CN107121254B - A kind of large size guided missile on-hook vibration rig and method - Google Patents
A kind of large size guided missile on-hook vibration rig and method Download PDFInfo
- Publication number
- CN107121254B CN107121254B CN201710458403.4A CN201710458403A CN107121254B CN 107121254 B CN107121254 B CN 107121254B CN 201710458403 A CN201710458403 A CN 201710458403A CN 107121254 B CN107121254 B CN 107121254B
- Authority
- CN
- China
- Prior art keywords
- hook
- test
- vibration
- guided missile
- air spring
- 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.)
- Active
Links
- 238000000034 method Methods 0.000 title claims description 10
- 238000012360 testing method Methods 0.000 claims abstract description 85
- 238000009434 installation Methods 0.000 claims abstract description 14
- 238000006073 displacement reaction Methods 0.000 claims abstract description 12
- 230000005284 excitation Effects 0.000 claims description 18
- 238000004458 analytical method Methods 0.000 claims description 10
- 230000005540 biological transmission Effects 0.000 claims description 10
- 238000013461 design Methods 0.000 claims description 9
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 7
- 230000004044 response Effects 0.000 claims description 7
- 238000002474 experimental method Methods 0.000 claims description 6
- 239000000203 mixture Substances 0.000 claims description 6
- 238000012790 confirmation Methods 0.000 claims description 5
- 238000005457 optimization Methods 0.000 claims description 4
- 238000005452 bending Methods 0.000 claims description 3
- 238000007405 data analysis Methods 0.000 claims description 3
- 238000013480 data collection Methods 0.000 claims description 3
- 238000013523 data management Methods 0.000 claims description 3
- 238000011161 development Methods 0.000 claims description 3
- 238000011068 loading method Methods 0.000 claims description 3
- 238000005259 measurement Methods 0.000 claims description 3
- 239000000725 suspension Substances 0.000 claims description 3
- 238000001629 sign test Methods 0.000 claims 1
- 238000004088 simulation Methods 0.000 abstract description 7
- 230000008859 change Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 230000003116 impacting effect Effects 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 241000486406 Trachea Species 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 235000013399 edible fruits Nutrition 0.000 description 1
- 238000013401 experimental design Methods 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 210000003437 trachea Anatomy 0.000 description 1
- 230000032258 transport Effects 0.000 description 1
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
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/06—Multidirectional test stands
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
- Vibration Prevention Devices (AREA)
Abstract
大型导弹挂机振动试验设备，由挂机模拟边界结构支撑件、挂架转接装置、空气弹簧支撑系统、挂架、挂机导弹、空气压缩机、激光位移计、压力控制器、振动工装、球头、垂向振动台、水平振动台安装基座、水平振动台、试验承载基座组成，其特征在于，挂机导弹安装在挂架上，挂架通过挂机转接装置安装在挂机模拟边界结构支撑件上；挂机模拟边界结构支撑件安装在空气弹簧支撑系统上，空气弹簧支撑系统安装在试验承载基座上；垂向振动台与水平振动台通过球头与振动工装连接，振动工装用来固定挂机导弹。
Large-scale missile on-hook vibration test equipment, consisting of on-hook simulated boundary structure support, pylon adapter, air spring support system, pylon, on-hook missile, air compressor, laser displacement meter, pressure controller, vibration tooling, ball head, It is composed of a vertical vibration table, a horizontal vibration table installation base, a horizontal vibration table and a test bearing base. It is characterized in that the on-hook missile is installed on the pylon, and the pylon is installed on the support of the on-hook simulated boundary structure through the on-hook transfer device. The on-hook simulation boundary structure support is installed on the air spring support system, and the air spring support system is installed on the test bearing base; the vertical shaking table and the horizontal shaking table are connected with the vibration tool through the ball head, and the vibration tool is used to fix the on-hook missile .
Description
Technical field
The present invention relates to Structural Dynamics fields, and in particular to large-scale guided missile multiple spot multiaxis on-hook vibration experiment.
Background technique
For on-hook guided missile, by aircraft vehicle vibrations transmitting and Aerodynamic force action when flight, certain vibration environment can be born, it is right
Its structural strength impacts.In order to guarantee product safety and reliability, for hanging product aboard, require out
Open up the examination of on-hook vibration environment test.If can effectively be examined to product by true ground simulation test, protect
Card will not generate destruction in use, to guarantee that product has enough fatigue resistances.
