CN108956081A - A kind of experimental rig for warship face rotor starting process - Google Patents
A kind of experimental rig for warship face rotor starting process Download PDFInfo
- Publication number
- CN108956081A CN108956081A CN201810614120.9A CN201810614120A CN108956081A CN 108956081 A CN108956081 A CN 108956081A CN 201810614120 A CN201810614120 A CN 201810614120A CN 108956081 A CN108956081 A CN 108956081A
- Authority
- CN
- China
- Prior art keywords
- rotor
- blade
- starting process
- warship face
- experimental rig
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The embodiment of the invention discloses a kind of experimental rigs for warship face rotor starting process, are related to aeromechanics technology field, can be used in studying the influence that the complex working condition in the rotor starting process of warship face waves blade flapping angle and blade tip displacement.The present invention includes: that warship face rotor starting process simulation test device is mainly made of model ship and rotor system model two parts, and rotor system includes teetering rotor and articulated rotor.The testing system apparatus essential structure includes model ship 1, including hangar 2 and deck 3, blade 4, stop block 5, propeller hub 6, blade clamping device 7, rotary shaft 8, center hinge 9, Anti-slip nut 10, bolt 11, angular transducer 12, motor 13, motor bolt 14, bearing 15, removably naval vessel superstructure 16, hangar door 17, acceleration transducer 19.The present invention is suitable for studying rise/stopping for the rotor craft under the operating condition of sea.
Description
Technical field
The present invention relates to aeromechanics technology field more particularly to a kind of test dresses for warship face rotor starting process
It sets.
Background technique
Different from the operating condition of land, rotor craft at sea flies, warship, pneumatically asking for more complexity can be encountered
Topic.Under normal circumstances, the aerodynamic lift of rotor and blade centrifugal force increase with the revolving speed of rotor and are increased, and are set using traditional
Meter scheme is that can be designed the rotor crafts such as unmanned plane, the helicopter for being much adapted to that land uses.However rotor craft
If the case where at sea working, encountering is then much more complex, such as: sea meteorological condition is complicated, and variable direction, air is flowing through
When naval vessel superstructure, it is often accompanied by the generation of the forms of motion such as separation, reflux, vortex.In addition, the opening and closing of hangar of ship door is to warship
Boat deck flow field also has a great impact.
And rotor craft starts and stalls the stage, rotor revolving speed is lower, and centrifugal force is smaller, blade elongated flexible, right
Outer gas stream variation is sensitive, and when rotation, which easily generates, excessively waves.Due to excessively waving, rotor blade can be sent out with helicopter fuselage
Raw physical impacts.These factors have resulted under marine work condition environment, the complexity of the aerodynamic phenomenon of rotor craft,
So that very difficult with the aerodynamic characteristic of theoretical analysis method Accurate Prediction rotor.
The civilian nothing of market many years especially has been put at present due to lacking suitable experimental provision in civil field
Man-machine product is difficult to be directly applied to maritime environment, and marine worker equipment is also the field that various countries are paid close attention to, military skill therein
Art conversion is civilian more very long, this all constrains the development of the civilian rotor craft under marine work condition environment.
Summary of the invention
The embodiment of the present invention provides a kind of experimental rig for warship face rotor starting process, for studying warship face rotor
Complex working condition in starting process waves the influence of displacement to blade flapping angle and blade tip.
In order to achieve the above objectives, the embodiment of the present invention adopts the following technical scheme that
Warship face rotor starting process simulation test device is mainly made of model ship and rotor system model two parts, rotation
Wing system includes teetering rotor and articulated rotor.The testing system apparatus essential structure include model ship (1) (including
Hangar (2) and deck (3)), blade (4), stop block (5), propeller hub (6), blade clamping device (7), rotary shaft (8), center hinge
(9), Anti-slip nut (10), bolt (11), angular transducer (12), motor (13), motor bolt (14), bearing (15), can fill
The naval vessel superstructure (16) unloaded, hangar door (17), acceleration transducer (19).
