CN106763411A - A kind of isolation mounting for the in-orbit weightlessness simulation of spacecraft - Google Patents
A kind of isolation mounting for the in-orbit weightlessness simulation of spacecraft Download PDFInfo
- Publication number
- CN106763411A CN106763411A CN201610986347.7A CN201610986347A CN106763411A CN 106763411 A CN106763411 A CN 106763411A CN 201610986347 A CN201610986347 A CN 201610986347A CN 106763411 A CN106763411 A CN 106763411A
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- China
- Prior art keywords
- vibration
- spacecraft
- simulation
- orbit
- isolation mounting
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/02—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using gas only or vacuum
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/02—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using gas only or vacuum
- F16F9/04—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using gas only or vacuum in a chamber with a flexible wall
Abstract
The invention provides a kind of isolation mounting for the in-orbit weightlessness simulation of spacecraft, vibration interference for being transferred to spacecraft for in-orbit super quiet weightless micro-vibration laboratory isolation ground, including vibration-isolating platform and some air cushion shock absorbers, the air cushion shock absorber is evenly arranged and is supported between vibration-isolating platform and laboratory's ground.Isolation mounting of the present invention, structural strength is high, rigidity is big, bearing capacity is strong, isolation vibration interference ability is strong, solves the technological difficulties of the vibration-isolating platform design of in-orbit weightlessness simulation, and low cost of manufacture, strong applicability achieve good economic benefits.
Description
Technical field
The present invention relates to a kind of isolation mounting for the simulation of spacecraft in-orbit weightlessness, micro- in particular for spacecraft
The big carrying isolation mounting of vibration test test.
Background technology
During micro-vibration refers to spacecraft in orbit, rotatable parts high-speed rotation, large-scale controllable member driving mechanism on star
Thruster ignition operation, large-size pliable structure turnover shade alternating hot and cold induce disturbance etc. all during step motion, change rail posture adjustment
The shaking response that can produce celestial body.All there is micro-vibration disturbing source in most of spacecrafts.Due to micro-vibration mechanical environment effect
Amplitude is small, most of satellite borne equipment will not be produced and significantly affected, and is generally omitted.But it is micro- to shake to high accuracy remote sensing satellite
Dynamic disturbance will have a strong impact on the important performance indexes such as its pointing accuracy, stability and resolution ratio.
Satellite platform is subject to the adjustment of attitude momenttum wheel, thruster posture adjustment, solar array adjustment, the work of camera scanning mechanism etc.
The single or comprehensive function of vibration source is disturbed, spacecraft can be caused to produce misoperation to the system of micro-vibration environment sensitive, it is this micro- to shake
Dynamic kinetic energy is small, bandwidth, and attitude control system is difficult observing and controlling, and can cause composition space camera structure and optical system
The Light deformation of each inside parts or micro-displacement each other, influence image quality.If certain model satellite momentum wheel is in electricity
The microvibration caused during survey, it is with causing satellite quick operationally to generate saltus step, so as to be generated to its service behaviour
Serious influence.Certain model finds when infrared camera and CCD camera are imaged jointly, when infrared camera is imaged in ground test
Sweeping mirror rotates the low frequency for causing and disturbs and shakes, and by celestial body structure Coupling to CCD camera, CCD camera is put mirror and produces mechanical oscillation,
Have impact on CCD camera image quality.Therefore, the high precision measurement technical need for micro-vibration environment is also more and more urgent.For
Realize the in-orbit weightlessness simulation of spacecraft, complete micro-vibration high precision measurement, design it is a kind of it is big carry vibration-isolating platform, micro-
During vibration-testing, ground is transferred to the vibration interference of spacecraft, sets up clamped experimental technique state, by extraneous vibration to surveying
The vibration interference of test system is reduced to minimum level, so that what the moving component of accurate measurement spacecraft body was operationally produced
Micro-vibration.
The content of the invention
It is an object of the invention to provide a kind of isolation mounting for the in-orbit weightlessness simulation of spacecraft, micro-vibration is solved
Ground vibration interference problem of transmission in test process, realizes the in-orbit weightlessness ground experiment simulation of spacecraft, while in isolation
In the case that ground vibration is disturbed, it is ensured that the rigidity of vibration-isolating platform, intensity, bearing capacity and intrinsic frequency, more accurately enter
The in-orbit weightless micro-vibration environmental simulation of row.
The present invention is for the solution technical scheme that is used of its technical problem：
A kind of isolation mounting for the in-orbit weightlessness simulation of spacecraft, for being in-orbit super quiet weightless micro-vibration experiment
Room isolation ground is transferred to the vibration interference of spacecraft, including vibration-isolating platform and some air cushion shock absorbers, the air bullet
Spring vibration isolator is evenly arranged and is supported between vibration-isolating platform and laboratory's ground.