Traditional on-hook vibration test is generallyd use testpieces is directly fixed or is individually being shaken with frame Suspending fixation
On dynamic platform, one direction once carries out vibration test.And after large-scale guided missile is hanging on aircraft, by aircraft edge effect, power
Learning characteristic can change, and since guided missile quality is excessive, the coupling with aircraft enhances, and cause low frequency dynamic stress serious, have
Stronger boundary effect.In addition, large-scale guided missile frequency is lower, it is easy to appear response and is unevenly distributed, not only influence thrust, it is also possible to
It will cause local overtesting.
Therefore, it in order to guarantee airborne missile product reliability, when carrying out full bullet on-hook vibration test program planning, needs
It is reasonably designed, selects optimal excitation and control program, and in view of boundary effect is simulated, just can increase ground
Authenticity is tested in interview.
Summary of the invention
The purpose of the present invention is to the above problems, it is desirable to provide a kind of vibration of truer reflection on-hook large size guided missile
Analogy method realizes the true ground examination of on-hook guided missile, effectively assesses the fatigue resistance of on-hook guided missile, guarantee the safe and reliable of product
Property.
The invention discloses: a kind of large size guided missile on-hook vibration rig by on-hook simulating boundary structural support, is hung
Frame switching device, air spring support system, hanger, on-hook guided missile, air compressor, laser displacement gauge, pressure controller, vibration
Start building dress, bulb, vertical vibration platform, horizontal vibration platform installation pedestal, horizontal vibration platform, test bearing base composition,；On-hook is led
Bullet is mounted on hanger, and hanger is mounted on on-hook simulating boundary structural support by on-hook switching device；Side is simulated in on-hook
Boundary's structural support is mounted in air spring support system, and air spring support system is mounted on test bearing base；It hangs down
It is connected by bulb with vibration tool to shake table with horizontal vibration platform, vibration tool is used to fix on-hook guided missile.
Further, the air spring supports that system further includes air spring, upper junction plate, lower connecting plate, guiding limit
Position bar composition, wherein the upper junction plate and lower connecting plate are connect with on-hook simulating boundary structural support, lower connecting plate and
Bearing base connection is tested, air spring is mounted among upper junction plate and lower connecting plate, and air spring passes through tracheae and pressure
Controller connection.
A kind of large size guided missile on-hook vibration testing method, feature exist, comprising the following steps:
A carries out the simulation of on-hook border structure, designs on-hook simulating boundary structural support；
B designs free suspension system；
C carries out the test of guided missile hook state transmission characteristic, while carrying out key position response measurement, passes through test data point
Analysis, the transmission characteristic of acquisition；
D utilizes the transmission characteristic of hook state, and carrying out thrust estimation and full snap in conjunction with on-hook vibration test condition should divide
Analysis selects Optimum Excitation point position by optimizing, and determines required vertical vibration platform or horizontal vibration platform；
E is according to selected excitation point position, in conjunction with body external form, excitation orientation and excitational equipment parameters of structural dimension, if
Exciting tool structure form is counted, and utilizes finite element method (fem) analysis, the suitable exciting tooling of optimization；
F carries out playing inner sensor installation, and completes to detect, and guided missile is assembled；
G builds test bearing base；
H assembles large-scale guided missile on-hook vibration experiment, is fixed and is mounted on test bearing base；
I assembles guided missile and hanger, and then integral installation is on hanger switching device；
J installs sensor, and connecting test cable debugs acquisition system；
K carries out the calibration test of section dynamic bending moment；
L on-hook simulating boundary structural support and test bearing base disconnect, then air spring group is mounted on test and is held
It carries on pedestal, on-hook simulating boundary structural support is fallen on air spring, installs laser displacement gauge, air compressor is connected
Onto air spring, intermediate concatenation pressure controller, by adjusting pressure and displacement monitoring, adjustment structural support to suitable height
Degree；
M installation vibration tool simultaneously connects vertical vibration table and horizontal vibration platform, installs among vibration tool and shake table
Bulb；
The excitation control debugging of n shake table；
O selects control program, carries out small magnitude trial test, while carrying out data collection and analysis, and confirmation control program is
It is no to meet the requirements, if conditions are not met, adjustment control program, re-starts small magnitude trial test；
P carries out multistage loadings after meeting technical requirements, and until regulation tests magnitude, development formal test is carried out a small amount of
Grade token test, and carry out test data analyzer confirmation；
After q formal test, small magnitude token test is carried out, by Data Management Analysis, examines Product Status；
After the test, removal sensor and test equipment disconnect shake table excitation system and guided missile to r；Adjust air
Pressure removes guided missile and rack combination body so that structural support is fallen on test bearing base.
