CN107727340A - The elastic vibration mode testing method of rotary missile - Google Patents
The elastic vibration mode testing method of rotary missile Download PDFInfo
- Publication number
- CN107727340A CN107727340A CN201710714401.7A CN201710714401A CN107727340A CN 107727340 A CN107727340 A CN 107727340A CN 201710714401 A CN201710714401 A CN 201710714401A CN 107727340 A CN107727340 A CN 107727340A
- Authority
- CN
- China
- Prior art keywords
- guided missile
- rolling
- missile
- elastic
- vibration mode
- 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
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0066—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by exciting or detecting vibration or acceleration
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
Abstract
The invention provides a kind of elastic vibration mode testing method of rotary missile, it comprises the following steps：Step 1, guided missile is horizontally suspended by two elastic threads, connected between guided missile and elastic threads using rolling bearing, make guided missile around the free rolling of the longitudinal axis；Guided missile one end is connected by fixture with a Flexible Rotating, and a rolling drive device drives guided missile rolling by Flexible Rotating so that body can produce laterally free displacement, and rotating speed is controllable simultaneously, eliminates boundary constraint of the rolling driving to body tail end；Step 2, the rolling drive device being made up of motor, deceleration device, Flexible Rotating and drive control device, guided missile can be driven to reach and maintain to specify rotating speed rolling, rotating speed continuously adjustabe in the range of 0~20 revolutions per second.Present invention obtains the elastic response characteristic under guided missile rotation status, can apply to mould measurement of the guided missile under rotation status.
Description
Technical field
The present invention relates to guided missile elastic vibration and mould measurement field, in particular it relates to a kind of elastic vibrating of rotary missile
Dynamic mode testing method.
Background technology
Rotary missile due to cost is low, response quickly, beneficial to miniaturization and suitable dress property it is good the features such as, in guided weapon field
With huge development potentiality and application prospect.For the rapidity of raising, reduce flight resistance, rotary missile be commonly designed compared with
Big slenderness ratio, therefore the rigidity of structure is relatively low；Simultaneously as the raising of maneuverability requirement, missile flight overload are increasing.
Under the conditions of the big angle of attack, body can produce serious elastic deformation.Exemplified by drawing nurse guided missile by the U.S., its slenderness ratio is maximum more than 20
Flight overload more than 45g, body longitudinal side are notable to elastic vibration.
Longitudinal side is that high mobile missile master-plan and Control System Design must take into consideration to elastic vibration, especially for
Rotary missile, body elastic vibration characteristics of mode under rotation status will change, while suffered aerodynamic loading is also with rotating speed
Cyclically-varying, cause elastic movement to produce serious cross-couplings with rotary motion and act on.One side cross-couplings reduce bullet
The dynamic stability of body, it may cause occur the dynamic instability caused by elastic deformation in missile flight；On the other hand, coupling
The measurement output that dynamic response has a strong impact on control feedback transducer is closed, causes the control system designed according to non-rotating situation
Control in practical flight and do not restrain, cause flight to fail.
In order to solve the influence that rotary missile elastic vibration is brought to master-plan and guidance control system design, accurately obtain
It is highly important to obtain the elastic vibration characteristics of guided missile in rotating condition.Guided missile elastic modal parameters are obtained using research technique
It is the basis of missile dynamics modeling and Control System Design with the changing rule of rotating speed.For the springform of non-rotating guided missile
State method of testing has developed into ripe, but this method can not be applied to mould measurement of the guided missile under rotation status.
The content of the invention
For in the prior art the defects of, it is an object of the invention to provide a kind of elastic vibration mould measurement of rotary missile
Method, the elastic response characteristic under guided missile rotation status is which gived, can apply to mode of the guided missile under rotation status and survey
Examination.
