CN106441826A - Simulation method used for satellite high-precision load ground weightlessness - Google Patents
Simulation method used for satellite high-precision load ground weightlessness Download PDFInfo
- Publication number
- CN106441826A CN106441826A CN201610538568.8A CN201610538568A CN106441826A CN 106441826 A CN106441826 A CN 106441826A CN 201610538568 A CN201610538568 A CN 201610538568A CN 106441826 A CN106441826 A CN 106441826A
- Authority
- CN
- China
- Prior art keywords
- satellite
- load
- weightlessness
- suspension
- analogy method
- 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
- 238000000034 method Methods 0.000 title claims abstract description 26
- 238000004088 simulation Methods 0.000 title abstract description 4
- 238000002955 isolation Methods 0.000 claims abstract description 19
- 239000000725 suspension Substances 0.000 claims description 47
- 238000012544 monitoring process Methods 0.000 claims description 3
- 238000012360 testing method Methods 0.000 description 14
- 230000005486 microgravity Effects 0.000 description 6
- 230000001629 suppression Effects 0.000 description 6
- 230000008878 coupling Effects 0.000 description 4
- 238000010168 coupling process Methods 0.000 description 4
- 238000005859 coupling reaction Methods 0.000 description 4
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000001228 spectrum Methods 0.000 description 3
- 240000002853 Nelumbo nucifera Species 0.000 description 2
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 2
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000003384 imaging method Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000006866 deterioration Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000003287 optical effect 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
- G01M13/00—Testing of machine parts
-
- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/008—Subject matter not provided for in other groups of this subclass by doing functionality tests
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Control And Safety Of Cranes (AREA)
Abstract
The present invention discloses a simulation method used for satellite high-precision load ground weightlessness. The method comprises the steps of 1 adjusting the attitude of a satellite; 2 unlocking a vibration isolation device; 3 unloading the head of a load photoelectric precision machine; 4 suspending the satellite flexibly; 5 adjusting the satellite horizontally; 6 statically placing the satellite; 7 readjusting the satellite horizontally; 8 readjusting the unloading force of the head of the load photoelectric precision machine.
Description
Technical field
The present invention relates to satellite fields, particularly to the analogy method of satellite load ground weightlessness.
Background technology
Micro-vibration refer in spacecraft running because movable part rotates or space alternating hot and cold caused by wideband, low
The vibration of intensity, typically will not cause structural deterioration but impact payload work.For guaranteeing the high accuracy such as optical camera effectively
The imaging precision of load, installs isolation mounting to suppress micro-vibration generally between payload light chain-drive section and satellite body.
For verifying the performance of isolation mounting, need satellite operation on orbit state, that is, need analog satellite body and load respectively
The microgravity state of lotus light chain-drive section, is only connected by isolation mounting between the two.Existing Bubble-floating Method, suspension method, balloon method
Above-mentioned requirements all cannot be met Deng microgravity state analogy method.Therefore, this paper presents a kind of brand-new satellite high-precision carries
Lotus ground weightlessness analogy method.
Content of the invention
The problem that the present invention solves is that existing microgravity state analogy method is not suitable for analog satellite body and load
The microgravity state of light chain-drive section；For solving described problem, the present invention provides a kind of simulation of satellite load ground weightlessness
Method.
The analogy method of the satellite load ground weightlessness that the present invention provides, including：Step one, the adjustment attitude of satellite；
Step 2, unblock isolation mounting；Step 3, unloading load light chain-drive section；Step 4, flexible suspention satellite；Step 5, level are adjusted
Section satellite；Step 6, standing satellite；Step 7, horizontal polyphony satellite；Step 8, polyphony load light chain-drive section unloading force.
Further, described step one includes adjusting the attitude of satellite to payload isolation mounting towards perpendicular using machinery
Straight state upwards.Refer to isolation mounting straight up and be connected with satellite face up, axis is perpendicular to horizontal plane.
Further, described step 2 includes：Release the fixed constraint between load light chain-drive section and satellite body, make load
Light chain-drive section is only connected by isolation mounting with satellite body.