The vibration-isolating platform vertical direction intrinsic frequency is 1.5Hz, meets the clamped test specification of spacecraft.
Each air cushion shock absorber sets an external Auxiliary Damping air bag of 100L, it is ensured that the stabilization of intrinsic frequency.
Balloon thickness is 1.5mm, prevents microvibration from passing through air bag this body structure transmission.
To ensure vibration-isolating platform certainty of measurement and stability, air spring impulse stroke is less than 10mm.
The vibration-isolating platform ensures smooth, steel plate thickness 8mm using punching block.
It is smooth to ensure ground, concrete cover is equipped with, thickness is 20mm, and adds epoxide terrace.
Level tune valve is also equipped with, when the load on vibration-isolating platform is changed, level is automatically adjusted.
Can raise vibration-isolating platform after air cushion shock absorber inflation, so as to be separated with laboratory ground.
The beneficial effects of the invention are as follows：Ground vibration interference problem of transmission in micro-vibration test process is solved, boat is realized
The in-orbit weightlessness ground experiment simulation of its device, while meeting, vibration insulation structure intensity is high, rigidity is big, bearing capacity is strong, isolation
Vibration interference ability strong demand.Vibration isolation uses air cushion shock absorber and vibration-isolating platform structure type, vibration isolation greatly improved and puts down
The vibration isolating effect of the vibration interference of platform so that the intrinsic frequency of vibration-isolating platform is less than 1.5Hz, substantially increases micro-vibration test
High accuracy and stability.
Brief description of the drawings
The detailed description made to non-limiting example with reference to the following drawings by reading, further feature of the invention,
Objects and advantages will become more apparent upon：
Fig. 1 is isolation mounting schematic diagram of the present invention；
Fig. 2 is air cushion shock absorber schematic layout pattern.
Specific 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 to the ordinary skill of this area
For personnel, without departing from the inventive concept of the premise, some changes and improvements can also be made.These belong to the present invention
Protection domain.
Shown in Fig. 1, Fig. 2, provided by the present invention for the isolation mounting of the in-orbit weightlessness simulation of spacecraft, mainly anti-
The sandstone ground that shakes is placed in melt pit, and size is set on the melt pit of 12.6m × 9.6m × 0.9m, to build 10m on basic blocks top
The large-scale vibration-isolating platforms of × 8m × 1.8m, for being transferred to shaking for spacecraft for in-orbit super quiet weightless micro-vibration laboratory isolation ground
Dynamic interference, the isolation mounting intrinsic frequency is 1.5Hz, meets the clamped test specification of spacecraft.Structure of the present invention by
Air cushion shock absorber 3 is put in the decentralization of large-scale vibration-isolating platform 2, and vibration isolation treatment is carried out to whole platform, and the vibration of measuring system is done
Disturb and be reduced to minimum level structure using diaphragm type vibration isolation form, sandstone ground is connected by uniform 16 air cushion shock absorbers 3
Hole and vibration-isolating platform.In order to increase rigidity, the structure of steel die that vibration-isolating platform is welded using reinforcing bar and shaped steel combination, then pour coagulation
Soil.Vibration-isolating platform quality is 170000Kg, and bearing capacity is 30000Kg.In order to ensure vibration-isolating platform certainty of measurement and stability,
Air spring impulse stroke is less than 10mm.Air spring uses dual chamber structure, and balloon thickness 1.5mm prevents microvibration from leading to
Cross air bag and pass to vibration-isolating platform in itself, it is ensured that the stabilization of system frequency.Each air cushion shock absorber sets one
The external Auxiliary Damping air bags of 100L or air accumulator 5, it is ensured that system frequency is 1.3Hz.Level tune is equipped with isolation mounting
Valve 4, when vibration-isolating platform load can be made to change, automatically adjusts level.
Vibration-isolating platform structural strength of the present invention is high, rigidity is big, bearing capacity is strong, isolation vibration interference ability is strong, solves
The technological difficulties of the vibration-isolating platform design of in-orbit weightlessness simulation, low cost of manufacture, strong applicability achieve good economy
Effect.
Specific embodiment of the 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 within the scope of the claims make a variety of changes or change, this not shadow
Sound substance of the invention.In the case where not conflicting, feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (9)
1. a kind of isolation mounting for the simulation of spacecraft in-orbit weightlessness, for being in-orbit super quiet weightless micro-vibration laboratory
Isolation ground is transferred to the vibration interference of spacecraft, it is characterised in that including vibration-isolating platform and some air cushion shock absorbers, institute
State air cushion shock absorber and be evenly arranged and be supported between vibration-isolating platform and laboratory's ground.
2. the isolation mounting for the simulation of spacecraft in-orbit weightlessness according to claim 1, it is characterised in that described
Vibration-isolating platform vertical direction intrinsic frequency is 1.5Hz, meets the clamped test specification of spacecraft.