According to an aspect of the present invention, there is provided a kind of elastic vibration mode testing method of rotary missile, its feature exist
In the elastic vibration mode testing method of the rotary missile comprises the following steps：
Step 1, guided missile is horizontally suspended by two elastic threads, connected between guided missile and elastic threads using rolling bearing,
Make guided missile around the free rolling of the longitudinal axis；Guided missile one end is connected by fixture with a Flexible Rotating, and a rolling drive device passes through
Flexible Rotating drives guided missile rolling so that body can produce laterally free displacement, and rotating speed is controllable simultaneously, eliminates rolling driving pair
The boundary constraint of body tail end；
Step 2, the rolling drive device being made up of motor, deceleration device, Flexible Rotating and drive control device, can drive
Dynamic guided missile reaches and maintains to specify rotating speed rolling, rotating speed continuously adjustabe in the range of 0~20 revolutions per second；
Step 3, guided missile is divided into N number of website vertically, N is natural number and N >=10, and each website installs acceleration
Sensor, the copybook of sensor one are mounted in body surface, and acceleration transducer response output is sent out in real time by wireless data transmission device
Ground base station is sent to, and by the first data logger recording responses signal；
Step 4, drop-hanger bearing is encouraged vertically upward using power hammer, pumping signal is output to the second number through charge amplifier
According to recorder, and spectrum analyzer is input to together with the sensor response signal of the first data logger, using orthogonal multinomial
Formula method identifies modal parameter of the guided missile under given rotating speed.
Preferably, the rigidity of the rolling bearing, the rigidity of fixture, which are both greater than, is tested the 1.5 of guided missile maximum test frequency
Times；The frequency of elastic threads is less than the 10% of subject guided missile fundamental frequency；The body initial level limits of error of elastic threads are not
More than 5 ‰, the extensibility of elastic threads should be between 40%~60%；The gross mass of rolling bearing and fixture is no more than full bullet quality
2%.
Preferably, the rolling bearing is made up of internal layer anchor ear, single-groove grooved ball bearing, outer layer anchor ear and axial baffle,
Internal layer anchor ear can be fixed on body surface, and outer layer anchor ear is connected with elastic threads.
Preferably, the Flexible Rotating is steel rod structure, and its corner frequency is less than subject guided missile fundamental frequency
10%, the first-order modal frequency and Free Modal frequency of the subject guided missile under the constraints are less than 1% compared to deviation, second order
Modal frequency deviation is less than 3%, and three rank modal frequency deviations are less than 5%.
Preferably, the acceleration transducer packet is connected with multiple wireless data transmission devices.
Preferably, the elastic vibration mode testing method of the rotary missile is using mounting bracket, elastic threads, wobble shaft
Hold, rolling drive device, wireless senser measuring system, power hammer excitation system and spectrum analyzer, rolling drive device by
Fixture, Flexible Rotating, motor, deceleration device and drive control device composition, wireless senser measuring system by acceleration transducer,
Wireless data transmission device, ground base station and the first data logger composition, power hammer excitation system force hammer, charge amplifier and the
Two data loggers form.
Preferably, the Flexible Rotating and guided missile are in alignment, and in same level plane.
Preferably, mode ginseng of the spectrum analyzer using orthogonal polynomial method identification guided missile under given rotating speed
Number, orthogonal polynomial method are using the rational fraction of frequency response function as mathematical modeling, and Laplace transformation is carried out to system differential equation,
Equationof structure group, obtains the eigen vector of system, finally identifies each modal parameter.
Compared with prior art, the present invention has following beneficial effect：The present invention is outstanding using being made up of rolling bearing
Extension system, body can rotate freely during experiment, while by rolling drive device, body rotating speed is controllable and linearly may be used
Adjust.Using the rolling drive system being made up of Flexible Rotating, Flexible Rotating is steel rod structure, can be transmitted caused by motor
Rolling driving moment, simultaneously because its structural modal frequency is much smaller than the longitudinal side of guided missile to structural modal frequency, to test result
Influence can be ignored.Using the wireless senser measuring system being made up of high-sensitivity accelerometer, solves acceleration sensing
Device caused wire winding problem during guided missile rolling.It is special present invention obtains the elastic response under guided missile rotation status
Property, available for instructing rotary missile master-plan and Control System Design.
Brief description of the drawings
The detailed description made by reading with reference to the following drawings to non-limiting example, further feature of the invention,
Objects and advantages will become more apparent upon：
Fig. 1 is the fundamental diagram of the elastic vibration mode testing method of the rotary missile of the present invention.
Embodiment
With reference to specific embodiment, the present invention is described in detail.Following examples will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill to this area
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection domain.