Further, described step 3 includes：Unload load light chain-drive section, each suspension centre by the way of truss hangs unloading
Suspension force determined according to the weight of load light chain-drive section, barycenter and hoisting point position, each suspension centre is adjusted using chain block
Suspension force, using stretch cord as lifting rope, stretch cord connects force transducer and is used for suspension force monitors.
Further, described step 4 includes：Using driving, satellite is lifted by crane, the suspension force of each suspension centre is according to load ray machine
The weight of head, barycenter and hoisting point position determine, using stretch cord as lifting rope, stretch cord connects force transducer and is used for suspension force
Monitoring, is simultaneously connected with flower basket bolt；After satellite lifting, distance parks more than frock 200mm.
Further, described step 5 includes：Satellite horizontal adjustment to realize the fine setting of satellite levelness using flower basket bolt, makes
Levelness is better than 0.1 °.
Further, described step 6 time of repose is 30min.
Further, described step 7 includes using using flower basket bolt, satellite levelness being finely tuned, and makes satellite levelness excellent
In 0.1 °.
Further, described step 8 includes finely tuning suspension force using chain block, makes suspension force reach step 3 sensing
The measured value of device.
Advantages of the present invention includes：
(1) simulation of multiple satellite microgravity states can, be realized, including isolation mounting released state and non-unblock shape
State；
(2), versatility is good, is not limited by the suspension centre quantity of test product, hoisting point position and product centroid position；
(3), can achieve the suspention of test product self-balancing, higher levelness can be obtained by fine setting.
(4), suspension system natural frequency is low, can effectively completely cut off extraneous vibration source impact, and suspended state is stable.
(5), easy to operate, safe and reliable.
Brief description
Fig. 1 is infrared high spectrum barycenter and hoisting point position relation schematic diagram；
Fig. 2 is the suspention interface of whole star and its simplifies diagram；
Fig. 3 (a) is load Vibration Condition before vibration isolation, and Fig. 3 (b) is load Vibration Condition after vibration isolation.
Specific embodiment
Taking the flexible double suspention operating modes in the test of certain model satellite micro-vibration as a example describe flexible double suspention system below in detail
The application of system.
1 micro-vibration Introduction of The Experiment
The load more sensitive to micro-vibration is provided with certain model satellite, for guaranteeing the on-orbit performance of load, special for it
Door have developed micro-vibration suppression subsystem, in order to obtain whole star micro-vibration environment, checking micro-vibration suppression system performance, needs to carry out
Whole star micro-vibration test.
Micro-vibration suppression subsystem can be divided into micro-vibration isolation mounting (vibration isolator) and micro-vibration tripper by composition.Every
Vibrating device has 4 groups, and tripper has 6 groups, is distributed in on floor, load light chain-drive section passes through isolation mounting and unblock dress
Put and be connected with celestial body.Impaction state (powered phase) and released state (in-orbit section) can be divided into by its working condition.Impaction state is：
Micro-vibration suppression subsystem is connected by six compression points and four vibration isolators between floor and survey meter, wherein vibration isolator
In impaction state, vibration isolator is unlocked compression force compresses 2mm of bolt.Released state is：Micro-vibration suppression subsystem with over the ground
Pass through four vibration isolators between plate and survey meter to connect, six compression point release screw bolts unblocks, vibration isolator discharges completely, load with
Celestial body is connected by vibration isolator.
Satellite in orbit after, load unlocks, and vibration isolator discharges, and star is used for the flywheel of posture adjustment and other moving components
Rotation enantiomorph produce micro-vibration environment, the pointing accuracy of load is impacted and then video imaging quality, vibration isolator
Effect is by the isolation of the micro-vibration environment of celestial body it is ensured that the pointing accuracy of load.Need in the flexible double suspention operating modes of micro-vibration test
Satellite is carried out gravity unloading, runs with moving component start on clock star and micro-vibration environment is produced to whole star, by load solution
Need to provide microgravity ring to load after the unblock of the anti-vibration performance of the vibration environment comparison test vibration isolator before and after lock, wherein load
Border.The natural frequency of vibration isolator is 15Hz, in order to ensure whole star and load flexibility suspension system to the anti-vibration performance of vibration isolator not
Produce impact it is desirable to the fundamental frequency≤0.5Hz of flexible suspension system.
