the purpose of a suspension damper is to dissipate energy imparted to the road wheels
by undulating road surfaces, vehicle acceleration and turning. But for the Warrior
APC the primary purpose is to minimise the vehicle’s pitching motion. Tracked
vehicles are particularly susceptible to pitching motion because of their high pitching
inertia and relatively high suspension compliance. Pitch mode natural frequencies are
typically very low (circa 1.0Hz) and are a main source of ride discomfort, severely
reducing the vehicles off-road performance if not damped [21].
The Warrior has twelve road wheels (six on either side of the vehicle) each mounted
on a 400mm trailing wheel arm. Transverse horizontal torsion bars allow the wheel
100
arm to rotate in response changing ground profiles. Rotary dampers act in parallel
with torsion bars at six of the twelve wheel stations. Numbering pairs of wheel
stations from 1 to 6 along the vehicle from the front to rear (Fig 9.0-1), dampers are
installed at stations 1, 2 and 6. The three central stations (3, 4 and 5) are undamped. It
is damping at the stations furthest from the centre of gravity that offer most resistance
to pitching motion.
The 3D solid model of a Warrior’s APC running gear (Fig 9.0-1) shows the drive
sprocket at the front of the vehicle, six pairs of road wheels, six pairs of torsion bars,
idler wheels, support rollers and the track.
1
2
3
4
5
6
Fig. 9.0-1: Warrior Armoured Personnel Carrier running gear (Horstman Defence
Systems Ltd). Wheel stations are numbered 1 to 6 from front to rear
9.1 Design of the Warrior APC Rotary damper
In principle the Warrior’s rotary damper has the simplest possible design. It is an un-
pressurized passive device with a single simple orifice determining the resistance to
flow between chambers in both directions. Pressure relief valves restrict damping
force to maximum compression and rebound values.
101
For its purpose, the damper requires a maximum rotation angle of approximately 90°
(±45°). Therefore, to optimise space, the design has two identical chambers 180°
apart. The chambers have identical, vane pistons, orifice and pressure relief valves
(see Figure 9.1-1).
Pressure Orifice
relief valve restrictor
A B
Stator
B A
Rotor
Tip seals
Fig. 9.1-1: Section through rotary damper
Passageways connect the chambers labelled ‘A’ and the chambers labelled ‘B’ so that
oil pressure is balanced. The damper’s rotor is connected directly to the road wheel
arm and torsion bar so that it rotates at the same angular velocity.
Fig. 9.1-2: Sectioned view of the rotary damper
102
Damper resistance is caused by the restriction to oil flow through both orifices and
seals. ‘The damping rate is determined by the rate at which fluid is allowed to leak
from the pressurised chambers across the rotor vanes, via seals orifices and
valves…perfect sealing is not of paramount importance’…[21].
Although the principle behind the damper is simple its design in detail and its
construction are not. The sectioned 3D image (Fig 9.1-2) illustrates this. The damper
incorporates wheel arm bearing and is designed to withstand high torsional and radial
loads. Rotating components are mounted in a cast-steel housing, which supports the
bearings outer race and the dampers stator.
A complex labyrinth of channels is necessary to connect the chambers, to fill the
damper with oil and purge it of entrapped air. Priming is a lengthy procedure
requiring, specialist tools, hydraulic pump and heavy lifting equipment that can rotate
the damper into various orientations.
Because damping force is generated by oil flowing through a single simple orifice the
damping rate is the same in both bounce and rebound up to where the pressure relief
valves operate. This is unusual in damper design. It is more common for damping rate
in compression to be higher than the rate in rebound.
Figure 9.1-3 shows the envelope to which the damper has been designed. The upper
and lower bounds allow for nonlinearities such as, variation in valve coefficient,
transition from laminar to turbulent flow, flow past seals, mechanical backlash,
friction, viscosity variation and expansion due to temperature change.
In response to exceptionally rapid motion in bounce the pressure relief valves acts to
restrict maximum force transmitted to the hull. In rebound following a bump when the
only restoring force is that of the torsion bar the relief valve allows the road wheel to
return quickly to its normal position.
103
20000
Torque (Nm)
Compression
0
Rebound
-20000
-8 0 8
Angular velocity (rad/sec)
Fig. 9.1-3: Design specification showing the allowable range of damper torque
An additional design requirement for the damper is that low displacement amplitudes
have low resistance. This is so that the transmitablity of high frequencies to the
Warrior’s hull is low. As explained here in an excerpt taken from Holman [21].
‘The main source of ride discomfort is vehicle pitching. This results from excitation of
the pitch mode natural frequency of the vehicle. This is typically very low (c 1 Hz).
Oscillations of this type must be adequately damped. However, it is undesirable that a
damper should respond positively to the higher frequency, small amplitude oscillation
induced by passage over cobblestone surfaces (or, in the case of tracked vehicles,
track links). Response to these would result in unwanted energy dissipation’ [21].
Holman goes on to state that this requirement has been satisfied: ‘Frequency response
testing has shown that, although the damper responds very effectively to frequencies
normally associated with pitch oscillation, energy dissipation at high frequencies
(30Hz) is very low’ [21].
104
Data from test conducted by Horstman Defence Systems Limited show that the
damper satisfies the requirements. Torque lies within the limits specified in Figure
9.1-3 and power dissipation falls at low amplitude as required.
The results produced by Horstman Defense Systems Ltd however are not ideal for the
development of a damper model for vehicle simulation. The Horstman characteristic
torque verses angular velocity graph is produced by constant velocity excitation
(triangular waveform) producing an individual point on the graph for each
measurement (Fig. 9.1-4) rather then the continuous plot produced in response to
sinusoidal excitation, which would show nonlinearity and hysteresis in detail.
Fig. 9.1-4 Characteristic graph of torque verses angular velocity, produced by

Horstman Defense Systems Ltd
105
To investigate the nonlinearities and hysteresis for the development of a damper
model a test rig was built, measurements of torque versus angular velocity in response
to sinusoidal excitation have been undertaken and these are presented in Chapter 12.
However because the test rig that was built has limited range, the Horstman data (Fig
9.1-4) is used to develop the model at high velocities.
106
Chapter 10
Literature review of automotive suspension damper models
10.0 Introduction
Many papers have been published on the topic of automotive damper modelling [22-
36] and although each may describe a different damper design (monotube, dual tube
or gas pressurized) all agree that damper response is significantly non-linear.
Physical models attributed non-linearity primarily to, turbulent flow, gas
compressibility and friction. Although other nonlinearities that may also be described
are: pressure relief (blow-off), temperature/viscosity variation, cavitation, aeration
and mechanical backlash.
Here in Chapter 10 four descriptive techniques for vehicle damper models are
discussed. These are: equivalent linearization, restoring force method, physical
models and models which use discrete spring, damper and friction elements.
10.1 Linear equivalent models
Linearization is effectively an averaging technique where parameters for a linear
single degree of freedom mass-spring-damper system are determined from the true
non-linear damper response. This type of model is described by the following linear
equation.
meq &x& + ceq x& + k eq x = F Equation 10.1-1
Where, meq is the equivalent mass of reciprocating parts, ceq is the equivalent damping
coefficient, keq is equivalent spring coefficient, F is the reaction force, x, x& and &x& are
displacement, velocity and acceleration, respectively. The coefficients ceq and keq
107
maybe derived by harmonic excitation or by a broadband excitation that simulates the
motion the damper will experiences as a vehicle component. But whichever type of
excitation is used when testing the damper, the experimental method by which the
coefficients are determined is the same (requiring measurements of
F (t ), x(t ) and x& (t ) ). However due to the dampers non-linearity, the coefficients in
each case are likely to have different values.
The theory of ‘linearization of nonlinear systems’ is covered in detail by Worden and
Tomlinson [50]; who in turn refer to the work of Hagegorn and Wallaschek with
regard to determining linearised coefficients by experimental methods. Hagedorn and
Wallaschek [24] derive linearised equations for an automotive damper that equate the
coefficients ceq and keq to measured, force F (t ) , displacement x(t ) and velocity x& (t ) .
These equations can be interpreted as Equations 10.1-2 and 10.1-3 below, where the
‘bar’ notation f (t ) , has been used to indicate ‘mean value’ rather then ‘expected
value’ E [ f (t )] as in Hagegorn and Waklaschek.
Linerarized damping coefficient c eq =

(F (t ) − F (t ) )x& (t ) Equation 10.1-2
x& 2 (t )
‘Equation 10.1-2 describes a power balance: In the mean all power provided by
external force (F) is dissipated in the damper of the linearized system’ [24].
F (t ) x(t ) + m x& (t ) + F (t ) x(t )

Linearized stiffness coefficient k eq = 2
x 2 (t ) − x(t )
Equation 10.1-3
108
‘Equation 10.1-3 can be interpreted as an energy balance stating that in the mean
kinetic and potential energy of the linearized system are equal to each other’ [24].
Hagedorn and Wallaschek [24] compare the equivalent linearized harmonic and
broadband coefficients for a monotube automotive damper and recognise that the
result is dependant upon the test signal, suggesting that motion of the damper while
on the vehicle should be recorded and used to determine these coefficients. But
Hagedorn and Wallaschek suggest that a linearized model is most useful in
comparative tests where the effect of design changes or ageing are explored.
Assessing linear and bilinear models, Hall and Gill [22] compare the ride performance
predicted by a physical model that described both non-linearity and hysteresis with a
model that excluded hysteresis and a linearized model. The conclusion was that
models that do not describe hysteresis or which linearize the data ‘are inappropriate
and lead to over-optimistic estimates of ride performance’.
10.2 Restoring force maps
A restoring force map is a three dimensional plot with force response on the vertical
axes, displacement and velocity on the horizontal axes. Values for the map are most
often determined by damper tests at constant frequency of varying amplitude. The
map maybe described by either a grid of flat surfaces connecting measured points or a
continuous smooth surface profile produced by a three-dimensional curve fitting
technique. When used to simulate damper response data is retrieved from the stored
map for the given displacement and velocity conditions.
The restoring force map method has limited application because of damper non-
linearities, which produce a frequency dependent response.
Examples of restoring force maps are given by, C.Surace. et. al. [26] and Duym [33].
109
Duym states that restoring force maps are unsuccessful for broadband excitation but
that they are useful in modelling the response to harmonic motion. C.Surface. et. al.
simply use the restoring force map method to compare measured response with the
response produce by a physical model. The map is not used for damper simulation.
10.3 Parametric or physical models
The most common type of damper model is the physical or parametric model. This
method describes damper response by equating formulas for physical phenomena and
the kinematics of the mechanism. For example: laminar flow through an orifice is
proportional to pressure drop, turbulent flow approximately proportional to pressure
drop squared. Flows are equated to volumetric change, displacement and compliance.
Gas laws are applied where appropriate and friction is described by a suitable
function.
This modelling method produces a set of non-linear differential equations that are
suited to Newton-Raphson Predictor Corrector numerical simulation, however a
drawback is that precise parameter identification for the many values requires
repeated simulation and automated minimisation algorithm techniques. A number of
papers, which use physical parametric damper models, are: [22, 26, 27, 30, 31, 34, 35
and 36]. These models are all very similar in principle, however they differ in some
details. Summaries of their characteristics are listed in Table 10.3-1. But this table
presents only an overview of the physical phenomena described in each model; the
detailed description of any component may differ in each case. For instance, turbulent
flow maybe described by ∆ P ∝ V& 2 or ∆ P ∝ V& 1.75 ; friction may be described as
Coulombic, include stiction or be a function of displacement and/or velocity.
110
Hall Surace Kwang Purdy Yung Duym Duym Duym
Author/s & Gill et. al. -jin &
& [22] [26] [27] [30] Cole [36] [34] [35]
Reference [31]
(1986) (1991) (1997) (2000) (2002) (1997) (1998) (2000)
Mono
Type of
Dual- Mono- Mono- Dual- Mono- Dual- Dual- &
automotive
tube tube tube tube tube tube tube Dual-
damper
tube
Friction √ √ √ √ √ √ √
Oil and
chamber √ √ √ √ √ √ √ √
compliance
Adiabatic
gas √ √ √ √ √ √
compression
Cavitation /
Vapour √ √ √
pressure
Gas
solubility - √
Henry’s law
Laminar
√
flow
Turbulent
√ √ √ √ √ √ √ √
flow
Pressure
relief √ √ √ √
(Blow-off)
Thermal
√ √
effects
Table 10.3-1: A summary of the various physical phenomena that are described in a
selection of parametric models
111
10.4 Spring and dashpot models
The parametric models described above in Section 10.3 can also be represented as a
nonlinear spring in series with a nonlinear dashpot, plus a frictional element.
Turbulent flow through an orifice is then represented by the nonlinear dashpot and the
nonlinear spring represents, chamber compliance, compression oil and compression of
entrapped gas. This approach suits the implementation of a physical model in
software packages such as MSC.ADAMS where discrete components are assembled
to represent the mechanical system. Figure 10.4-1 illustrates this approach.
F
X1
Fs = f ( x1 − x 2 )
X2
Where Fs = Spring force
Fd = f ( x& 2 ) and Fd = Dashpot force
Fig. 10.4-1: A physical damper model represented by non-linear dashpot and non-
linear spring in series.
Karadyi and Masada (1986) [23] use a linear spring and dashpot and included
backlash in an early attempt to produce a computer simulation of an automotive
damper. Duym [33] implements a model that has a cubic spring and tri-linear damper
but reports that accuracy was lower when compared to other modelling methods such
as a physical model or restoring force map.
112
Chapter 11
Rotary damper test rig design and experimental procedure
11.0 Test rig design and instrumentation
A test rig was built which could rotate the damper through ±0.4 radians at a maximum
angular velocity of 4 rads/sec. The limiting factors being, maximum displacement and
velocity of the hydraulic ram that provided the motive force. Driving motion was
transmitted from the hydraulic ram to the rotary damper by a connecting rod and the
apparatus mounted on a test bed. A schematic drawing of the arrangement is
presented in Figure 11.0-1.
Rotary damper
Load cell Hydraulic ram
Connecting rod
Fig. 11.0-1: Schematic drawing of the rotary damper test rig
Although the test rig arrangement allows a maximum displacement of ±0.4 radians
and angular velocity of 4 rad/sec, due to flexibility of the test bed the limits were
restricted to a maximum displacement of ±0.2 rads and maximum angular velocity of
1.0 rad/sec.
All tests where conducted by displacement controlled sinusoidal motion of the
hydraulic ram. The hydraulic ram’s position was measured by an internal Linear
113
Variable Displacement Transducer (LVDT) and the dampers angular displacement by
a rotary potentiometer at its axis. A strain gauge load cell mounted on the hydraulic
ram measured the force applied to the connecting rod. An accelerometer mounted on
the hydraulic ram allowed for force correction due to the accelerating mass of the
connecting rod. The four signals (linear ram displacement, angular rotary damper
displacement, force and acceleration) were passed through a low pass filters and
stored via an A-to-D interface board in computer memory. For drawings detailing test
rig design, data acquisition and control see Appendix 7.
11.1 Data processing
11.1.1 Angular displacement measurement
A voltage proportional to angular displacement was produced by the rotary
potentiometer mounted at the dampers axis. The voltage was multiplied by a
calibration factor after storage in the computer.
11.1.2 Angular velocity measurement
To avoid differentiation of the potentiometer signal with respect to time, which would
amplify noise, it was assumed that the angular displacement of the damper was
sinusoidal. Angular displacement of the rotary damper is then described by:
θ = Θ . sin(φ ) Equation 11.1-1
where θ is the dampers angular displacement, Θ is the dampers maximum angular
displacement and φ is the angle of the drive signal (or angle of the hydraulic ram
motion).
114
The angular velocity is then simply found from:
θ& = Θ .2π . f . cos(φ ) Equation 11.1-2
The assumption that the dampers angular displacement is sinusoidal introduces a
small error due to the connecting rod mechanism because it is the linear motion of the
hydraulic ram that is displacement controlled, not the rotary motion of the damper. To
demonstrate that this error is negligible the measured hydraulic ram and rotary
damper displacements for the maximum amplitude (±0.2 rads) have been normalised
and compared in Figure 11.1.2-1. Evidently the two motions are the same to a very
small degree.
1.2
Rotary damper displacement
Hyraulic ram displacement

Normalised signal
0.0
-1.2
1 51 101 151 201 251 301 351 401
Sample number
Fig. 11.1.2-1 Comparison between normalised hydraulic ram and rotary damper
motion
115
11.1.3 Determining the torque at the damper
Torque applied to the damper is calculated by subtracting the force due to accelerating
components from the measured load cell force then correcting for the angle between
connecting rod and torque arm.
Referring to Figure 11.1.3-1: The mass of reciprocating components (load cell, pivot
assembly and connecting rod) is 12 kg. Rotating inertia of the radius arm (which links
connecting rod with damper) is 0.039 kg.m2. Inertial force due to the rotation of the
connecting rod is considered negligible because its angular displacement is small.
Torque applied to the damper is then calculated as follows:
⎡ ⎛ I .Θ 2 ⎞⎤
( )
T = ⎢ F − 12. A.ω 2 . sin(ω .t ) − ⎜ .ω . sin(ω .t ) ⎟⎥ × r × cos(θ ) × cos(φ )
⎣ ⎝ r ⎠⎦
Equation 11.1.3-1
Where, ‘T’ is torque. ‘F’ is the force measured by the load cell. ‘A’ is the amplitude of
the input linear displacement. ω = 2πf where ‘f’’ is frequency of sinusoidal input. ‘I’
is the radius arm inertia; ‘Θ’ is amplitude of damper rotation. ‘r’ is radius arm length.
‘θ’ is radius arm angle and ‘φ’ is connecting rod angle.
Inertia of
radius arm = 0.039 kg.m 2
Input displacement
A. sin(wt)
0
0
Mass of load cell and

Mass of piviot assembly = 3 kg
Connecting rod = 9 kg
Fig. 11.1.3-1: Schematic drawing of rotary damper test rig mechanism
116
Because the connection rod is long, ‘φ’ is always small and cos 0 is 1, Equation
11.1.3-1 becomes:
⎡ ⎛ I .Θ 2 ⎞⎤
( )
T = ⎢ F − 12. A.ω 2 . sin(ω .t ) − ⎜ .ω . sin(ω .t ) ⎟⎥ × r × cos(θ )
⎣ ⎝ r ⎠⎦
Equation 11.1.3-2
The characteristic plot ‘torque versus angular velocity’ and the work diagram ‘torque
versus angular displacement’ can then be produced.
11.2 Test settings
The following four test (A, B, C, & D) were carried out (Table 11.2-1). The amplitude
of sinusoidal excitation remained constant; frequency was varied.
Test A Test B Test C Test D
Hydraulic ram amplitude (mm) ± 37.0 ± 37.0 ± 37.0 ± 37.0
Rotary damper amplitude

± 0.21 ± 0.21 ± 0.21 ± 0.21
(radians)
Drive signal frequency (Hz) 0.75 0.5 0.25 0.1
Samples per cycle 400 400 400 400
Sample rate (Hz) 300 200 100 40
Low pass filter –3dB point (Hz) 100 50 25 10
Table 11.2-1: Rotary damper test settings
117
Chapter 12
Measured damper response and model development
12.0 Measured damper response
Figures 12.0-1 and 12.0-2 show the damper response to four sinusoidal displacement
measurements of the same amplitude at 0.1Hz, 0.25Hz 0.5Hz and 0.75Hz. Higher
frequency tests where not possible due to test rig structural limitations. Both Figure
12.0-1 and 12.0-2 show typical vehicle damper responses, however particular features
are unique to this rotary damper.
Figure 12.0-1, referred to as the ‘work diagram’, shows energy dissipation increasing
as frequency increases (as expected) but its asymmetric shape is evidence of non-
linearity. A similar asymmetric work diagram shape is reported by Drum et. al. [36],
who attribute this it to aeration where entrapped air in the oil chamber is compressed
and expanded.
4000
0.1Hz
0.25Hz
0.5Hz
0.75Hz
Torque (Nm)
-4000
-0.3 0.0 0.3
Angular displacement (Rads)
Fig. 12.0-1: Torque versus angular displacement (Work diagram)
118
4000
Torque (Nm)
0.1Hz
0.25Hz
0.5Hz
0.75Hz
c = 3.0kNS/m
-4000
-1.5 0.0 1.5
Fig. 12.0-2: Torque versus angular velocity (Characteristic diagram)
Figure 12.0-2, referred to as the ‘characteristic diagram’, is broadly typical of those
reported for vehicle dampers showing hysteresis due to the compression of air, oil and
compliance of the oil chamber (see Table 10.3-1). There is also a typical non-linear
relationship between force and angular velocity, attributed to the turbulent flow
relationship, ∆ P ∝ V& α , where ∆P is pressure across the orifice, V& is flow velocity
and the power ‘α’ ranges from 1.7 to 2.0 [48]. Although these featured are common to
all characteristic graphs, the degree to which the effect of each component is seen is
unique to a given damper.
As a general observation it can said that except for a slight discrepancy in negative
velocity where there is a discontinuity or ‘step’ at around 500 –1000Nm, damping
force is the same in both forward and reverse velocity as expected for this design of
damper. Also that the general slope of the torque versus angular velocity
characteristic plot is approximately 3.0kNm/rad (indicated by the diagonal line in Fig.
12.0-2), laying within the specified design requirements shown in Figure 9.1-3.
119
The measurements presented in Figures 12.0-1 and 12.0-2 allows the examination of
low velocity phenomena such as; friction, laminar to turbulent flow transition and the
compression of entrapped gas. However, due to the test rigs structural limitations
measurements presented here are taken at a relatively low torque (up to 4kNm). The
designed pressure relief (blow-off) torque in compression is approximately 12kNm
and in rebound 6kNm (see Fig. 9.1-3), so evidence of the relief valve beginning to
open is not seen. The characteristics of the pressure relief value are therefore taken
from Horstman Defence Systems Limited test data (Fig. 9.1-4).
12.1 Friction and laminar flow
Non-linearity due to friction and the laminar flow through orifice and passages is seen
in the low frequency measurement (0.1Hz).
400
Torque (Nm)
0.1Hz
1kNms/rad
-400
-0.3 0.0 0.3
Fig. 12.1-1: Torque versus angular velocity for the low frequency (0.1Hz) test
120
Cole and Yung [32] demonstrated that the performance of a damper model at high
frequencies (low amplitude) could be improved by changing the description of
friction from a Coulombic model to one base on Berg’s friction model [6]. This
illustrates that the description of friction in a model improves its accuracy. However,
the initial step at zero velocity in Figure 12.1-1 indicates that the friction force in this
damper is less then 50Nm. This is small compared to the viscous force that the rotary
damper generates, therefore for simplicity; a description of the friction force will be
omitted from the dampers model.
This low value of friction is likely to be due to the dampers ‘high quality’ bearings,
which also provide the main suspension support and are designed to withstand high
off-axis loads.
We also see in Figure 12.1-1 that at low angular velocity the force-velocity
relationship is linear. A straight line overlaying the plot shows that this relationship is
approximately 1 kNms/rad. This laminar flow relationship at low velocity could
explain the low energy dissipation at high frequency (low amplitude) reported by
Holman [21].
12.2 Laminar to turbulent flow transition
The torque-velocity graph (Fig. 12.2-1) indicates three flow regimes: a low velocity
region where flow is laminar, a transitional region and a region at high velocity where
the flow is turbulent and the relationship non-linear.
We see in Figure 12.2-1 that laminar to turbulent flow transition occur at around 0.25
rad/sec where the response is unstable and begins to rise more steeply. However,
laminar to turbulent transition is not modelled in any of the physical models listed in
table 10.3-1. Yung & Cole [31] and Duym [34, 35] use the relationship ∆ P ∝ V& 1.75 to
121
describe turbulence that is not ideal, other models describe turbulent flow simply
using the squared relationship (∆ P ∝ V& 2 ) but in all cases this relationship begins at
zero velocity.
2500
Torque (Nm)
0.1Hz
0.25Hz
0.5Hz
-2500
-0.75 -0.50 -0.25 0.00 0.25 0.50 0.75
Angular velocity (Rads/sec)
Fig. 12.2-1: Torque versus angular velocity (for frequencies up to 0.5Hz only)
It is proposed here that viscous force is modelled as laminar ( T = A.ω ) up to 0.25
rad/sec, and above 0.25 rad/sec as turbulent ( T = B.ω 1.75 + C ), where ‘T’ is torque,
‘A’, B and ‘C’ are constants and ‘ω’ is angular velocity.
By fitting a straight line (Fig. 12.1-1) the constant ‘A’ was found to be 1kNm and by
fitting the equation for turbulence to the transition point (250Nm at 0.25 rad/sec) and
the peak measured viscous force (3250Nm at 1rad/sec) The constants B and C are
found. This is shown graphically in Figure 12.2-2.
122
4000
Torque (Nm)
Laminar to turbulent
transition point
Viscous force (Fd)
-4000
-1.2 0 1.2
Fig. 12.2-2: Laminar and turbulent flow regions of the viscous force
12.3 Pressure relief valve characteristics (Blow-off)
Duym [34, 35] merges the transition between turbulent flow and opening of the
pressure relief valve using a ‘smoothing function’. Pressure relief valve blow-off is
not seen in Figure 12.0-2 because the damper test rigs cannot generate the required
torque. However, Horstman Defense Systems Limited has supplied test data showing
the response of 49 damper units to constant velocity excitations. Figure 12.3-1 shows
this Horstman data where curves have been drawn by hand through the upper and
lower limits. The dampers viscous force is taken as the mean point through this plot,
midway between the upper and lower limits. This line is merged with the measured
viscous force (Fd) response (Fig. 12.2-2) assuming laminar flow up to 0.25 rad/sec
and turbulent flow above this velocity up to where the turbulent response merges with
the Hostman data.
123
Fig. 9.2-3 Characteristic graph: Torque verses angular velocity
Fig. 12.3-1 Data supplied by Horstman Defense Systems Ltd
Equivalent data to Figure 12.3-1 for the pressure relief valve opening in rebound is
not available from Horstman Defense Systems Limited. Therefore the data for
compression is assumed to be representative and applied to rebound.
The complete force verses angular velocity viscous force showing, laminar, turbulent
and pressure relief in both compression and rebound is presented in Figure 12.3-2.
Also shown are the upper and lower design specification limits.
124
20000
Torque (Nm)
Torque verses angular

velocity response
Design specification limits
-20000
-12 0 12
Fig. 12.3-2: Rotary damper torque - angular velocity response without hysteresis
12.4 Hysteresis due to entrapped air, oil compression and chamber compliance
The characteristic graph of torque versus velocity (fig. 12.0-2) shows significant
hysteresis at 0.75Hz that could be caused by entrapped air, compression of oil or
expansion of the oil chamber. However, the shape of the hysteresis loops indicates
that it is predominantly due to the compression of air. The loop is ‘broad’ and
‘rounded’ at low velocity, becoming ‘narrow’ and ‘pointed’ at high velocity
indicating non-linear compression; not the linearity expect for oil compression and
chamber compliance. Oil compressibility and expansion of the chamber must make
some contribution to this hysteresis but these effects will not be modelled
independently a function is developed here which describes a range of compliance
from isothermal compression of air to linear elastic compression of oil and chamber,
depending on the value of its constants. Therefore these phenomena are ‘lumped’
together in the model, being described by a ‘non-physical’ function.
125
As described in Section 9.0, the Warriors rotary damper has a labyrinth of
passageways connecting various chambers making the procedure for purging air from
the system elaborate. We therefore might expect some entrapped air in the oil
chamber. A model which includes the effect of entrapped air in the oil chamber,
where Henry’s law is applied, has been developed by Duym, et. al. [36]. Henry’s law
states that, ‘The mass of gas that dissolves in a volume of liquid is directly
proportional to the pressure’ and is described by the relationship:
H .m gs
P= Equation 12.4-1
Voil
Where, ‘P’ is pressure, ‘H’ is Henry’s constant, ‘mgs’ is mass of gas dissolved in
solution and ‘Voil’ is volume of oil.
The application of Henry’s law influences the understanding of the physical process
active in the damper with the conclusion that compression and expansion of entrapped
gas should be modelled as an isothermal process. This is illustrated in the schematic
diagram, Fig. 12.4-1.
Piston motion
Fig. 12.4-1: Schematic diagram illustrating the compression and expansion of

entrapped gas
126
Air on the compressed side of the piston dissolves in the oil under pressure and come
out of solution on the low pressure side in the from of small bubbles. Duym, et. al.
[36] showed that due to oil viscosity and low buoyancy the expected velocity that
these bubbles rise due to gravity is approximately 0.001 m/s; Negligible relative to
piston velocity. Because these bubbles are small and have insufficient time to collect
and form a large volume of air, heat transfer to the oil is rapid and the process
isothermal. Therefore from the ideal gas law ( P.V = mRT ) the following equation
applies to the air bubbles either side of the piston:
P0 .V0 P1 .V1
= Equation 12.4-2
m gb 0 m gb1
Where, P0 is initial pressure, P1 current pressure, V0 initial volume, V1 current volume,
mgb0, initial mass of gas bubble and mgb1, current mass of gas bubble. It is shown in
Appendix 5 that from Equations 12.4-1 and 12.4-2 force acting on the piston can be
described by the following function:
⎡ ⎤
⎢ ⎥
⎢ 1 1 ⎥
F = C1 − Equation 12.4-3
⎢ xd x ⎥
⎢1 + C 1− d ⎥
⎣ 2 C2 ⎦
Where, F is force acting on the piston, C1 and C2 are constants and xd is change in gas
volume.
It is possible to produce an almost linear relationship by setting the value of C2 so that
C 2 >> x d . This would suit a model where the mass of entrapped air is small
127
12.5 Model implementation
The model has only two components. A non-linear viscous force described by
laminar, turbulent and blow-off regions (Fig. 12.3-2) and compression of entrapped
gas (described by Equation 12.4-3). Friction is negligible. The model is implemented
as a non-linear spring and non-linear dashpot in ADAMS software as shown below in
Figure 12.5-1
F
X1
⎡ ⎤
⎢ 1 1 ⎥
Fs = C1 ⎢ − ⎥
⎢1 + x d 1 − x d ⎥ X2
⎢ C C 2 ⎥⎦
⎣ 2
Fd = Splined response curve
Where, Fs = Spring force, Fd = Dashpot force. C1 and C2 are constants and Gas
compression, xd =X1-X2. The damper force-velocity response (Fd) is described
by the splined curve presented in Appendix 6, Figure A6-1.
Fig. 12.5-1: The rotary damper, modelled by a non-linear dashpot and non-linear
spring in series
Because the dampers torque-velocity characteristic (Fd) has three regions (laminar,
turbulent and blow-off) it is convenient to describe the response using a ‘splined’
curve. The curve is fitted to data points rather then using three functions, one for each
region. It is important for robust and trouble free implementation in Newton-Raphson
Predictor-Corrector based simulation software that the curve is smooth at the
transition between regions and this is more easily achieved using a splined curve.
128
Numerical values for the torque-velocity response are given in Appendix 6 and the
smoothed splined response presented above in Figure A6-1.
12.6 Damper rotor inertia
The model requires a value of inertia for the dampers rotating mass. To find this value
a damper was dismantled and the inertia of its rotating parts measured by means of
‘bifilar suspension’. The damper rotor’s inertia was found to be 0.118 kg.m2.
129
Chapter 13
Comparison between measured and modelled rotary damper response
13.0 Introduction
The rotary damper model is presented in Figure 12.5-1.
F
X1
⎡ ⎤
⎢ 1 1 ⎥
Fs = C1 ⎢ − ⎥
⎢1 + x d 1 − x d ⎥
⎢ C C 2 ⎥⎦ X2
⎣ 2
Fd = Splined response curve
Where, Fs = Spring force, Fd = Dashpot force. C1 and C2 are constants and Gas
compression, xd =X1-X2. The damper force-velocity response (Fd) is described
by the splined curve presented in Appendix 6, Figure A6-1.
Fig. 12.5-1: The rotary damper, modelled by a non-linear dashpot and non-linear
spring in series
The derivation of the viscous force (Fd) is described in Sections 12.1, 12.2, 12.3 and
Appendix 6. Values for the constants C1 and C2 are found by trial and error, i.e.
simulations are run repeatedly and the values adjusted manually to achieve ‘best fit’
by visual comparison. The values for C1 and C2 used for the results presented in
Figures 13.1-1 and 13.1-2 are: C1 = 0.8 x 106 Nm, C2 = 0.03 rads.
130
13.1 Measured and modelled results for the rotary damper
4000
0.1Hz
0.25Hz
0.5Hz
0.75Hz
Torque (Nm)
-4000
-0.3 0 0.3
Displacement (Rads)
Fig. 12.0-1: Measured torque versus angular displacement (Work diagram)
4000
Torque (Nm)
-4000
-0.3 0 0.3
Angular displacement (Rads)
Fig. 13.1-1: Modelled torque versus angular displacement (Work diagram)
131
4000
Torque (Nm)
0.1Hz
0.25Hz
0.5Hz
0.75Hz
-4000
-1.5 0.0 1.5
Fig. 12.0-2: Measured torque versus angular velocity (Characteristic diagram)
4000
Torque (Nm)
-4000
-1.5 0 1.5
Angular velocity (Rads/sec)
Fig. 13.1-2: Modelled torque versus angular velocity (Characteristic diagram)
132
13.2 Predicted response at high velocity
It is interesting to predict the dampers response to high frequency sinusoidal
displacements that are beyond the limits of the test rig to measure. Also, the rapid
changes in force and direction will test the models computational robustness for use in
full vehicle simulations. The results are presented below in Figures 13.2-1 and 13.2-2.
15000
1Hz
2Hz
5Hz
10Hz
Torque (Nm)
-15000
-0.3 0 0.3
Angular displacement (rads)
Fig. 13.2-1: Modelled torque versus angular displacement in response to high

frequency sinusoidal motion
Figure 13.2-1 shows that the predicted response to high frequency sinusoidal motion
is a rapid increase and decrease in torque to the limiting pressure relief valve settings.
This would probably be found to be incorrect if the damper where tested at these
high-frequency settings because flow through the pressure relief valve would become
non-linear (turbulent) and damping force would increase. However, most importantly
the simulation runs ‘trouble free’ without computational failure.
133
15000
Torque (Nm)
1Hz
2Hz
5Hz
10Hz
-15000
-15 0 15
Fig. 13.2-2: Modelled torque versus angular velocity in response to sinusoidal

motion
Figure 13.2-2 shows the predicted response to high frequency sinusoidal motion
generating a high degree of hysteresis due to air compression.
134
Chapter 14
Rotary damper: Conclusion and Further work
14.0 Conclusion and further work
The modelled response presented above in Figure 13.1-1 and 13.1-2 shows that the
main damper characteristics (non-linear force-velocity response and non-linear
compliance) are described. The same trends are seen in both the modelled and
measured data but in detail there are some differences between the plots. Possible
causes of these differences are as follows:
1. For simplicity laminar to turbulent transition has been modelled as instantaneous
and occurring at the same value when velocity is increasing and when decreasing.
This is not ‘realistic’. It is known that the transition from laminar to turbulent flow
is not instantaneous and occurs at a higher velocity when moving from a laminar
flow regime to a turbulent flow regime then in the reverse direction [37, 38] but
modelling this behaviour would be complex and would introduce many more
parameters for little improvement in the models accuracy.
2. Torque due to friction is less then 50Nm (see Section 12.1) and for simplicity has
not been included in the model. If this effect where modelled correlation between
measured and modelled response would improve.
3. It is possible that the restriction to flow presented by the pressure relief valve and
the seals, is not constant with pressure. The ‘step’ we see in the measured
response in one direction only between 500Nm and 1000Nm may be caused by
135
reverse flow through pressure relief valves and/or seals, which has a step change
as chamber pressure increases.
In conclusion the model developed here represents the measured response to a close
degree using only a simple splined curve and an isothermal description of entrapped
air. An important objective was to produce a simple and robust model that could
represent the rotary damper in a full vehicle simulation and includes nonlinearities,
which reproduce the low damping at high frequency (low amplitude) reported by
Holman [21]. These objectives have been achieved.
Further work
Areas for further work that would improve the damper model developed here are:
1. Strengthening the test rig for measurements at high force. It could then be
determine whether the predicted response presented in Figs.13.2-1 and 13.2-2 is
accurate.
2. It is known that damper model accuracy at high frequency and low amplitude can
depend upon the description of friction [31, 32]. Further work in this area may be
required for use in vehicle vibration models that operate up to 30Hz.
3. Investigate the effect of temperature on the dampers response and how the model
developed here could describe this behaviour. For simplicity temperature effects
were not studied in this work; all measurements were made at room temperature
(approx. 20°C).
4. The damper model should be applied in a full vehicle simulation and the results
assessed by comparison with measured data.
136
137
Chapter 15
Conclusion and further work
15.0 Overview
The objective set out at the beginning of this report was to develop models for
Warrior Armoured Personnel Carrier running gear components for use in multibody
dynamic simulations of the full vehicle. This objective has been achieved for three
components. In Chapters 3-8 models for two Carbon Black Filled Natural Rubber
(CBFNR) track components were developed. These were the Track Link Bush and the
Road Wheel Tyre. In Chapters 9-14 a model for the Warrior’s suspension rotary
damper was developed. These models are shown to be computationally robust and
compatible with software that uses the Newton-Raphson Predictor Corrector method.
For simplicity the models have been developed with a minimum number of
parameters and it is shown that their response is adequate for vehicle simulations in
the first instance where the development of a full vehicle model is at an early stage.
The models have been implemented using ADAMS software and the results show
good correlation with measured response but they are phenomenological in nature.
That is: they reproduce the response that has been measured. They are not guaranteed
to describe the response to force and displacement inputs at amplitudes and
frequencies that have not been measured.
15.1 Rubber component models
The model developed for CBFNR in this work describes dynamic response at the
component level. There has been no attempt to describe the materials microstructure,
its micro-mechanical behaviour or develop constitutive equations. The measured
137
response is simply reproduced by combining three functions; an elastic force
description, a viscoelastic force description and a geometric multiplier.
A novel method has been developed for measuring the CBFNR components elastic
response and determining a geometric multiplier for its viscoelastic response where
the component is exercised by small amplitude sinusoidal motion at varying preloads.
The assumption being; that by applying a preload, then exercising the component first
at large amplitude, then steadily reducing to a small amplitude; the hysteretic response
becomes steady about its mean point and that this point lies on the elastic force line.
The elastic force is then taken as a polynomial fit to successive measurements at
varying preload and by subtracting the elastic force from the total response a
viscoelastic multiplying function is determined from the change in amplitude of
hysteresis loops at varying preloads.
The models viscoelastic description is based on a nonlinear Maxwell element used by
Haupt and Sedlan [19]. This element is used primarily because values of force and
displacement at turning points do not need to be stored (as in some other methods [6,
7, 8]) and is therefore suitable for use in dynamic simulation software that uses the
Newton-Raphson Predictor Corrector method. But the element also naturally
reproduces the fundamental features of CBFNR. These are an asymmetric hysteresis
loop shape, a predominately frequency independent response and stress relaxation.
The model developed here for CBFNR components is a compromise though; it does
not describe ‘strain history dependent viscosity’, which Haupt and Sedlan [19] and
Haupt and Lion [20] include in their models. A ‘nested’ stiffening element has been
added to better describe the materials response to dual-sine motion and stress
relaxation but an attempt to describe strain history dependent viscosity has not been
made for the sake of simplicity. The final CBFNR model has also been rationalised so
138
that many of the coefficient values and time constants are the same in both the Track
Link Bush and Road Wheel Tyre models. This has reduced the number of parameter
values required in each case to just four.
15.2 Suspension damper model
The Warrior APC rotary suspension damper model developed in this work shows
good correlation with the measured response. The dampers main characteristics are a
nonlinear torque-velocity response and nonlinear compliance that is predominately
due to entrapped air in the oil chamber.
The viscous force developed by the flow of oil through orifices and past seals is
described by a continuous torque-velocity curve that represents regions of, laminar
flow, turbulent flow and pressure relief. Compliance due to entrapped air in the oil
chamber is described by applying Henry’s Law, the Ideal Gas Law and assuming
isothermal compression and expansion. Coefficients for this description have been
‘lumped’ together where possible to produce a simple non-parametric function that
has only two unknown constants and is therefore easily matched to measured data.
The damper model developed here is simple and computationally robust fulfilling its
requirements as a component in full vehicle simulations.
15.3 Further work
Areas for further work on CBFNR component models are as follows:
1. Validate the novel measuring technique developed in this work, which determines
the elastic force component, the viscoelastic force component and a geometric
multiplier. Where the elastic force component is taken as a line drawn through the
centre of small amplitude hysteresis loops at varying preloads.
139
2. Introduce ‘strain history dependent parameters’ such as strain-rate dependence
similar to that used by Haupt and Sedlan [19] and Haupt and Lion [20].
3. Develop a three dimensional constitutive material model based on the elastic,
viscoelastic and geometric descriptions presented in this work.
4. Determine whether a rolling Road Wheel model is required and if so develop one.
5. Investigate the effect of temperature on the dynamic response of CBFNR and how
the model developed here could describe this behaviour. For simplicity
temperature effects were not studied in this work, all measurements were made at
room temperature (approx. 20°C).
6. Further work is required to determine whether the model developed here for
describing CBFNR components in simulation software that uses the Newton-
Raphson Predictor-Corrector algorithm has wider applications. Answering such
questions as: Is the model suitable for use in other types of simulation software?
And, does the model describe the internal damping of other materials?
7. An important area of study for further work is the CBFNR response to transient
vibration. This has not been explored in depth in this study; only a few
measurements of the rubber component’s response to a stepped displacement
where made. This is an area where further work is required to developed the
model and understand the materials behaviour.
140
8. The CBFNR component models developed here should be applied in a full vehicle
simulation and the results assessed by comparison with measured data to
determine whether the use of these models improves the accuracy of the full
vehicle simulation.
Areas for further work on the Warrior suspension rotary damper are as follows:
1. The test rig should be strengthened so that measurements can be made at higher
frequency and higher amplitude to further validate the damper model.
2. Friction is not described in the model because it is considered negligible but this is
a possible area for further work if in the future the transmission of high-frequency
low-amplitude force from ground to hull via the damper is considered significant
for full vehicle simulations of the full Warrior APC. (see papers by Yung and
Cole [31,32]).
3. Investigate the effect of temperature on the dampers response and how the model
developed here could describe this behaviour. For simplicity temperature effects
were not studied in this work, all measurements were made at room temperature
(approx. 20°C).
4. As for the rubber model; the damper model should be applied in a full vehicle
simulation and the results assessed by comparison with measured data.
141
References
_________________________
[1] Robertson, B. ‘Vibration of Tank Tracks’ PhD Thesis, University of

Newcastle upon Tyne, 1980
[2] Boast, D. and Fellows, S., Hale “Effects of temperature, frequency and
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145
Appendix 1: Time independent force-displacement relationship for the Haupt
and Sedlan viscoelastic element
F
F xA
k
xB
Fig. A1-1 The viscoelastic Sedlan and Haupt element
The Sedlan and Haupt viscoelastic element [19] is a modified Maxwell element where
the dashpot viscosity coefficient ‘η’ is a function of xA as follows:
c
η=
x& A + ξ (A1.1)
Where; ‘F’ is force applied to the viscoelastic element, ‘c’ is maximum possible
damping force, ‘ξ’ is a constant, xA is displacement across the viscoelastic element
(i.e. relative to ground) and xB is displacement across the dashpot. So that:
cx& B
F=
x& A + ξ (A1.2)
F = kxA − kxB (A1.3)
1
dF
And = kx& A − kx&B (A1.4)
dt
1 dF
Rearranging (A1.4) x&B = x& A − (A1.5)
k dt
Substituting (A1.5) into (A1.2)
⎛ c.x& A ⎞ ⎛ c ⎞⎛ 1 ⎞ dF
F = ⎜⎜ ⎟ − ⎜ ⎟⎜ ⎟
⎟ ⎝ k ⎠⎜ x& + ξ ⎟ dt
x
&
⎝ A + ξ ⎠ ⎝ A ⎠
(A1.6)
Dividing the numerator and denominator of the right hand side by x& A :
⎛ ⎞ ⎛ ⎞
⎜ ⎟ ⎜ ⎟
F =⎜
c ⎟ − ⎛⎜ c ⎞⎟⎜ 1 ⎟ dF
⎜ ξ ⎟ ⎝ k ⎠⎜ ξ ⎟ dx A
⎜ sgn ( x& A ) +
(A1.7)
⎟ ⎜ sgn( x& A ) + ⎟
⎝ x& A ⎠ ⎝ x& A ⎠
Notice that the differential is now expressed in terms of dxA not dt. Assuming that ‘ξ’
ξ
has a small value so that as the velocity ‘ x& A ’ increases; tends to zero. Then we
x& A
have:
c dF
F = c.sgn( x& A ) − .sgn( x& A ). (A1.8)
k dx A
Rearranging (A1.8):
F1 xA1
−1
∫ ∫
k
− .dF = . sgn( x& A ).dx A (A1.9)
c. sgn( x& A ) − F c
Fo x A0
2
Where, F0 and xA0 are force and displacement at the previous turning point
respectively; F1 and xA1 are current force and displacement respectively.
Integrating (A1.9):
x
[− ln c.sgn( x& A ) − F ] F1
F0
⎡ k .x A
=⎢
⎤ A1
. sgn( x A ) ⎥
& (A1.10)
⎣ c ⎦ xA0
Then:
⎛ k . sgn( x& A ) ⎞
F1 = C . sgn( x& A ) − (C . sgn( x& A ) − F0 ).Exp⎜ − .( x A1 − x A0 ) ⎟
⎝ c ⎠
(A1.11)
3
Appendix 2: Response of the Haupt and Sedlan viscoelastic element to a
stepped input
F
x1
t0 time
k x1
x2
t0 time
Fig. A2-1: Response to stepped displacement
The Sedlan and Haupt viscoelastic element [19] is a modified Maxwell element where
the dashpot coeffiecient ‘η’ is a function of x&1 as follows:
c
η=
x&1 + ξ (A2.1)
So that:
c.x& 2
F= = k ( x1 − x2 )
x&1 + ξ (A2.2)
Where, ‘F’ is applied force, ‘c’ is the maximum possible damping force, ‘ξ’ is a
constant, x1 is total displacement of the element and x 2 is displacement across the
dashpot. So that:
From (A2.2), when x&1 = 0 , ξ .F

x&2 = (A2.3)
c
4
dF
Also from (A2.2), = k .x&1 − k .x& 2 (A2.4)
dt
Substituting (A2.3) into (A2.4) we have:
dF ξ .F
= k .x&1 − k .
dt c (A2.5)
For the stepped input at, t > t0 , x&1 = 0 . Therefore:
1 dF ξ.
− . = F (A2.6)
k dt c
F1 t1
ξ.k.
∫ ∫
1 (A2.7)
.dF = − .dt
F c
F0 t0
Therefore the response to a stepped input is an exponential function dependent upon,
ξ, k, and c, as follows:
⎡ ξ .k .t ⎤
F1 = F0 .Exp ⎢ −
⎣ c ⎥⎦ (A2.8)
Where, F0 is force at t0 and F1 is force at time ‘t’.
5
Appendix 3: Test rig frequency response for rubber component measurement
The ‘dynamic compliance frequency response’ for each rubber component test rig
was determined before time domain measurements were taken and the lowest test rig
resonant frequency determined. The track running gear component time domain
measurements where then taken less then 50% of this value to avoid the effect of test
rig resonance.
Dynamic compliance is also known as, receptance, admittance or dynamic flexibility
[49]; it is the inverse of ‘dynamic stiffness’ and defined as:
X (ω )
H (ω ) = (A3.1)
F (ω )
Where, H(ω) is dynamic compliance, X(ω) is complex displacement and F(ω)
complex force. Dynamic compliance and phase angle are plotted against frequency in
Figures, A3-1b, A3-2b and A3-3b. These response plots have been produced by
random excitation. The frequency response is then found as follows:
S dx (ω )
H (ω ) = (A3.2)
S df (ω )
Where, Sdx(ω) is ‘cross spectral density’ (CSD) of the random drive signal and
displacement, and Sdf(ω) is CSD of the random drive signal and force and H(ω) the
frequency response function (FRF).
CSD is the Fourier transforms of the cross correlation (or product) in the time domain
of two signals, averaged for many sections (or lengths) of data. Details of this method
can be found in Ewins [49], Worden and Tomlinson [50] and Cartwright [51].
Essentially, the random drive signal is used as a ‘reference’ and by averaging a
6
number of frequency response plots (more then 100), the effect of noise and spurious
signals is reduced. The random drive signal component is cancelled in the division of
Equation A3.2 and the plot of dynamic compliance and phase angle determined in the
frequency domain. Software supplied by ‘Prosig Limited’ was used to record and
process the test data. In this software, the algorithm for determining Cross Spectral
Density is pre-programmed and is simply applied to the time domain measurements.
The broadband random excitation method used here has the advantage that it quickly
produces an FRF over a wide frequency range but the method has limitations
regarding the analysis of nonlinear systems. These limitations are discussed in detail
both by Ewins [49], and Worden and Tomlinson [50]. However for the purpose of
identifying the test rigs resonant frequency the method is adequate.
The graphs (A3-1b, A3-2b and A3-3b) show large spikes at zero frequency, which
should be ignored as they are due to the DC components of the signal. But we also see
that compliance below the first resonant frequency tends to increase as zero hertz is
approached (Fig A3-2b) and does not stay level as would be expected for a linear
system. This is likely to be due to the rubbers amplitude dependant stiffness, as
discussed in Section 3.3, which reduces as amplitude increases. The ‘random drive
signal’ results in higher amplitude displacements across the rubber component at low
frequency then at high frequency due to the acceleration of test rig masses and so
lower frequencies show higher compliance.
7
Fig. A3-1a: Road wheel tyre test rig
2.0E-07
Spike at low frequency cause

Dynamic compliance (m/N)
1.5E-07 by a DC component in the

measured data component
1.0E-07
5.0E-08
0.0E+00
0 100 200 300 400 500
Frequency (Hz)
90
Phase (Degrees)
60
30
-30
0 100 200 300 400 500
Frequency (Hz)
Fig. A3-1b: Road wheel tyre test rig FRF
The tyre test rig shows the first significant resonance occurring at approximately
40Hz. Therefore measurements of the road wheel response in the time domain will
not be taken at frequencies above 20Hz .
8
Fig. A3-2a: Track bush radial force test rig
1.0E-07
8.0E-08 Rising dynamic

compliance at low
6.0E-08 frequency, indicating
rubber bush non-
4.0E-08 linearity.
2.0E-08
0.0E+00
0 100 200 300 400 500
Frequency (Hz)
180
Phase (Degrees)
120
60
0
-60
0 100 200 300 400 500
Frequency (Hz)
Fig. A3-2b: Track bush radial force test rig FRF
The track bush radial force test rig does not show significant resonant effects below
150Hz.
9
Fig. A3-3a: Track bush torsional response test rig
2.0E-04
1.5E-04
1.0E-04
5.0E-05
0.0E+00
0 25 50 75 100
Frequency (Hz)
270
Phase (Degrees)
180
90
0
0 25 50 75 100
Frequency (Hz)
Fig. A3-3b: Track bush torsional response test rig FRF
The track bush torsional force test rig shows significant resonance at approximately
12Hz.
10
Appendix 4a: The ‘Four viscoelastic element’ model
Fig. A4a-1: Four viscoelastic element model
Values for the track bush torsional model
c
Nm/Degree Nm Degrees/sec τ=
k .ξ
k1 = 10 c1 = 20 ξ1 = 0.02 τ1 = 100
k2 = 20 c2 = 20 ξ2 = 20 τ2 = 0.05
k3 = 3 c3 = 40 ξ3 = 13.3 τ3 = 1.0
k4 = 40 c4 = 40 ξ4 = 20 τ4 = 0.05
Elastic force: Fe = 12.4 θ + 130.4 Nm/Degree Equation 5.3.1-1
Geometric multiplier: f ( x0 ) = 0.033 x0 − 10 + 1 Equation 5.3.2-1
11
Appendix 4b: The final ‘three viscoelastic-element’ model
Fig. A4b-1: Three viscoelastic element model
Values for the road wheel tyre model
c
N/m N m/sec τ=
k .ξ
k1 = 1500 c1 = 1000 ξ1 = 0.0067 τ1 = 100
k2 = 1500 c2 = 1000 ξ2 = 6.67 τ2 = 0.1
k3 = 150 c3 = 500 ξ3 = 3.33 τ3 = 1.0
Note: The four variable parameters (k1, k3, c1 and c3) are highlighted in bold.
Elastic force: Fe = 1.82 × 10 11.x 3 - 2.14 × 10 8 .x 2 + 2.17 × 10 6 .x N/m
Equation 5.3.1-3
Geometric multiplier: f (x0 ) = 543.x0 + 1 Equation 5.3.2-2
12
Values for the track bush torsional model
c
N/m N m/sec τ=
k .ξ
k1 = 10 c1 = 20 ξ1 = 0.02 τ1 = 100
k2 = 10 c2 = 20 ξ2 = 20 τ2 = 0.1
k3 = 3 c3 = 40 ξ3 = 13.3 τ3 = 1.0
Elastic force: Fe = 12.4 θ + 130.4 Nm/Degree Equation 5.3.1-1
Geometric multiplier: f ( x0 ) = 0.033 x0 − 10 + 1 Equation 5.3.2-1
Values for the track bush radial model.
c
N/m N m/sec τ=
k .ξ
k1 = 60,000 c1 = 3,800 ξ1 = 0.00063 τ1 = 100
k2 = 60,000 c2 = 3,800 ξ2 = 0.63 τ2 = 0.1
k3 = 17,000 c3 = 100,000 ξ3 = 5.9 τ3 = 1.0
Elastic force: Fe = 81.8 × 10 6 .x N/m Equation 5.3.1-2
Geometric multiplier: f ( x0 ) = 1
13
Appendix 5: Compression of damper oil, entrapped air and compliance of oil
the chamber
Piston motion
Fig. A5-1: Schematic representation of the damper showing how entapped air is
compressed and expanded as oil flows from one chamber into the other
Figure A5-1 illustrates a possible physical mechanism where entrapped air is
dissolved in oil on the high pressure side of the piston and comes out of solution as
small bubbles on the low pressure side according to Henry’s law which states: ‘The
mass of gas that dissolves in a volume of liquid is directly proportional to the
pressure’. Henry’s law is described by the following relationship:
H .m gs
P= (N/m2) (A5-1)
Voil
Where, ‘P’ is pressure, ‘H’ is Henry’s constant (m2/s2 ), ‘mgs’ is mass of gas dissolved
in solution and ‘Voil’ is volume of oil.
The mass of gas in solution (mgs) and mass of gas in bubble (mgb) are related by:
m gt = m gs + m gb (A5-2)
Where mgt is the total mass of gas in the chamber.
14
Combining equation A5-1 and A5-2 we have:
P.Voil
m gb = m gt − (A5-3)
H
Since, mgt, Voil and H are all constants equation A5-3 can be rewritten as:
m gb = c1 − c 2 .P (A5-4)
Because the gas bubbles are small we can assume rapid heat transfer between air and
oil and therefore constant temperature. Applying the ideal gas law, P.V = mRT , to the
entrapped air on one side of the piston we have:
P0 .V0 P1 .V1
= (A5-5)
m gb 0 m gb1
Where, P0 is initial pressure (atmospheric), P1 instantaneous pressure, V0 initial
volume, V1 instantaneous volume, mgb0, initial mass of gas bubble and mgb1,
instantaneous mass of gas bubble.
Equation A5-5 applies up to the point where all entrapped air is dissolved in oil after
which we have compression of the oil and compliance of the chamber only.
Substituting Equation A5-4 in to Equation A5-5 we have:
P0 .V0 P1 .V1
= (A5-6)
c1 − c 2 .P0 c1 − c 2 .P1
Rearranging Equation A5-6:
c1 .Po .V0
P1 = (A5-7)
c1 .V1 − c 2 .P0 .V1 + c 2 .P0 .V0
15
Because piston and cylinder areas are constant we can substitute ‘volume of entrapped
air’ for ‘piston displacement’ and ‘chamber pressure’ for ‘force acting on the piston’
so that:
V0 → x 0 (A5-8)
V1 → x0 − x d (A5-9)
P0 → F0 (A5-10)
and P1 → F1 (A5-11)
Where, x0 represents the initial volume of entrapped gas, xd is change in gas volume,
F0 is force on piston at x0 and F1 is the dampers reaction force. The units of c1 remain
as (kg) the units for c2 become (s2/m). This substitution gives:
Fo .x0 .c1
F1 = (A5-12)
c1 .x 0 − c1 x d − c 2 .F0 .x0 + c 2 .F0 .x0 + c 2 .F0 .x0
dividing through by x0 .c1 Equation A5-12 reduces to:
Fo
F1 = (A5-13)
x c x
1 − d + 2 .F0 . d
x0 c1 x0
c2
Letting F0 = c , where c and rearranging equation A5-13 we have:
c1
Fo
F1 = (A5-14)
x
1 − d (1 + c )
x0
16
Since both F0 and x0 are constants Equation A5-14 reduces to:
C1
F1 = (A5-15)
x
1− d
C2
Where the unit for C1 are Newtons (N) and C2 meters (m).
It is worth noting the following points regarding equation A5-15.
xd
1. The following condition applies: 0 < <1
C2
2. It is possible to produce an almost linear relationship by setting the value of C2
so that C 2 >> x d . This would suit a model where the mass of entrapped air is
small and compressibility primarily due to oil bulk modulus and chamber
compliance.
3. Equation A5-15 relates piston force to displacement (xd) with only two
‘tuneable’ parameters, C1 and C2, but we have lost the physical meaning of these
constants. The model has become ‘non-physical’ or ‘non-parametric’. Henry’s
constant, initial volume of oil, initial volume of gas, initial mass of gas and initial
pressure are ‘lumped’ together because all these values are unknown constants.
Equation A5-15 relates the force exerted on the piston by gas pressure in one chamber
only. But the damper has chambers either side of the piston. Therefore the dampers
reaction force (F1) is described by the following equation (A5-16).
⎡ ⎤
⎢ 1 1 ⎥
F1 = C1 ⎢ − ⎥ (A5-16)
⎢1 + x d 1 − x d ⎥
⎢ C C 2 ⎥⎦
⎣ 2
17
Figure A5-2 illustrates how Equation A5-16 behaves, summing the force on either
side of the piston.
2.5
Right hand chamber
Sum
Force acting on pistion
Left hand chamber
0.0
-2.5
-1.5 0.0 1.5
Displacement (xd)
Fig. A5-2: Response described by Equation A5-15 for C1 =1 and C2 =2
In figure A5-2: for the purpose of demonstration, C1 and C2 have been given the
values ‘1’ and ‘2’ respectively, but in the damper model, C1 and C2 are set to match
experimental data. This was achieved by repeatedly running simulations and visually
comparing the measured and modelled characteristic force-velocity graphs.
18
Appendix 6: Torque-Angular velocity relationship for the Warrior APC rotary
damper model (excluding hysteresis)
In chapter 12, points on the dampers characteristic response plot where found which
represented three viscous flow regimes, laminar, turbulent and pressure relief (Blow-
off). These values are presented in the first and second columns of Table A6-1. The
table shows ‘smoothed’ values in the third column (highlighted by a heavy boarder)
that have been corrected manually to produce a smooth transition between the
turbulent flow region and the pressure relief valve opening.
Figure A6-1 shows this ‘smoothed’ curve implemented in ADAMS software as a
‘splined curve’ for uses in the damper model.
19
Angular Measured Smoothed
velocity response curve
(rad/sec) (Nm) (Nm)
-14.0 -8050 -8050

-13.0 -8050 -8050
-12.0 -8050 -8050
-11.0 -8050 -8050
-10.0 -7950 -7950
-9.0 -7950 -7950
Blow-off -8.0 -7800 -7800
-7.0 -7600 -7600
-6.0 -7400 -7400
-5.0 -7250 -7250
-4.0 -7000 -7000
Rebound -3.0 -6500 -6500
-2.0 -6000 -6000
-1.8 -9091 -5800
-1.6 -7398 -5550
-1.4 -5856 -5200
Turbulent flow -1.2 -4471 -4471
-1.0 -3250 -3250
-0.8 -2186 -2186
-0.6 -1306 -1306
-0.4 -622 -622
-0.2 -194 -194
-0.1 -100 -100
Laminar flow 0.0 0 0
0.1 100 100
0.2 194 194
0.4 622 622
0.6 1306 1306
0.8 2186 2186
1.0 3250 3250
Turbulent flow 1.2 4471 4471
1.4 5856 5856
1.6 7398 7200
1.8 9091 8000
2.0 10932 8500
Compression 3.0 10300 10300
4.0 11600 11600
5.0 12100 12100
6.0 12600 12600
7.0 12850 12850
Blow-off 8.0 13000 13000
9.0 13200 13200
10.0 13400 13400
11.0 13550 13550
12.0 13550 13550
13.0 13650 13650
14.0 13650 13650
Table A6-1: Numeric data for the damper torque verses angular velocity response
20
21
Appendix 7: Test rig design and instrumentation
Test rigs were built to measure the dynamic response of each rubber track
components. These were; track bush radial response, track bush torsional response
and road wheel tyre radial response. A test rig was also built to measure the rotary
damper’s response. Drawings depicting each of these test rigs are presented in
Figures, A7-2, A7-3, A7-4 and A7-5 respectively.
Figure A7-1 is a schematic drawing of the data acquisition and control system setup
for a measurement of Track Link Radial response to random excitation. This is shown
as an example since the main features of this setup remained the same in all tests.
Two types of test were conducted on each component; sinusoidal excitation and
random excitation. The instrumentation and channel allocations for each case are
listed in Table A7-1.
22
Hydraulic ram
Signal generator
Control unit
Programable amplifiers
Progammable
anti-aliassing filters
CH1 CH8
Programmable
A-D Converers and memory
COMPUTER
DATS signal processing software
Fig. A7-1: Test rig control and instrumentation set up for random drive signal
(Transducer power supplies and amplifiers have not been shown for clarity)
Data
Measurement 1 Measurement 2
Channel
1 Random drive signal Sinusoidal drive signal
2 Hydraulic ram LVDT Hydraulic ram LVDT
3 Load cell Load cell
4 Accelerometer LVDT
5 Accelerometer
6 Accelerometer
7 Accelerometer
8 Test rig base motion accelerometer
Table A7-1: Data acquisition channel assignment for both random and sinusoidal
drive signals
23
2760mm
940mm 1400mm
Hydraulic ram force
The Linear Variable Displacement Transducer

is positioned across the Track Links to
measure relative displacement
LVDT positioned across the
track links
Fig. A7-2: Test rig for the measurement of Track Bush Radial Response
24
Hydraulic ram
2,000
Hydraulic ram
1,200 2500
Fig. A7-3: Test rig for the measurement of the Track Bush Torsional Response
Figure A4-3 shows the two hydraulic rams required to measure Track Bush Torsional
response. The vertical hydraulic ram applies a constant radial load; simulating track
tension. The horizontal hydraulic ram rotates the lower link about the track bush axis.
Hydraulic ram
LVDT
Road Wheel Tyre
1,200 2500
Fig. A4-4: Test rig for the measurement of the Road Wheel Tyre Response
Figure A7-4 shows the Linear Variable Displacement Transducer positioned to

measure distance across the Tyre only. Flexing of the wheels aluminium hub or the
test rig does not effect the measurement.
25
Rotary damper
Hydraulic ram
1,200 2500
Fig. A4-5: Test rig for the measurement of the rotary damper’s Response
26

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CRANFIELD UNIVERSITY

Models for the Dynamic Simulation of Tank Track Components

Defence College of Management and Technology

MODELS FOR DYNAMIC SIMULATION OF TANK TRACK COMPONENTS

Date of original submission

I must acknowledge the support provided by Cranfield University, Engineering

model the dynamics of a prototype high-speed military tracked vehicle. Specifically

from the ground to the vehicle’s hull.

masses or as linear springs without internal damping. These present no difficulty to

viscoelastic characteristics. Stiffness is amplitude dependent and the material exhibits

a significant amount of internal damping, which is predominantly Coulombic in

angular velocity to damping torque. Hysteresis due to the compression of entrapped

from the model.

All components are modelled using MSC.ADAMSTM multibody dynamic analysis

software. The models are shown to be easily implemented and computationally

has been met.

Models for the Dynamic Simulation of Tank Track Components ------------------------b

List of tables -------------------------------------------------------------------------------------ix

List of Figures -----------------------------------------------------------------------------------x

Nomenclature for Chapters 1 to 8 ----------------------------------------------------------xvii

Nomenclature for Chapters 9 to 13--------------------------------------------------------xviii

Chapter 1: The background and objectives of this study ------------------------------1

1.0 Introduction -----------------------------------------------------------------------1

1.1 The Warrior APC---------------------------------------------------------------- 3

Chapter 2: Literature review of high-speed tracked vehicle dynamic models ----5

2.0 Introduction -----------------------------------------------------------------------6

2.1 Robertson, B.----------------------------------------------------------------------6

2.2 Ma, Perkins, Scholar and Assanis et. al.,--------------------------------------7

2.3 Ryu, Bae, Choi and Shabana----------------------------------------------------8

2.4 Slattengren ------------------------------------------------------------------------9

Chapter 3: The characteristic behaviour of Carbon Black Filled Natural rubber-

3.0 Introduction ---------------------------------------------------------------------11

3.1 Frequency and temperature dependence-------------------------------------11

3.2 Stress relaxation (Viscous flow)----------------------------------------------15

Chapter 4: Literature review of models developed for Carbon Black Filled

4.0 Introduction ---------------------------------------------------------------------18

4.1 Descriptions for the Elastic stress component ------------------------------19

4.2 Descriptions for the viscous stress component------------------------------24

4.3 Summary ----------------------------------------------------------------------- 38

5.1 Warrior APC track rubber components--------------------------------------42

5.2 Test rigs design and experimental procedure -------------------------------44

5.3 Measurement I: Low amplitude displacement with various preloads, 1Hz

5.4 Measurement II: Constant preload at various amplitudes,1Hz sinusoidal

5.5 Measurement III: Constant amplitude and constant preload at various

5.6 Measurement IV: Stress relaxation: Force response to a stepped

displacement over time---------------------------------------------------------60

5.7 Track bush torsional response at various radial loads----------------------62

5.8 Track bush torsional response to duel-sine displacement -----------------63

Chapter 6: Development of a model for rubber components -----------------------64

6.2 The time dependent viscoelastic element -----------------------------------67

6.3 Stress relaxation and the response to duel-sine motion--------------------75

6.5 Summary ---------------------------------------------------------------------- 86

Chapter 7: Comparison between measured and simulated rubber component

7.1 Implementation of the final model in ADAMS software------------------87

7.2 Comparison between measured and simulated response plots------------89

Chapter 8 Summary of the rubber components investigation --------------------97

Chapter 9: The Warrior APC rotary damper --------------------------------------100

9.1 Design of the Warrior APC rotary damper --------------------------------101

Chapter 10: Literature review of automotive suspension damper models ------107