As shown in figure 1, the elastic vibration mode testing method of rotary missile of the present invention comprises the following steps：
Step 1, guided missile is horizontally suspended by two elastic threads, connected between guided missile and elastic threads using rolling bearing,
Allow guided missile around the free rolling of its longitudinal axis；Guided missile one end (generally selecting tail end) is connected by fixture with a Flexible Rotating,
One rolling drive device drives guided missile rolling by Flexible Rotating so that body can produce laterally free displacement rotating speed simultaneously
It is controllable, eliminate boundary constraint of the rolling driving to body tail end；
Step 2, the rolling drive device being made up of motor, deceleration device, Flexible Rotating and drive control device, can drive
Dynamic guided missile reaches and maintains to specify rotating speed rolling, rotating speed continuously adjustabe in the range of 0~20 revolutions per second；
Step 3, guided missile is divided into N number of website vertically, N is natural number and N >=10, and each website installs acceleration
Sensor, the copybook of sensor one are mounted in body surface, and acceleration transducer response output is sent out in real time by wireless data transmission device
Ground base station is sent to, and by the first data logger A recording responses signals；
Step 4, drop-hanger bearing is encouraged vertically upward using power hammer, pumping signal is output to the second number through charge amplifier
According to recorder B, and spectrum analyzer is input to together with the first data logger A sensor response signal, using orthogonal more
Modal parameter of the item formula method identification guided missile under given rotating speed.
The rigidity of rolling bearing, the rigidity of fixture are both greater than 1.5 times of subject guided missile maximum test frequency；The frequency of elastic threads
Rate is less than the 10% of subject guided missile fundamental frequency；The body initial level limits of error of elastic threads are no more than 5 ‰, elastic threads
Extensibility should be between 40%~60%；The gross mass of rolling bearing and fixture is no more than the 2% of full bullet quality, improves accurate
Degree.
Rolling bearing is made up of internal layer anchor ear, single-groove grooved ball bearing, outer layer anchor ear and axial baffle, and internal layer anchor ear can
Body surface is fixed on, outer layer anchor ear is connected with elastic threads, so improves intensity.
Flexible Rotating is steel rod structure, and its corner frequency is less than the 10% of subject guided missile fundamental frequency, in the constraint
Under the conditions of subject guided missile first-order modal frequency and Free Modal frequency compared to deviation be less than 1%, second-order modal frequency departure
It is less than 5% less than 3%, three rank modal frequency deviation, improves accuracy.
In experiment, guided missile is reached by motor driving and maintains the rotating speed specified, and pulsed excitation suspended axle is hammered into shape using power
The outer wall held, acceleration transducer output on bullet is delivered to by ground base station by wireless data transmission device and recorded.According to
The excitation of data logger collection and response signal, using spectrum analyzer using orthogonal polynomial method identification guided missile given
Modal parameter under rotating speed.This method obtains the elastic response characteristic under guided missile rotation status, available for instructing rotary missile
Master-plan and Control System Design.
Acceleration transducer packet is connected with multiple wireless data transmission devices so that body rolling is not connected wire and done
Disturb.
The elastic vibration mode testing method of rotary missile of the present invention is using mounting bracket 1, elastic threads, rolling bearing, rolling
Rotary driving device, wireless senser measuring system, power hammer excitation system and spectrum analyzer, rolling drive device by fixture,
Flexible Rotating, motor, deceleration device and drive control device composition, wireless senser measuring system is by acceleration transducer, wireless
Data transmission device, ground base station and the first data logger composition, power hammer excitation system force hammer, charge amplifier and the second number
Formed according to recorder, so easy to use, simple in construction, cost is low.Flexible Rotating and guided missile are in alignment, and in same water
In average face, stability is so improved.
Data storage (such as response signal) is output to spectrum analysis by the first data logger and the second data logger
Instrument, modal parameter of the spectrum analyzer using orthogonal polynomial method identification guided missile under given rotating speed, orthogonal polynomial method
It is using the rational fraction of frequency response function as mathematical modeling, Laplace transformation is carried out to system differential equation, equationof structure group is obtained and is
The eigen vector of system, each modal parameter is finally identified, so improves accuracy.
The specific embodiment of the present invention is described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring the substantive content of the present invention.