2 flexible double suspension systems are set up
2.1 load flexibility suspension systems are set up
According to knowable to payload interface data, the position relationship between its barycenter and load point of suspension is as shown in Fig. 1, table 1.M2
For infrared high spectrum barycenter, E, F, G, H are four load point of suspension.
Table 1 infrared high spectrum barycenter and hoisting point position relation data
Position relationship according to load weight, barycenter and point of suspension can obtain shown in its equilibrium equation such as above formula (1),
Because 4 points are suspended in midair, between each point of suspension of load, the coupling of power has or not array solution, according to above-mentioned matching principle, chooses flexible strand
Bearing area is [20Kg, 22Kg] (ensureing flexible suspention fundamental frequency), can obtain carrying match parameter such as table 2 institute of the flexible suspention of load
Show：
The bearing capacity coupling of table 2 load point of suspension and flexible strand bearing point matching result
According to above matching result, choose the flexible strand of respective amount, build load flexibility suspension system.Wherein weigh biography
Sensor range is 100kg, and certainty of measurement is better than 50g；Flexible strand length adjustment device selects bottle gouard moved by hands, and bottle gouard moved by hands can be
Elongation height arbitrarily being adjusted in 2.5 meters of stroke range, and single-point carrying >=100kg, arbitrarily can adjust in the range of stroke
Load flexible strand length at corresponding suspension centre.Flexible strand is arranged on corresponding bearing point, four groups of bottle gouards moved by hands stretch together,
Be stretched to load apart from ground 1m about stop, the adjustable height individually adjusting each bottle gouard moved by hands, to load level, uses water
Level tests its levelness, measures each point of suspension force value again after standing 30min, and adjustment flexible strand elongation is to load-carrying water again
Flat.Test data is as shown in table 3 below.
Table 3 load flexibility suspension system experimental test data
2.2 whole star flexibility suspension systems are set up
The suspention interface of whole star and its simplification diagram are as shown in Fig. 2 set up whole star on the basis of the geometric center of technique ring
Coordinate system, according to whole star mass property test result, the center-of-mass coordinate of satellite is：(1688.0,19.527,53.53), satellite
Quality 2318.1Kg.Bearing point is as follows in (X, Y) direction coordinate：H (120,1035), I (1504,1035), J (3219,1035),
M (3219, -1035), L (1504, -1035), K (120, -1035).
Whole star is 6 points of liftings, and wherein free variable has 3, can obtain unique solution in order to ensure carrying coupling, whole star is flexible
Using the symmetrical structural advantage of whole star point of suspension so that the suspension force of the whole star point of suspension left and right sides is full in rope matching process
Enough to the proportional relation of barycenter, that is,：H/M=I/L=J/K=(XM-XBarycenter)/(XBarycenter-XH).
The bearing area choosing flexible strand is [20Kg, 22Kg], can obtain the carrying match parameter such as table 4 of the flexible suspention of whole star
Shown
The flexible suspention of the whole star of table 4 carries matching result
According to above matching result, choose the flexible strand of respective amount, build whole star flexibility suspension system.Wherein weigh biography
Sensor range is 1000kg, and certainty of measurement is better than 0.5kg；Flexible strand length adjustment device selects flower basket bolt, and flower basket bolt can
Flexible strand elongation is arbitrarily adjusted in 0.5 meter of stroke range.Using driving, whole star is lifted to apart from horizontal support face height
Stop at about 400mm, then adjust whole star levelness, after standing 30min, measure each point of suspension force value again, adjust flexible again
Rope elongation amount is to satellite level.Test data is as shown in table 5 below.