The present embodiment is used to wave warship face rotor starting process blade flapping angle and blade tip displacement and effectively be measured,
Blade flapping angle is measured using angular transducer, acceleration transducer measurement blade tip waves displacement.The experimental rig is specifically used
In being tested in wind-tunnel, simulate different wind speed, wind direction sea situation under, warship face rotor lasts the different starting times, lifts up
The blade flapping phenomenon of seesaw type rotor and articulated rotor starting process is studied under different sea situations, different rotor classes with this
The blade flapping problem of type.
Detailed description of the invention
It to describe the technical solutions in the embodiments of the present invention more clearly, below will be to needed in the embodiment
Attached drawing is briefly described, it should be apparent that, drawings in the following description are only some embodiments of the invention, for ability
For the those of ordinary skill of domain, without creative efforts, it can also be obtained according to these attached drawings other attached
Figure.
Fig. 1 is teetering rotor simulation test device schematic diagram provided in an embodiment of the present invention；
Fig. 2 is articulated rotor simulation test device schematic diagram provided in an embodiment of the present invention；
Fig. 3 is teetering rotor restraint device schematic diagram provided in an embodiment of the present invention；
Fig. 4 is articulated rotor restraint device schematic diagram provided in an embodiment of the present invention；
Fig. 5 is motor scheme of installation provided in an embodiment of the present invention；
Fig. 6 is that model ship superstructure provided in an embodiment of the present invention and hangar door are opened and closed schematic diagram；
Fig. 7 is rotor difference provided in an embodiment of the present invention start position schematic diagram；
Wherein: model ship -1, hangar -2, deck -3, blade -4, stop block -5, propeller hub -6, blade clamping device -7,
Rotary shaft -8, center hinge -9, Anti-slip nut -10, bolt -11, angular transducer -12, motor -13, motor bolt -14, bearing -
15, naval vessel superstructure -16, hangar door -17, groove -18, acceleration transducer -19.
Specific embodiment
Technical solution in order to enable those skilled in the art to better understand the present invention, with reference to the accompanying drawing and specific embodiment party
Present invention is further described in detail for formula.Embodiments of the present invention are described in more detail below, the embodiment is shown
Example is shown in the accompanying drawings, and in which the same or similar labels are throughly indicated same or similar element or has identical or class
Like the element of function.It is exemplary below with reference to the embodiment of attached drawing description, for explaining only the invention, and cannot
It is construed to limitation of the present invention.Those skilled in the art of the present technique are appreciated that unless expressly stated, odd number shape used herein
Formula " one ", "one", " described " and "the" may also comprise plural form.It is to be further understood that specification of the invention
Used in wording " comprising " refer to that there are the feature, integer, step, operation, element and/or component, but it is not excluded that
In the presence of or add other one or more features, integer, step, operation, element, component and/or their group.It should be understood that
When we say that an element is " connected " or " coupled " to another element, it can be directly connected or coupled to other elements, or
There may also be intermediary elements.In addition, " connection " used herein or " coupling " may include being wirelessly connected or coupling.Here make
Wording "and/or" includes one or more associated any cells for listing item and all combinations.The art
Technical staff is appreciated that unless otherwise defined all terms (including technical terms and scientific terms) used herein have
Meaning identical with the general understanding of the those of ordinary skill in fields of the present invention.It should also be understood that such as general
Those terms, which should be understood that, defined in dictionary has a meaning that is consistent with the meaning in the context of the prior art, and
Unless defined as here, it will not be explained in an idealized or overly formal meaning.
The embodiment of the present invention provides a kind of experimental rig for warship face rotor starting process, as shown in Figure 1,
Described device is made of model ship (1) and rotor system, and rotor system is mounted on deck (3).
Model ship (1) includes hangar (2) and deck (3).
Rotor system includes: blade (4), stop block (5), propeller hub (6), blade clamping device (7), rotary shaft (8), center
It cuts with scissors (9), Anti-slip nut (10), bolt (11), angular transducer (12), motor (13), motor bolt (14), bearing (15), add
Velocity sensor (19).
Angle sensor (12) is fixed on the lower section of blade clamping device (7), and acceleration transducer (19) is embedded in
Inside blade tip.