Claims (8)
- A kind of 1. elastic vibration mode testing method of rotary missile, it is characterised in that the elastic vibrating dynamic model of the rotary missile State method of testing comprises the following steps：Step 1, guided missile is horizontally suspended by two elastic threads, connected between guided missile and elastic threads using rolling bearing, make to lead Bullet is around the free rolling of the longitudinal axis；Guided missile one end is connected by fixture with a Flexible Rotating, and a rolling drive device passes through flexibility Rotating shaft drives guided missile rolling so that body can produce laterally free displacement, and rotating speed is controllable simultaneously, eliminates rolling driving to body The boundary constraint of tail end；Step 2, the rolling drive device being made up of motor, deceleration device, Flexible Rotating and drive control device, can drive and lead Bullet reaches and maintains to specify rotating speed rolling, rotating speed continuously adjustabe in the range of 0~20 revolutions per second；Step 3, guided missile is divided into N number of website vertically, N is natural number and N >=10, and each website installs acceleration sensing Device, the copybook of sensor one are mounted in body surface, and acceleration transducer response output is sent in real time by wireless data transmission device Ground base station, and by the first data logger recording responses signal；Step 4, drop-hanger bearing is encouraged vertically upward using power hammer, pumping signal is output to the second data through charge amplifier and remembered Instrument is recorded, and spectrum analyzer is input to together with the sensor response signal of the first data logger, using orthogonal polynomial side Method identifies modal parameter of the guided missile under given rotating speed.
- 2. the elastic vibration mode testing method of rotary missile according to claim 1, it is characterised in that the wobble shaft Rigidity, the rigidity of fixture held are both greater than 1.5 times of subject guided missile maximum test frequency；The frequency of elastic threads is less than subject guided missile The 10% of fundamental frequency；The body initial level limits of error of elastic threads are no more than 5 ‰, and the extensibilitys of elastic threads should be Between 40%~60%；The gross mass of rolling bearing and fixture is no more than the 2% of full bullet quality.
- 3. the elastic vibration mode testing method of rotary missile according to claim 1, it is characterised in that the wobble shaft Body table can be fixed on by internal layer anchor ear, single-groove grooved ball bearing, outer layer anchor ear and axial baffle composition, internal layer anchor ear by holding Face, outer layer anchor ear are connected with elastic threads.
- 4. the elastic vibration mode testing method of rotary missile according to claim 1, it is characterised in that described flexible turn Axle is steel rod structure, and its corner frequency is less than the 10% of subject guided missile fundamental frequency, and the subject under the constraints is led The first-order modal frequency and Free Modal frequency of bullet are less than 1% compared to deviation, and second-order modal frequency departure is less than 3%, three rank moulds State frequency departure is less than 5%.
- 5. the elastic vibration mode testing method of rotary missile according to claim 1, it is characterised in that the acceleration Sensor group is connected with multiple wireless data transmission devices.
- 6. the elastic vibration mode testing method of rotary missile according to claim 1, it is characterised in that the rotation is led The elastic vibration mode testing method of bullet is using mounting bracket, elastic threads, rolling bearing, rolling drive device, wireless senser Measuring system, power hammer excitation system and spectrum analyzer, rolling drive device is by fixture, Flexible Rotating, motor, deceleration device With drive control device form, wireless senser measuring system by acceleration transducer, wireless data transmission device, ground base station and First data logger forms, power hammer excitation system force hammer, charge amplifier and the second data logger composition.
- 7. the elastic vibration mode testing method of rotary missile according to claim 1, it is characterised in that described flexible turn Axle and guided missile are in alignment, and in same level plane.