Table 5 whole star flexibility suspension force test data
2.3 micro-vibration tests
Above-mentioned whole star and load flexibility suspension system coupling finish after will load flexibility suspension system and whole star flexible outstanding
Relative position relation between crane system is adjusted in place, and first carries load according to each point of suspension after table 3 leveling and carries out gravity
Unloading, whole star double hook lifting certain altitude (not less than 400mm) according to table 5 in midair whole star is respectively suspended with unloading force value and adjust afterwards
Whole, it is adjusted according still further to each point of suspension unloading value force value of table 3.Then according to micro-vibration test requirements document is tested, before unblock
The Vibration Condition of load is as shown in Figure 3 afterwards.By contrast, micro-vibration subsystem has all played good micro-vibration suppression and has made
With wherein Fig. 3 (a) is load Vibration Condition before vibration isolation, and Fig. 3 (b) is load Vibration Condition after vibration isolation.
Although the present invention is open as above with preferred embodiment, it is not for limiting the present invention, any this area
Without departing from the spirit and scope of the present invention, the methods and techniques content that may be by the disclosure above is to this for technical staff
Bright technical scheme makes possible variation and modification, and therefore, every content without departing from technical solution of the present invention, according to the present invention
Technical spirit any simple modification, equivalent variations and modification that above example is made, belong to technical solution of the present invention
Protection domain.
Claims (9)
1. the analogy method of satellite load ground weightlessness is it is characterised in that include：Step one, the adjustment attitude of satellite；Step
2nd, unlock isolation mounting；Step 3, unloading load light chain-drive section；Step 4, flexible suspention satellite；Step 5, horizontal adjustment are defended
Star；Step 6, standing satellite；Step 7, horizontal polyphony satellite；Step 8, polyphony load light chain-drive section unloading force.
2. according to the satellite load ground weightlessness described in claim 1 analogy method it is characterised in that described step one
Including using machinery, the attitude of satellite is adjusted to payload isolation mounting towards state straight up.
3. according to the satellite load ground weightlessness described in claim 1 analogy method it is characterised in that described step 2
Including：Release the fixed constraint between load light chain-drive section and satellite body, so that load light chain-drive section is only passed through with satellite body
Isolation mounting connects.
4. according to the satellite load ground weightlessness described in claim 1 analogy method it is characterised in that described step 3
Including：Unload load light chain-drive section by the way of truss hangs unloading, the suspension force of each suspension centre is according to load light chain-drive section
Weight, barycenter and hoisting point position determine, to adjust the suspension force of each suspension centre using chain block, using stretch cord as hanging
Rope, stretch cord connects force transducer and is used for suspension force monitoring.
5. according to the satellite load ground weightlessness described in claim 1 analogy method it is characterised in that described step 4
Including：Using driving, satellite is lifted by crane, the suspension force of each suspension centre is according to the weight of load light chain-drive section, barycenter and hoisting point position
Determine, using stretch cord as lifting rope, stretch cord connects force transducer and is used for suspension force monitoring, is simultaneously connected with flower basket bolt；Defend
After star lifting, distance parks more than frock 200mm.
6. according to the satellite load ground weightlessness described in claim 1 analogy method it is characterised in that described step 5
Including：Satellite horizontal adjustment to realize the fine setting of satellite levelness using flower basket bolt, makes levelness be better than 0.1 °.
7. according to the satellite load ground weightlessness described in claim 1 analogy method it is characterised in that described step 6
Time of repose is 30min.
8. according to the satellite load ground weightlessness described in claim 1 analogy method it is characterised in that described step 7
Including using using flower basket bolt, satellite levelness is finely tuned, make satellite levelness be better than 0.1 °.