Beneficial effects of the present invention:
(1) present invention realizes the full bullet on-hook vibration test requirement of large-scale guided missile hook state, by really simulating,
Effectively examination guided missile fatigue resistance, guarantees the safety of machine on on-hook guided missile；
(2) present invention has carried out practical application in model experimental design, and test has for the first time carried out effectively extension overlap circle
Simulation increases the authenticity of ground experiment, and passes through the test energisation mode of multiple spot multi, realizes large-scale full bullet
Vibration respond control.
Detailed description of the invention
A kind of large-scale guided missile on-hook vibration rig front view of Fig. 1；
Wherein, 1 on-hook simulating boundary structural support, 2 hanger switching devices, 3 air spring support systems, 4 hangers, 5
On-hook guided missile, 6 air compressors, 7 laser displacement gauges, 8 pressure controllers, 9 vibration tools, 10 bulbs, 11 vertical vibration platforms, 12
Horizontal vibration platform installation pedestal, 13 horizontal vibration platforms, 14 test bearing bases, 15 tracheaes.
A kind of large-scale guided missile on-hook vibration rig top view of Fig. 2；
Wherein, 1 on-hook simulating boundary structural support, 4 hangers, 5 on-hook guided missiles, 7 laser displacement gauges, 8 pressure controllers,
9 vibration tongs, 10 bulbs, 11 vertical vibration platforms, 12 horizontal vibration platform installation pedestals, 13 horizontal vibration platforms.
The single air spring assembly schematic diagram of Fig. 3；
Wherein, 3-1 air spring, 3-2 upper junction plate, 3-4 lower connecting plate, 3-3 guide and limit bar.
A kind of large-scale guided missile on-hook vibration testing method flow chart of Fig. 4.
Specific embodiment
In addition to embodiment described below, the present invention can also have other embodiments or be implemented in different ways.Therefore,
It should be known that the invention is not limited to it is described in the following description or in the accompanying drawings shown in component structure it is detailed
Situation.When only introducing one embodiment here, claim is not limited to the embodiment.
Embodiment 1, with Fig. 1, for Fig. 2:
As seen from Figure 1, large-scale guided missile on-hook vibration rig is mainly turned by on-hook simulating boundary structural support, hanger
Connection device, air spring support system, hanger, on-hook guided missile, air compressor, laser displacement gauge, pressure controller, vibration work
Dress, bulb, vertical vibration platform, horizontal vibration platform installation pedestal, horizontal vibration platform, test bearing base composition.
On-hook guided missile is connect with hanger, and hanger is mounted on on-hook simulating boundary structural support by on-hook switching device
On；The on-hook simulating boundary structural support is mounted in air spring support system, the air spring support system peace
On test bearing base；Vertical vibration platform is connected by bulb with vibration tool with horizontal vibration platform.
Air spring support system is made of the equally distributed air spring assembly of multiple groups, in the present embodiment, testing equipment
An air spring support system is respectively arranged in left and right ends, and each air spring support system includes two air spring assemblies,
Each air spring assembly includes air spring, upper junction plate, lower connecting plate, guide and limit bar composition, wherein the upper connection
Plate and lower connecting plate are connect with on-hook simulating boundary structural support, and lower connecting plate is connect with test bearing base, air bullet
Spring is mounted among upper junction plate and lower connecting plate, and air spring is connect by tracheae with pressure controller.Guide and limit bar is used
In position limitation protection.