- 8. the elastic vibration mode testing method of rotary missile according to claim 1, it is characterised in that the frequency spectrum point Modal parameter of the analyzer using orthogonal polynomial method identification guided missile under given rotating speed, orthogonal polynomial method is with frequency response letter Several rational fractions is mathematical modeling, and Laplace transformation is carried out to system differential equation, equationof structure group, obtains the characteristic value of system With characteristic vector, each modal parameter is finally identified.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710714401.7A CN107727340B (en) | 2017-08-18 | 2017-08-18 | The elastic vibration mode testing method of rotary missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710714401.7A CN107727340B (en) | 2017-08-18 | 2017-08-18 | The elastic vibration mode testing method of rotary missile |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107727340A true CN107727340A (en) | 2018-02-23 |
| CN107727340B CN107727340B (en) | 2019-09-17 |
Family
ID=61205223
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710714401.7A Active CN107727340B (en) | 2017-08-18 | 2017-08-18 | The elastic vibration mode testing method of rotary missile |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107727340B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108845553A (en) * | 2018-06-15 | 2018-11-20 | 上海航天控制技术研究所 | A kind of servo elastic vibration inhibition comprehensive test method for elongated aircraft |
| CN109323831A (en) * | 2018-09-05 | 2019-02-12 | 哈尔滨工程大学 | A kind of elongate rotation shaft modal test device discharging advocate approach suddenly based on preload |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0838673A1 (en) * | 1996-10-03 | 1998-04-29 | AEROSPATIALE Société Nationale Industrielle | Device for simulating the aerodynamic forces appleid on two orientable aerodynamic surfaces of a vehicle such as a missile |
| CN1477381A (en) * | 2003-07-10 | 2004-02-25 | 上海交通大学 | Synchronous hammering mode test control equpment |
| US20080179993A1 (en) * | 2007-01-30 | 2008-07-31 | Sanderson Terry M | Structural material with piezoelectric material particles |
| CN102169046A (en) * | 2010-12-22 | 2011-08-31 | 北京航空航天大学 | Online elastic mode testing system for magnetically suspended electromechanical equipment |
| CN102901611A (en) * | 2012-09-29 | 2013-01-30 | 西安空间无线电技术研究所 | Rapid checking method for damage of modal test-based spaceborne antenna structure |
| CN103077259A (en) * | 2011-10-26 | 2013-05-01 | 上海机电工程研究所 | Hypersonic speed guided missile multi-field coupling dynamics integrated simulation analysis method |
| CN103630313A (en) * | 2012-08-27 | 2014-03-12 | 北京强度环境研究所 | Excitation system of thermal mode testing of aircraft heating structure and excitation method thereof |
| CN104048562A (en) * | 2013-09-30 | 2014-09-17 | 中国人民解放军国防科学技术大学 | Whole-missile vertical vibration test protection device |
| WO2015160945A1 (en) * | 2014-04-15 | 2015-10-22 | Lord Corporation | Systems and methods for structural health monitoring and protection |
| CN105547618A (en) * | 2015-12-03 | 2016-05-04 | 北京机械设备研究所 | Modal analysis method based on folding control surface rudder system |
| CN105571867A (en) * | 2016-01-21 | 2016-05-11 | 苏州东菱振动试验仪器有限公司 | Vibration control experiment platform for aero-engine |
| CN106053000A (en) * | 2016-07-15 | 2016-10-26 | 北京强度环境研究所 | Missile and carrier rocket modal test method |
| CN106124144A (en) * | 2016-06-15 | 2016-11-16 | 中国科学院光电研究院 | A kind of aerostatics mode testing method and system |
| CN106289680A (en) * | 2016-08-01 | 2017-01-04 | 中国航天空气动力技术研究院 | Assay device for the quiet aeroelastic test of wind-tunnel |
-
2017
- 2017-08-18 CN CN201710714401.7A patent/CN107727340B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0838673A1 (en) * | 1996-10-03 | 1998-04-29 | AEROSPATIALE Société Nationale Industrielle | Device for simulating the aerodynamic forces appleid on two orientable aerodynamic surfaces of a vehicle such as a missile |
| CN1477381A (en) * | 2003-07-10 | 2004-02-25 | 上海交通大学 | Synchronous hammering mode test control equpment |
| US20080179993A1 (en) * | 2007-01-30 | 2008-07-31 | Sanderson Terry M | Structural material with piezoelectric material particles |
| CN102169046A (en) * | 2010-12-22 | 2011-08-31 | 北京航空航天大学 | Online elastic mode testing system for magnetically suspended electromechanical equipment |