Blade (4) is connected by bolt with blade clamping device (7), blade clamping device (7) with propeller hub (6), propeller hub
(6) drive blade (4) around center hinge (9) lower rotation in vertical direction.
Center hinge (9) both ends install Anti-slip nut (10) additional, are fixed on rotary shaft (8), and Anti-slip nut (10) is for preventing
Propeller hub (6) and center hinge (9) are detached from.
The present embodiment is for effectively measuring warship face rotor starting process blade flapping angle, using angular transducer
Blade flapping angle is measured, acceleration transducer measurement blade tip waves displacement.The experimental rig is specifically used for carrying out in wind-tunnel
Test, simulate different wind speed, wind direction sea situation under, warship face rotor lasts different starting times, teetering rotor and hinge
The blade flapping phenomenon of formula rotor starting process is connect, is studied under different sea situations with this, the blade flapping of different rotor types is asked
Topic.
Specifically, as shown in Figure 1, rotor system uses teetering rotor system.Wherein, seesaw as shown in Figure 3 rotation
Wing restraint device schematic diagram, stop block (5) are mounted on above propeller hub (6), and are fixed on rotary shaft (8) by bolt (11),
Stop block (5) is used to preventing rotor blade tip from generating and excessive waves displacement.
Specifically, as shown in Fig. 2, rotor system uses articulated rotor system.Wherein, radial type as shown in Figure 4 rotation
Wing restraint device schematic diagram, the propeller hub (6) of articulated rotor is three connectors, by blade clamping device (7), respectively with 3
Blade (4) is connected.It is opened up in propeller hub (6) groove (18), groove (18) is used to that stop block (5) to be replaced to prevent rotor blade tip from generating
Excessive waves displacement.
Further, as shown in Figure 5, rotary shaft (8) is connected with motor (13) by transmission device, and motor (13) passes through
Motor bolt (14) is fixed on deck (3) back side.
Bearing (15) are installed additional between deck (3) and rotary shaft (8), for guaranteeing motor and concentric rotation axis degree.
Wherein, at least one aperture is opened up on deck (3), aperture is for installing bearing (15).Such as: as shown in Figure 7,
The aperture opened up on deck (3), permutation form is evenly distributed on deck (3), in order to study rotor in different start bits
The pneumatic situation set.
Further, in model ship (1) further include: removably naval vessel superstructure (16) and hangar door (17).Warship
The superstructure (16) of ship model, which can according to need, is loaded and unloaded, and hangar door (17) can be opened and closed, as shown in Figure 6.So as to
To simulate influence of the opening and closing of naval vessel superstructure and hangar door to warship surface current field, warship face rotor was started to probe into flow field
The influence of blade flapping angle in journey.
In the practical application of the present embodiment, by the warship face, rotor starting process simulation test device is placed in wind-tunnel,
To simulate true carrier-based helicopter in the starting process on naval vessel.After incoming flow flows through the hangar on naval vessel, separation, reflux occur for air-flow,
It acts on the rotor blade just started, and since rotor revolving speed is lower, centrifugal force is smaller, blade elongated flexible, to outside
Air-flow variation is sensitive, and when rotation, which easily generates, excessively waves, and due to excessively waving, rotor blade can be with helicopter fuselage generation object
Reason collision.In this wind tunnel test, change the start position of rotor, the displacement and blade flapping angle of blade tip is measured, to probe into
Warship face optimum start position.
Measurement process: the experimental rig of two kinds of different rotor models (is equivalent to reality in wind speed 3m/s, 4m/s, 5m/s respectively
Border wind speed 15m/s, 20m/s, 25m/s), 0 ° of wind direction, 10 °, 20 °, carry out in 30 ° of wind-tunnel.Of two kinds of different rotor models
The dynamic time is respectively 2s, 3.2s, 4.2s, 5.2s (being equivalent to practical starting time 10s, 15s, 20s, 25s).Change simultaneously rotor
Start position A1-C3, as shown in Figure 7.Different rotor models are measured respectively whether there is or not superstructures, hangar door opening and closing, different
In wind speed, different wind directions and different start positions undergo the blade tip of different starting times to wave displacement and blade flapping angle.From
And effectively simulation warship face rotor is in the blade flapping and blade of starting process and the collision process of fuselage.