As seen from Figure 1, three impacting point positions are provided on the present embodiment bullet, each position is vertical and horizontal direction swashs
It encourages, i.e., the present embodiment includes three vertical vibration platforms and three horizontal vibration platforms, is vertically and horizontally being tested, this is
System is three points two axis；The present invention can change according to products characteristics, add and reduce the quantity of shake table, change vibration
The direction etc. of platform.
The present invention is mainly large-scale guided missile on-hook multiple spot multi-axes vibration test method.This method pass through first calculating analyze into
Then row on-hook boundary condition simulation is carried out exciting conceptual design using transmission characteristic test, and determines impacting point position and number,
Finally, determining the multiple spot multi-axis excitation control program of on-hook guided missile by trial test, the vibratory response of on-hook guided missile is realized
Real simulation.Its specific procedure and step are as follows:
A designs on-hook simulating boundary structural support；Using finite element technique, in conjunction with guided missile hook state modal test knot
Fruit carries out the simulation of on-hook border structure by the matched mode of modal parameter, designs on-hook simulating boundary structural support；
B calculates structural support and large-scale guided missile on-hook vibration experiment overall load weight, in conjunction with installation space position
It sets, freely suspend frequency requirement in midair, select air spring model, optimum air number springs N is determined by load weight calculating.Benefit
The mode uniformly carried with N number of air spring, combination pressure controller and laser displacement gauge design free suspension system；
C carries out the test of guided missile hook state transmission characteristic, using excitational equipment, is motivated in body key position, together
Shi Jinhang key position response measurement obtains transmission characteristic by test data analyzer；
D utilizes the transmission characteristic of hook state, and carrying out thrust estimation and full snap in conjunction with on-hook vibration test condition should divide
Analysis selects Optimum Excitation point position by optimizing, and determines required horizontal or vertical shake table；
E is according to selected excitation point position, in conjunction with body external form, excitation orientation and excitational equipment parameters of structural dimension, if
Exciting tool structure form is counted, and utilizes finite element method (fem) analysis, optimization exciting tooling；
F is according to mission requirements, before guided missile assembling, carries out playing inner sensor installation, and complete to detect；On-hook guided missile carries out
Assembling, after assembling, is transported to testing ground；
G builds test carrying base using large-scale ingot bar and drum beam according to the dimension and weight of guided missile and structural support
Seat；
H assembles large-scale guided missile on-hook vibration experiment, is fixed and is mounted on test bearing base；
I assembles on-hook guided missile with hanger, and then integral installation is on hanger switching device；
J installs sensor, and connecting test cable debugs acquisition system；
K installs foil gauge in body key sectional position, by way of load, carries out the calibration of section dynamic bending moment and surveys
Examination；
L on-hook model configuration supporting element and test bearing base disconnect, then air spring support system is mounted on test
On bearing base, on-hook model configuration supporting element is fallen on air spring, installs laser displacement gauge, air compressor is connected to
Air spring, centre concatenation pressure controller adjust on-hook simulating boundary structural support by adjusting pressure and displacement monitoring
To proper height；
M installs vibration tool in multiple excitation point positions that body is selected, by vibration tool and vertical vibration table and level
Shake table connection, installs bulb among vibration tool and vertical vibration table and horizontal vibration platform, is carried out using bulb non-actuated
Direction mobile decoupling, prevents shake table from interfering；
The sensor, such as acceleration transducer, gyroscope etc. that n will be used to control, are connected to vibration controller, controller
Output is connected to vibrating table amplifier, completes vertical vibration table and horizontal vibration platform excitation control debugging；
O selects control program, carries out small magnitude trial test according to the experimental condition of regulation, while carrying out vibratory response number
According to, such as acceleration, strain, angular speed data collection and analysis, confirm whether control program meets the requirements, if conditions are not met,
Control program is adjusted, small magnitude test is re-started；
P carries out multistage loadings after meeting technical requirements, and until regulation tests magnitude, development formal test is carried out a small amount of
Grade token test, and carry out test data analyzer confirmation；
After q formal test, small magnitude token test is carried out, by Data Management Analysis, examines Product Status.
After the test, removal sensor and test equipment disconnect shake table excitation system and guided missile to r；Adjust air
Pressure removes guided missile and rack combination body so that structural support is fallen on test bearing base, and vanning transports out of respectively, removes
Other test facilities, site clearing, off-test.