9. according to the satellite load ground weightlessness described in claim 4 analogy method it is characterised in that described step 8
To finely tune suspension force including using chain block, to make suspension force reach the measured value of step 3 sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610538568.8A CN106441826B (en) | 2016-07-11 | 2016-07-11 | A kind of analogy method for satellite high-precision load ground state of weightlessness |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610538568.8A CN106441826B (en) | 2016-07-11 | 2016-07-11 | A kind of analogy method for satellite high-precision load ground state of weightlessness |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106441826A true CN106441826A (en) | 2017-02-22 |
| CN106441826B CN106441826B (en) | 2019-03-29 |
Family
ID=58183378
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610538568.8A Expired - Fee Related CN106441826B (en) | 2016-07-11 | 2016-07-11 | A kind of analogy method for satellite high-precision load ground state of weightlessness |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106441826B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107255570A (en) * | 2017-05-18 | 2017-10-17 | 上海卫星工程研究所 | It is suitable for the attitude adjusting method of big part turnover type expansion experiment |
| CN108918115A (en) * | 2018-06-05 | 2018-11-30 | 杭州市特种设备检测研究院 | Bridge crane no-load load testing machine and method |
| CN110803306A (en) * | 2019-12-06 | 2020-02-18 | 北京空间技术研制试验中心 | Passive vibration isolation device for spacecraft control moment gyro cluster |
| WO2023029148A1 (en) * | 2021-09-06 | 2023-03-09 | 北京空间机电研究所 | Height-adjustable spacecraft storage tank simulated loading static experiment device and method |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS63179228A (en) * | 1987-01-20 | 1988-07-23 | Mitsubishi Heavy Ind Ltd | Exciting device for spatial structure |
| JP2007292644A (en) * | 2006-04-26 | 2007-11-08 | Japan Aerospace Exploration Agency | Device and method for automatically selecting forecasting approach for random vibration of panel |
| CN102520719A (en) * | 2011-12-06 | 2012-06-27 | 北京邮电大学 | Microgravity air floatation target satellite simulator system with five degrees of freedom |
| CN102650563A (en) * | 2011-12-20 | 2012-08-29 | 北京卫星环境工程研究所 | Ground testing system for on-track micro vibration of spacecraft |
| CN103482088A (en) * | 2013-08-12 | 2014-01-01 | 上海卫星工程研究所 | Satellite micro-vibration test multi-point suspension system and design method thereof |
| CN103712759A (en) * | 2014-01-06 | 2014-04-09 | 北京卫星环境工程研究所 | Spacecraft whole-satellite micro-vibration mechanics environment ground test method |
| CN104280229A (en) * | 2014-09-17 | 2015-01-14 | 上海卫星工程研究所 | Unlocking test method of vibration isolation system |
| CN105530514A (en) * | 2016-01-28 | 2016-04-27 | 长光卫星技术有限公司 | Testing device for affect of satellite platform micro-vibration on camera imaging |
| CN105551366A (en) * | 2015-12-16 | 2016-05-04 | 北京精密机电控制设备研究所 | Ground microgravity equivalent experimental device and method of six-freedom-degree spatial mechanical arm |
-
2016
- 2016-07-11 CN CN201610538568.8A patent/CN106441826B/en not_active Expired - Fee Related
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS63179228A (en) * | 1987-01-20 | 1988-07-23 | Mitsubishi Heavy Ind Ltd | Exciting device for spatial structure |
| JP2007292644A (en) * | 2006-04-26 | 2007-11-08 | Japan Aerospace Exploration Agency | Device and method for automatically selecting forecasting approach for random vibration of panel |
| CN102520719A (en) * | 2011-12-06 | 2012-06-27 | 北京邮电大学 | Microgravity air floatation target satellite simulator system with five degrees of freedom |
| CN102650563A (en) * | 2011-12-20 | 2012-08-29 | 北京卫星环境工程研究所 | Ground testing system for on-track micro vibration of spacecraft |
| CN103482088A (en) * | 2013-08-12 | 2014-01-01 | 上海卫星工程研究所 | Satellite micro-vibration test multi-point suspension system and design method thereof |