All the embodiments in this specification are described in a progressive manner, same and similar portion between each embodiment
Dividing may refer to each other, and each embodiment focuses on the differences from other embodiments.Especially for equipment reality
For applying example, since it is substantially similar to the method embodiment, so describing fairly simple, related place is referring to embodiment of the method
Part explanation.The above description is merely a specific embodiment, but protection scope of the present invention is not limited to
This, anyone skilled in the art in the technical scope disclosed by the present invention, the variation that can readily occur in or replaces
It changes, should be covered by the protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of claim
Subject to enclosing.
Claims (8)
1. a kind of experimental rig for warship face rotor starting process, which is characterized in that described device is by model ship (1) and rotation
Wing system composition, rotor system are mounted on deck (3)；
Model ship (1) includes hangar (2) and deck (3)；
Rotor system includes: blade (4), stop block (5), propeller hub (6), blade clamping device (7), rotary shaft (8), center hinge
(9), Anti-slip nut (10), bolt (11), angular transducer (12), motor (13), motor bolt (14), bearing (15), acceleration
It spends sensor (19)；
Angular transducer (12) is fixed on the lower section of blade clamping device (7), and acceleration transducer (19) is embedded in inside blade tip.
2. the experimental rig according to claim 1 for warship face rotor starting process, which is characterized in that blade (4) with
Blade clamping device (7), blade clamping device (7) are connected by bolt with propeller hub (6), and propeller hub (6) drives blade (4) in
The heart cuts with scissors (9) lower rotation in vertical direction；
Center hinge (9) both ends install Anti-slip nut (10) additional, are fixed on rotary shaft (8), and Anti-slip nut (10) is for preventing propeller hub
(6) it is detached from center hinge (9).
3. the experimental rig according to claim 2 for warship face rotor starting process, which is characterized in that if rotor system
Using teetering rotor system, then:
Stop block (5) is mounted on above propeller hub (6), and is fixed on rotary shaft (8) by bolt (11), and stop block (5) is used for
It prevents rotor blade tip from generating and excessive waves displacement.
4. the experimental rig according to claim 2 for warship face rotor starting process, which is characterized in that if rotor system
Using articulated rotor system, then:
The propeller hub (6) of articulated rotor is that three connectors are connected with 3 blades (4) respectively by blade clamping device (7)；
It is opened up in propeller hub (6) groove (18), groove (18) is used to that stop block (5) to be replaced to prevent rotor blade tip from generating excessive wave
Displacement.
5. the experimental rig according to claim 1 for warship face rotor starting process, which is characterized in that rotary shaft (8)
It is connected with motor (13) by transmission device, motor (13) is fixed on deck (3) back side by motor bolt (14)；
Bearing (15) are installed additional between deck (3) and rotary shaft (8), for guaranteeing motor and concentric rotation axis degree.
6. the experimental rig according to claim 1 for warship face rotor starting process, which is characterized in that on deck (3)
At least one aperture is opened up, aperture is for installing bearing (15).
7. the experimental rig according to claim 1 for warship face rotor starting process, which is characterized in that on deck (3)
The aperture opened up, permutation form is evenly distributed on deck (3).