Claims (3)
1. a kind of large size guided missile on-hook vibration rig, by on-hook simulating boundary structural support (1), hanger switching device
(2), air spring support system (3), hanger (4), on-hook guided missile (5), air compressor (6), laser displacement gauge (7), pressure
Controller (8), vibration tool (9), bulb (10), vertical vibration platform (11), horizontal vibration platform installation pedestal (12), horizontal vibration
Platform (13), test bearing base (14) composition, which is characterized in that on-hook guided missile (5) is mounted on hanger (4), and hanger (4) passes through
On-hook switching device (2) is mounted on on-hook simulating boundary structural support (1)；On-hook simulating boundary structural support (1) peace
On air spring support system (3), air spring support system (3) is mounted in test bearing base (14)；Vertical vibration
Dynamic platform (11) are connect by bulb (10) with vibration tool (9) with horizontal vibration platform (13), and vibration tool (9) is used to fix on-hook
Guided missile (5).
2. a kind of large-scale guided missile on-hook vibration rig as described in claim 1, it is characterised in that the air spring branch
Hold system (3) further include air spring (3-1), upper junction plate (3-2), lower connecting plate (3-4), guide and limit bar (3-3) composition,
Wherein the upper junction plate (3-2) connect with on-hook simulating boundary structural support (1), and lower connecting plate (3-4) and test carry
Pedestal (14) connection, air spring (3-1) are mounted among upper junction plate (3-2) and lower connecting plate (3-4), air spring (3-
1) it is connect by tracheae (15) with pressure controller (8).
3. a kind of large size guided missile on-hook vibration testing method, feature exist, comprising the following steps:
A designs on-hook simulating boundary structural support；
B designs free suspension system；
C carries out the test of guided missile hook state transmission characteristic, while carrying out key position response measurement, obtains transmission characteristic；
D utilizes the transmission characteristic of hook state, carries out thrust estimation in conjunction with on-hook vibration test condition and plays response analysis entirely, leads to
Optimization is crossed to select Optimum Excitation point position, and determines required vertical vibration platform (11) and horizontal vibration platform (13)；
E is according to selected excitation point position, and in conjunction with body external form, excitation orientation and excitational equipment parameters of structural dimension, design swashs
Vibration tool structure form, and utilize finite element method (fem) analysis, optimization exciting tooling (9)；
F carries out playing inner sensor installation, and completes to detect, and on-hook guided missile (5) is assembled；
G builds test bearing base (14)；
H assembles large-scale guided missile on-hook vibration experiment, is fixed and is mounted in test bearing base (14)；
I assembles on-hook guided missile (5) and hanger (4), and then integral installation is on hanger switching device (2)；
J installs sensor, and connecting test cable debugs acquisition system；
K carries out the calibration test of section dynamic bending moment；
Air spring support system (3) is mounted in test bearing base (14) by l, on-hook simulating boundary structural support (1)
It falls in air spring support system (3), installs laser displacement gauge (7), air compressor is connected on air spring, centre string
It connects pressure controller (8), adjustment on-hook simulating boundary structural support (1) height；
M installs vibration tool (9), and vibration tool (9) is connect with vertical vibration table (11) and horizontal vibration platform (13)；
N vertical vibration table (11) and horizontal vibration platform (13) excitation control debugging；
O selects control program, carries out small magnitude trial test, while carrying out data collection and analysis, and whether confirmation control program is full
Foot requires, if conditions are not met, adjustment control program, re-starts small magnitude trial test；
P carries out multistage loadings after meeting technical requirements, and until regulation tests magnitude, it is special to carry out small magnitude for development formal test
Sign test, and carry out test data analyzer confirmation；