| CN103712759A (en) * | 2014-01-06 | 2014-04-09 | 北京卫星环境工程研究所 | Spacecraft whole-satellite micro-vibration mechanics environment ground test method |
| CN104280229A (en) * | 2014-09-17 | 2015-01-14 | 上海卫星工程研究所 | Unlocking test method of vibration isolation system |
| CN105551366A (en) * | 2015-12-16 | 2016-05-04 | 北京精密机电控制设备研究所 | Ground microgravity equivalent experimental device and method of six-freedom-degree spatial mechanical arm |
| CN105530514A (en) * | 2016-01-28 | 2016-04-27 | 长光卫星技术有限公司 | Testing device for affect of satellite platform micro-vibration on camera imaging |
Non-Patent Citations (1)
| Title |
|---|
| 程世祥等: ""卫星周期桁架结构振动特性应用研究"", 《噪声与振动控制》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107255570A (en) * | 2017-05-18 | 2017-10-17 | 上海卫星工程研究所 | It is suitable for the attitude adjusting method of big part turnover type expansion experiment |
| CN108918115A (en) * | 2018-06-05 | 2018-11-30 | 杭州市特种设备检测研究院 | Bridge crane no-load load testing machine and method |
| CN110803306A (en) * | 2019-12-06 | 2020-02-18 | 北京空间技术研制试验中心 | Passive vibration isolation device for spacecraft control moment gyro cluster |
| CN110803306B (en) * | 2019-12-06 | 2021-06-18 | 北京空间技术研制试验中心 | Passive vibration isolation device for spacecraft control moment gyro cluster |
| WO2023029148A1 (en) * | 2021-09-06 | 2023-03-09 | 北京空间机电研究所 | Height-adjustable spacecraft storage tank simulated loading static experiment device and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106441826B (en) | 2019-03-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106441826A (en) | Simulation method used for satellite high-precision load ground weightlessness | |
| Durda et al. | Experimental determination of the coefficient of restitution for meter-scale granite spheres | |
| Li et al. | Micro-vibration suppression methods and key technologies for high-precision space optical instruments | |
| CN104931219B (en) | A kind of landing shock experimental rig and its test method | |
| CN106516181B (en) | Big carrying Low-rigidity suspension system for the in-orbit weightlessness simulation of spacecraft | |
| CN106477074B (en) | A kind of in-orbit super quiet weightlessness simulation experiment system of novel spacecraft | |
| EA022224B1 (en) | Stabilization system for sensors on moving platforms | |
| CN107782536A (en) | A kind of multi-level micro-vibration system test method and system | |
| CN103616151A (en) | Spacecraft landing impact testing system in clean environment and testing method | |
| Pappa et al. | Structural dynamics experimental activities in ultralightweight and inflatable space structures | |
| CN108001713A (en) | Double star assembly spacecraft is in-orbit discretely to interview experiment device and detection method | |
| CN110344966B (en) | Device and method for constructing free boundary of solid rocket ground test | |
| CN105204541B (en) | A kind of high-precision Stewart Active Vibration Isolation Platforms | |
| CN109606732A (en) | A kind of efficient Aircraft Quality characteristic measurement method | |
| CN108897239A (en) | A kind of spacecraft two-stage gesture stability simulation system | |
| Israr | Vibration and modal analysis of low earth orbit satellite | |
| EP1509757B1 (en) | Device for measuring the inertia tensor of a rigid body | |
| CN104016232B (en) | Dynamic weighing mechanism for lifting device | |
| CN108011585A (en) | The mechanical resistance detection method and system of a kind of photovoltaic module | |
| CN110793793A (en) | Ground unfolding test system of large-scale load platform | |
| TW201321623A (en) | Pneumatic vibration damping apparatus | |
| CN107246862B (en) | Gravity balance method for ground test of heavy satellite-borne deployable antenna | |
| CA2303059C (en) | Apparatus for reducing rotation of an article | |
| CN107036802A (en) | A kind of shock absorber overloading-vibrating environment pilot system and test method | |
| Fan et al. | Design of zero-gravity unloading process equipment for satellite overlapping antenna on ground test |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190329 |