3. the isolation mounting for the simulation of spacecraft in-orbit weightlessness according to claim 1, it is characterised in that each
Air cushion shock absorber sets an external Auxiliary Damping air bag of 100L or air accumulator, it is ensured that the stabilization of intrinsic frequency.
4. the isolation mounting for the simulation of spacecraft in-orbit weightlessness according to claim 3, it is characterised in that air bag
Thickness is 1.5mm, prevents microvibration from passing through air bag this body structure transmission.
5. the isolation mounting for the simulation of spacecraft in-orbit weightlessness according to claim 1, it is characterised in that be to protect
Card vibration-isolating platform certainty of measurement and stability, air spring impulse stroke are less than 10mm.
6. the isolation mounting for the simulation of spacecraft in-orbit weightlessness according to claim 1, it is characterised in that described
Vibration-isolating platform ensures smooth, steel plate thickness 8mm using punching block.
7. the isolation mounting for the simulation of spacecraft in-orbit weightlessness according to claim 1, it is characterised in that be to protect
Card ground is smooth, is equipped with concrete cover, and thickness is 20mm, and adds epoxide terrace.
8. the isolation mounting for the simulation of spacecraft in-orbit weightlessness according to claim 1, it is characterised in that also match somebody with somebody
Standby Level tune valve, when the load on vibration-isolating platform is changed, automatically adjusts level.
9. the isolation mounting for the simulation of spacecraft in-orbit weightlessness according to claim 1, it is characterised in that air
Can raise vibration-isolating platform after spring vibration-isolator inflation, so as to be separated with laboratory ground.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610986347.7A CN106763411A (en) | 2016-11-09 | 2016-11-09 | A kind of isolation mounting for the in-orbit weightlessness simulation of spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610986347.7A CN106763411A (en) | 2016-11-09 | 2016-11-09 | A kind of isolation mounting for the in-orbit weightlessness simulation of spacecraft |
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| Publication Number | Publication Date |
|---|---|
| CN106763411A true CN106763411A (en) | 2017-05-31 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610986347.7A Pending CN106763411A (en) | 2016-11-09 | 2016-11-09 | A kind of isolation mounting for the in-orbit weightlessness simulation of spacecraft |
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| CN (1) | CN106763411A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108679141A (en) * | 2018-04-19 | 2018-10-19 | 杭州亿恒科技有限公司 | Multiple degrees of freedom active vibration isolation arrangement and method |
| CN109100104A (en) * | 2018-08-17 | 2018-12-28 | 北京卫星环境工程研究所 | Multipurpose micro-vibration test set laboratory |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5413316A (en) * | 1993-12-13 | 1995-05-09 | Bridgestone/Firestone, Inc. | Adjustable rate air spring |
| CN101858403A (en) * | 2010-06-12 | 2010-10-13 | 江苏大学 | Six-shaft vibration and shock isolation platform for moving carrier carrying equipment |
| 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 |
| CN102678808A (en) * | 2012-06-12 | 2012-09-19 | 南京农业大学 | Shock absorbing system with combined rigidity and damping adjusting function and shock absorbing method |
| CN105134865A (en) * | 2015-07-31 | 2015-12-09 | 上海卫星工程研究所 | Micro-vibration vibration isolation support for in-orbit satellite flywheel |
| EP3032134A1 (en) * | 2014-12-10 | 2016-06-15 | Contitech France | Fillable bellows made of elastomeric material |
-
2016
- 2016-11-09 CN CN201610986347.7A patent/CN106763411A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5413316A (en) * | 1993-12-13 | 1995-05-09 | Bridgestone/Firestone, Inc. | Adjustable rate air spring |
| CN101858403A (en) * | 2010-06-12 | 2010-10-13 | 江苏大学 | Six-shaft vibration and shock isolation platform for moving carrier carrying equipment |
| 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 |
| CN102678808A (en) * | 2012-06-12 | 2012-09-19 | 南京农业大学 | Shock absorbing system with combined rigidity and damping adjusting function and shock absorbing method |
| EP3032134A1 (en) * | 2014-12-10 | 2016-06-15 | Contitech France | Fillable bellows made of elastomeric material |
| CN105134865A (en) * | 2015-07-31 | 2015-12-09 | 上海卫星工程研究所 | Micro-vibration vibration isolation support for in-orbit satellite flywheel |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108679141A (en) * | 2018-04-19 | 2018-10-19 | 杭州亿恒科技有限公司 | Multiple degrees of freedom active vibration isolation arrangement and method |
| CN108679141B (en) * | 2018-04-19 | 2020-04-17 | 杭州亿恒科技有限公司 | Multi-degree-of-freedom active vibration isolation device and method |
| CN109100104A (en) * | 2018-08-17 | 2018-12-28 | 北京卫星环境工程研究所 | Multipurpose micro-vibration test set laboratory |
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Application publication date: 20170531 |
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