After q formal test, small magnitude token test is carried out, by Data Management Analysis, examines Product Status；
After the test, removal sensor and test equipment disconnect shake table excitation system and guided missile to r；Air pressure is adjusted,
So that structural support is fallen on test bearing base, guided missile and rack combination body are removed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710458403.4A CN107121254B (en) | 2017-06-16 | 2017-06-16 | A kind of large size guided missile on-hook vibration rig and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710458403.4A CN107121254B (en) | 2017-06-16 | 2017-06-16 | A kind of large size guided missile on-hook vibration rig and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107121254A CN107121254A (en) | 2017-09-01 |
| CN107121254B true CN107121254B (en) | 2019-04-16 |
Family
ID=59720009
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710458403.4A Active CN107121254B (en) | 2017-06-16 | 2017-06-16 | A kind of large size guided missile on-hook vibration rig and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107121254B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022078532A1 (en) * | 2020-10-12 | 2022-04-21 | České vysoké učení technické v Praze | A method and equipment for vibration testing of large and pliable components for their resilience to vibrations |
Families Citing this family (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107271129B (en) * | 2017-05-03 | 2019-03-12 | 北京航天控制仪器研究所 | A kind of vibration testing method of accurate power transmitting device |
| CN107902105B (en) * | 2017-09-27 | 2021-05-28 | 西北工业大学 | Apparatus and method for simulating reliability of airborne missile connection strength |
| CN107941442B (en) * | 2017-11-30 | 2023-08-29 | 北京强度环境研究所 | Vibration test device and method for performing vibration test on products |
| CN108731898B (en) * | 2018-04-18 | 2020-04-07 | 北京强度环境研究所 | Impact test device and method for performing impact test on product |
| CN108706107B (en) * | 2018-08-01 | 2024-02-20 | 中电科芜湖通用航空产业技术研究院有限公司 | Vibration test system of hybrid power device |
| CN109269750B (en) * | 2018-11-22 | 2024-03-12 | 苏州苏试试验集团股份有限公司 | Vibration test piece suspension installation device capable of being switched horizontally and vertically |
| CN110398335B (en) * | 2019-08-14 | 2024-06-07 | 天津航天瑞莱科技有限公司 | Test system for rotation superposition vibration of missile seeker |
| CN110895186B (en) * | 2019-11-28 | 2023-04-11 | 北京机电工程研究所 | Vibration system comprising a plurality of vibration tables and vibration test method |
| CN110895183B (en) * | 2019-11-28 | 2021-05-25 | 北京机电工程研究所 | A transfer device and test system in the vibration test of an aircraft externally mounted aircraft |
| CN111103109B (en) * | 2020-02-13 | 2024-11-05 | 中国工程物理研究院总体工程研究所 | Broadband torsional vibration test system |
| CN112577690A (en) * | 2020-08-20 | 2021-03-30 | 北京强度环境研究所 | Flexible supporting unit for missile hanging boundary |
| CN112393867B (en) * | 2020-12-14 | 2021-05-14 | 天津航天瑞莱科技有限公司 | Testing device for vibration test of aviation suspension launching device |
| CN112697368A (en) * | 2020-12-24 | 2021-04-23 | 彩虹无人机科技有限公司 | Missile mechanics environment test system |
| CN112936202B (en) * | 2021-03-26 | 2023-06-23 | 北京中科宇航技术有限公司 | Solid carrier rocket assembly trolley |
| CN113418670B (en) * | 2021-06-29 | 2022-12-13 | 上海机电工程研究所 | Vibration ejection separation test system |
| CN113959662B (en) * | 2021-09-22 | 2024-10-25 | 天津航天瑞莱科技有限公司 | A vibration test device for aircraft launch and separation |
| CN114112274A (en) * | 2021-11-05 | 2022-03-01 | 上海机电工程研究所 | Separation test device under random vibration ejection condition and installation test method thereof |
| CN114812992A (en) * | 2022-03-17 | 2022-07-29 | 上海航天精密机械研究所 | Vibration isolation and noise reduction vibration test equipment and method |
| CN115165280A (en) * | 2022-03-28 | 2022-10-11 | 北京强度环境研究所 | High-bearing anti-overturning triaxial vibration test device |
| CN114810889B (en) * | 2022-07-01 | 2022-10-14 | 中国飞机强度研究所 | High-bearing low-rigidity supporting device for aircraft vibration test |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100444657B1 (en) * | 2001-12-26 | 2004-08-30 | 한국항공우주연구원 | a |
| CN102494859A (en) * | 2011-11-15 | 2012-06-13 | 上海卫星工程研究所 | Fixed frequency calibration test method of spacecraft vibration |
| CN203858085U (en) * | 2014-05-29 | 2014-10-01 | 北京强度环境研究所 | Platform three-axis flight vibration time domain waveform reproducing system |
| CN205002948U (en) * | 2015-07-16 | 2016-01-27 | 北京强度环境研究所 | Large -scale structural vibration attribute testing pulse excitation device |
| CN106053000A (en) * | 2016-07-15 | 2016-10-26 | 北京强度环境研究所 | Missile and carrier rocket modal test method |
| CN106768771A (en) * | 2017-03-14 | 2017-05-31 | 北京强度环境研究所 | A kind of vibration testing device |
-
2017
- 2017-06-16 CN CN201710458403.4A patent/CN107121254B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100444657B1 (en) * | 2001-12-26 | 2004-08-30 | 한국항공우주연구원 | a |
| CN102494859A (en) * | 2011-11-15 | 2012-06-13 | 上海卫星工程研究所 | Fixed frequency calibration test method of spacecraft vibration |
| CN203858085U (en) * | 2014-05-29 | 2014-10-01 | 北京强度环境研究所 | Platform three-axis flight vibration time domain waveform reproducing system |
| CN205002948U (en) * | 2015-07-16 | 2016-01-27 | 北京强度环境研究所 | Large -scale structural vibration attribute testing pulse excitation device |
| CN106053000A (en) * | 2016-07-15 | 2016-10-26 | 北京强度环境研究所 | Missile and carrier rocket modal test method |
| CN106768771A (en) * | 2017-03-14 | 2017-05-31 | 北京强度环境研究所 | A kind of vibration testing device |
Non-Patent Citations (1)
| Title |
|---|
| "弹架系统振动响应特性测试";傅博等;《航空兵器》;20160630(第3期);第63页 |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022078532A1 (en) * | 2020-10-12 | 2022-04-21 | České vysoké učení technické v Praze | A method and equipment for vibration testing of large and pliable components for their resilience to vibrations |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107121254A (en) | 2017-09-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107121254B (en) | A kind of large size guided missile on-hook vibration rig and method | |
| CN105083588B (en) | A kind of many rotor unmanned aircraft Testing Platforms and method | |
| CN108001713B (en) | On-orbit separation ground test device and detection method for double-star combined spacecraft | |
| CN112179595B (en) | Helicopter body fairing vibration fatigue test verification method | |
| CN110542525B (en) | Method for testing vibration fatigue performance of metal in axial resonance state | |
| JP2014016339A5 (en) | ||
| CN107239630B (en) | A support system for vibration test of airborne external pendant and its design method | |
| CN110207963B (en) | Free-free boundary simulation device for air spring elastic support vertical structure | |
| CN103984241A (en) | Small unmanned helicopter test stand and test simulation method | |
| CN106092474A (en) | A kind of wing hanging engine vibration-damping STS system test set | |
| CN111380427A (en) | Missile full-missile double-station parallel excitation reliability test method and system based on comprehensive stress | |
| CN110344966B (en) | Device and method for constructing free boundary of solid rocket ground test | |
| CN106768771A (en) | A kind of vibration testing device | |
| CN106052999B (en) | Extra-high voltage direct current composite wall bushing outer surface anti-seismic test device and test method | |
| CN106527178B (en) | A kind of super-large dimension flexible spacecraft ground physical emulation test system | |
| Luczak et al. | Identification of the test setup influence on the modal properties of a short wind turbine blade during fatigue test | |
| CN112729734B (en) | Method for measuring transfer characteristics of series-type vibration isolator | |
| CN106052996B (en) | Extra-high voltage direct current composite wall bushing anti-seismic test device and test method | |
| CN106768792B (en) | A method of carrying out rotor model testing stand dynamic balancing adjustment | |
| Skorupka | Laboratory investigations on landing gear ground reactions (load) measurement | |
| Hamade et al. | Modal analysis of UH-60A instrumented rotor blades | |
| CN106153284B (en) | An integrated device for loading and spectral control of the entire cabin-level explosion shock test | |
| CN107044913A (en) | A kind of engine inertia parameter identification device and method | |
| CN113310695B (en) | Aircraft engine windmill load ground simulation method and system | |
| Füllekrug et al. | Identification of modal parameters, generalized and effective masses during base-driven tests |
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 |