| CN103077259A (en) * | 2011-10-26 | 2013-05-01 | 上海机电工程研究所 | Hypersonic speed guided missile multi-field coupling dynamics integrated simulation analysis method |
| CN103630313A (en) * | 2012-08-27 | 2014-03-12 | 北京强度环境研究所 | Excitation system of thermal mode testing of aircraft heating structure and excitation method thereof |
| CN102901611A (en) * | 2012-09-29 | 2013-01-30 | 西安空间无线电技术研究所 | Rapid checking method for damage of modal test-based spaceborne antenna structure |
| CN104048562A (en) * | 2013-09-30 | 2014-09-17 | 中国人民解放军国防科学技术大学 | Whole-missile vertical vibration test protection device |
| WO2015160945A1 (en) * | 2014-04-15 | 2015-10-22 | Lord Corporation | Systems and methods for structural health monitoring and protection |
| CN105547618A (en) * | 2015-12-03 | 2016-05-04 | 北京机械设备研究所 | Modal analysis method based on folding control surface rudder system |
| CN105571867A (en) * | 2016-01-21 | 2016-05-11 | 苏州东菱振动试验仪器有限公司 | Vibration control experiment platform for aero-engine |
| CN106124144A (en) * | 2016-06-15 | 2016-11-16 | 中国科学院光电研究院 | A kind of aerostatics mode testing method and system |
| CN106053000A (en) * | 2016-07-15 | 2016-10-26 | 北京强度环境研究所 | Missile and carrier rocket modal test method |
| CN106289680A (en) * | 2016-08-01 | 2017-01-04 | 中国航天空气动力技术研究院 | Assay device for the quiet aeroelastic test of wind-tunnel |
Non-Patent Citations (1)
| Title |
|---|
| 解本政 等: "某型导弹弹体结构模态试验分析方法探讨", 《第二十一届全国振动与噪声高技术及应用学术会议论文集》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108845553A (en) * | 2018-06-15 | 2018-11-20 | 上海航天控制技术研究所 | A kind of servo elastic vibration inhibition comprehensive test method for elongated aircraft |
| CN109323831A (en) * | 2018-09-05 | 2019-02-12 | 哈尔滨工程大学 | A kind of elongate rotation shaft modal test device discharging advocate approach suddenly based on preload |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107727340B (en) | 2019-09-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105136423B (en) | Consider the data analysing method of the free vibration dynamic derivative testing of frictional force | |
| CN103234729B (en) | Video measuring method of pneumatic rigidity and pneumatic damping in conventional wind tunnel force test | |
| CN104155054B (en) | A kind of frequency domain detection method of the rotary inertia rocking platform based on air supporting | |
| CN103471803A (en) | Method for determining aerodynamic parameters of model free flight tests | |
| US20190308721A1 (en) | Integrated smart sensing systems and methods | |
| CN105547618A (en) | Modal analysis method based on folding control surface rudder system | |
| CN109606732A (en) | A kind of efficient Aircraft Quality characteristic measurement method | |
| CN107064559A (en) | A kind of SINS accelerometer frequency characteristic test methods based on angle oscillating motion | |
| CN107727340B (en) | The elastic vibration mode testing method of rotary missile | |
| CN103323625A (en) | Error calibration compensation method of accelerometers in MEMS-IMU under dynamic environment | |
| CN104236795A (en) | Method and device for measuring rotation inertia of revolution body online | |
| CN106840590A (en) | A kind of component of miniaturized large-load integral type five dynamic pitching balance | |
| CN104198152B (en) | Bionic flapping-wing flying vehicle rises force test device and method of testing thereof | |
| CN101788305A (en) | Method for rapid field calibration of micro inertial measurement unit | |
| CN107388907A (en) | A kind of Free Modal pilot system under guided missile autorotation | |
| CN116296237B (en) | Vertical wind load test method for large carrier rocket in low-speed wind tunnel | |
| US8256276B2 (en) | Ball movement path measuring method | |
| CN203216468U (en) | Oil pumping unit suspension center displacement measuring apparatus | |
| CN116624137A (en) | Deep rock mass while-drilling data processing method and related device | |
| CN205280389U (en) | Measure airborne equipment of aircraft tire decrement | |
| CN101832782B (en) | Method for quick field calibration of micro inertial measurement unit | |
| CN108845159B (en) | Structure angular acceleration measuring device and method based on dynamic measurement centrifugal force | |
| Kamal et al. | Modeling and simulation of propeller propulsion model using wind tunnel | |
| CN108845553B (en) | Servo elastic vibration suppression comprehensive inspection method for slender aircraft | |
| CN104483067A (en) | Measuring method of dynamic unbalance amount of fan |
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 |