8. the experimental rig according to claim 1 for warship face rotor starting process, which is characterized in that model ship
(1) in further include: removably naval vessel superstructure (16) and hangar door (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810614120.9A CN108956081B (en) | 2018-06-14 | 2018-06-14 | Test device for ship surface rotor wing starting process |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810614120.9A CN108956081B (en) | 2018-06-14 | 2018-06-14 | Test device for ship surface rotor wing starting process |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108956081A true CN108956081A (en) | 2018-12-07 |
| CN108956081B CN108956081B (en) | 2020-12-25 |
Family
ID=64488874
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810614120.9A Active CN108956081B (en) | 2018-06-14 | 2018-06-14 | Test device for ship surface rotor wing starting process |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108956081B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113942639A (en) * | 2021-10-09 | 2022-01-18 | 中国直升机设计研究所 | Helicopter blade droop limiter, upper swing limiter and swing limiting system |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4582013A (en) * | 1980-12-23 | 1986-04-15 | The Holland Corporation | Self-adjusting wind power machine |
| JP2010044032A (en) * | 2008-08-08 | 2010-02-25 | Noriaki Yamaguchi | Wind tunnel for reinforcing torque as wind turbine |
| US8308433B2 (en) * | 2010-09-30 | 2012-11-13 | General Electric Company | System and method for controlling wind turbine blades |
| CN102963533A (en) * | 2012-12-14 | 2013-03-13 | 中国航空工业集团公司上海航空测控技术研究所 | Helicopter health and usage monitoring system (HUMS) and method thereof |
| CN103954426A (en) * | 2014-03-31 | 2014-07-30 | 南京航空航天大学 | Rotor wing dynamic test device |
| US9240083B2 (en) * | 2009-03-02 | 2016-01-19 | Sikorsky Aircraft Corporation | Rotor system health monitoring using shaft load measurements and virtual monitoring of loads |
| CN105716837A (en) * | 2014-12-03 | 2016-06-29 | 中国飞行试验研究院 | Airborne rotor motion measurement method based on PSD optical imaging |
| CN106599419A (en) * | 2016-12-02 | 2017-04-26 | 中国船舶工业系统工程研究院 | Ship stern flow field numerical simulation and wind tunnel experiment data comprehensive comparison method |
| CN206155788U (en) * | 2016-10-25 | 2017-05-10 | 深圳创壹通航科技有限公司 | Rotor device and autogyro of autogyro |
| CN107140202A (en) * | 2017-05-12 | 2017-09-08 | 上海寅翅智能科技有限公司 | A kind of centrifugal flapping hinge rotor head |
| CN107310721A (en) * | 2017-07-17 | 2017-11-03 | 飞瑞航空科技（江苏）有限公司 | A kind of depopulated helicopter rotor oar clamp mechanism |
| CN107672793A (en) * | 2017-08-25 | 2018-02-09 | 珠海磐磊智能科技有限公司 | Rotor driver, aircraft and its flight control method |
| CN207141389U (en) * | 2017-08-15 | 2018-03-27 | 深圳市道通智能航空技术有限公司 | Fold propeller, Power Component and unmanned vehicle |
-
2018
- 2018-06-14 CN CN201810614120.9A patent/CN108956081B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4582013A (en) * | 1980-12-23 | 1986-04-15 | The Holland Corporation | Self-adjusting wind power machine |
| JP2010044032A (en) * | 2008-08-08 | 2010-02-25 | Noriaki Yamaguchi | Wind tunnel for reinforcing torque as wind turbine |
| US9240083B2 (en) * | 2009-03-02 | 2016-01-19 | Sikorsky Aircraft Corporation | Rotor system health monitoring using shaft load measurements and virtual monitoring of loads |
| US8308433B2 (en) * | 2010-09-30 | 2012-11-13 | General Electric Company | System and method for controlling wind turbine blades |
| CN102963533A (en) * | 2012-12-14 | 2013-03-13 | 中国航空工业集团公司上海航空测控技术研究所 | Helicopter health and usage monitoring system (HUMS) and method thereof |
| CN103954426A (en) * | 2014-03-31 | 2014-07-30 | 南京航空航天大学 | Rotor wing dynamic test device |
| CN105716837A (en) * | 2014-12-03 | 2016-06-29 | 中国飞行试验研究院 | Airborne rotor motion measurement method based on PSD optical imaging |
| CN206155788U (en) * | 2016-10-25 | 2017-05-10 | 深圳创壹通航科技有限公司 | Rotor device and autogyro of autogyro |
| CN106599419A (en) * | 2016-12-02 | 2017-04-26 | 中国船舶工业系统工程研究院 | Ship stern flow field numerical simulation and wind tunnel experiment data comprehensive comparison method |
| CN107140202A (en) * | 2017-05-12 | 2017-09-08 | 上海寅翅智能科技有限公司 | A kind of centrifugal flapping hinge rotor head |
| CN107310721A (en) * | 2017-07-17 | 2017-11-03 | 飞瑞航空科技（江苏）有限公司 | A kind of depopulated helicopter rotor oar clamp mechanism |
| CN207141389U (en) * | 2017-08-15 | 2018-03-27 | 深圳市道通智能航空技术有限公司 | Fold propeller, Power Component and unmanned vehicle |
| CN107672793A (en) * | 2017-08-25 | 2018-02-09 | 珠海磐磊智能科技有限公司 | Rotor driver, aircraft and its flight control method |
Non-Patent Citations (4)
| Title |
|---|
| NEWMAN,SIMON JAMES: "An investigation into the phenomenon of helicopter blade sailing", 《UNIVERSITY OF SOUTHAMPTON》 * |
| S.J. NEWMAN: "The verification of a theoretical helicopter rotor blade sailing method by means of windtunnel testing", 《AERONAUTICAL JOURNAL》 * |
| 吴世杰: "直升机桨叶扬起下坠接触过程动力学研究", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
| 薛建海、宋辰瑶、郭艳颖主编: "《R44直升机系统》", 30 September 2015, 西北工业大学出版社 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113942639A (en) * | 2021-10-09 | 2022-01-18 | 中国直升机设计研究所 | Helicopter blade droop limiter, upper swing limiter and swing limiting system |
| CN113942639B (en) * | 2021-10-09 | 2023-05-05 | 中国直升机设计研究所 | Centrifugal blade swing limiting system of helicopter |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108956081B (en) | 2020-12-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Chen et al. | Design and analysis of folding propulsion mechanism for hybrid-driven underwater gliders | |
| CN105003395A (en) | Motion performance test model and method for floating draught fan | |
| Serrano et al. | Effect of disk angle-of-attack on aerodynamic performance of small propellers | |
| Wang et al. | AirDyn: an instrumented model-scale helicopter for measuring unsteady aerodynamic loading in airwakes | |
| Healey | The prospects for simulating the helicoptership interface | |
| Wisniewski et al. | The influence of airfoil shape, Reynolds number and chord length on small propeller performance and noise | |
| CN108956081A (en) | A kind of experimental rig for warship face rotor starting process | |
| Van Treuren et al. | Near and far field noise decay from a quadcopter propeller with and without a leading edge notch | |
| Taymourtash et al. | Unsteady load assessment of a scaled-helicopter model in a ship airwake | |
| Van Treuren et al. | Acoustically Testing Stock and Modified UAS Propellers in Both the Near and Far Field | |
| Tanner et al. | Experimental boundary layer study on hovering rotors | |
| Oldeweme et al. | Experiment Design for a Distributed Propulsion configuration at High Lift | |
| Feil et al. | Computational and experimental aeromechanics analysis of a coaxial rotor system in hover and forward flight | |
| KR102423920B1 (en) | Propeller performance test device | |
| Mateer et al. | Superstructure aerodynamics of the Type 26 global combat ship | |
| Sabzehparvar | In-flight thrust measurements of propeller-driven airplanes | |
| Berry et al. | Wind tunnel testing of an instrumented rotor at high advance ratio | |
| CN109625316A (en) | The measurement method of hinge moment on the inside of super high aspect ratio wing rudder face | |
| Philipsen et al. | An overview of advanced propeller simulation tests in the german dutch wind tunnels (DNW) | |
| Hota et al. | Aerodynamic characterization of a rotor in free rotation | |
| Tung et al. | A comparison of airload data between model-scale rotor and full-scale flight test | |
| Ortolani et al. | Investigation of single propeller blade loads during turning motion by free running manoeuvring model tests | |
| Abrego et al. | A Small-Scale Tiltrotor Model Operating in Descending Flight | |
| Hook | Aerodynamic Experiments of a Dual Ducted Fan Vehicle in Hover and Edgewise Flight | |
| Kolewe et al. | MARSPEED-Modelling and Real Time Simulating the Motion of a Wing-in-Ground-Effect Vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |