CN104290927A - One-way impact isolating device for satellite - Google Patents
One-way impact isolating device for satellite Download PDFInfo
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- CN104290927A CN104290927A CN201410466522.0A CN201410466522A CN104290927A CN 104290927 A CN104290927 A CN 104290927A CN 201410466522 A CN201410466522 A CN 201410466522A CN 104290927 A CN104290927 A CN 104290927A
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Abstract
The invention discloses a one-way impact isolating device for a satellite. The one-way impact isolating device is mainly composed of a frame body, a cover plate, a bottom plate and two energy absorption material blocks. The cover plate is mounted on the frame body and is in surface contact with the frame body, a relative displacement section is formed inside the plate surface of the cover plate between the cover plate and the frame body, and thus an impact energy absorption action space exists in the direction. The bottom plate is mounted on the frame body, and the bottom plate and the cover plate are in surface contact. The energy absorption material blocks are contained into two enclosed spaces which are defined by the frame body, the cover plate and the bottom plate and are in close fit with the frame body and the cover plate. According to the one-way impact isolating device for the satellite, an impact-isolated object can be borne reliably and safely, the mounting rigidity, strength, position accuracy and the like of the impact-isolated object are guaranteed, meanwhile, impact transmission can be effectively isolated in one certain direction, it can be reliably guaranteed that the impact-isolated object has a sufficiently small impact environment, and the purpose that the impact-isolated object or an impact sensitive component can operate safely in an on-orbit mode for working is achieved.
Description
Technical field
The present invention relates to space technology field, in particular, relate to the unidirectional shock isolating apparatus of a kind of satellite.
Background technology
The unidirectional shock isolating apparatus of general satellite, because satellite launches annex (as sun battle array, deployable antenna battle array etc.) be designed with honeycomb damping piece to priming system impact, can reduce the impact in certain direction, but cannot cover all directions.Therefore, be necessary to design the unidirectional shock isolating apparatus of a kind of satellite, the impact launching the direction that annex self cannot cover is isolated and absorbed.And this unidirectional shock isolating apparatus adapts to the features such as the less design space of satellite, lower weight and ripe heaven material.Meanwhile, shock isolating apparatus also needs to ensure the installation rigidity of correspondence position, intensity and precision.Because present stage there is no the mature technology of such satellite with unidirectional shock isolating apparatus, and star existing more shock-sensitive parts, very easily damaging because withstanding shocks.Therefore, design the development of a kind of satellite with unidirectional shock isolating apparatus, to effectively absorbing or improving shock environment, ensure that the safety of sensing unit on star is with reliable, seems very important and urgent.
Summary of the invention
For the technical matters existed in above-mentioned prior art, the invention provides the unidirectional shock isolating apparatus of a kind of satellite, can reliable and secure carry by every rushing object, ensure by while rushing the installation rigidity of object, intensity and positional precision etc., the transmission of effective shock isolation, reliably ensureing to be possessed enough little shock environment by every rushing object, reaching by every the object of carrying out operation on orbit with rushing object or shock-sensitive piece safety.
For achieving the above object, the technical solution adopted in the present invention is as follows:
The unidirectional shock isolating apparatus of a kind of satellite, primarily of framework, cover plate, base plate and energy-absorbing material block composition, wherein, described cover plate is arranged in described framework, contact with described framework face, and in cover plate plate face, there is relative displacement interval between cover plate and framework, this direction is made to there is the action space impacting energy-absorbing, described base plate is arranged in described framework, for face contacts between described base plate with described cover plate, described energy-absorbing material packaged enter by described framework, in two enclosure spaces that cover plate and base plate are formed, and closely cooperate with described framework and described cover plate.
Described energy-absorbing material block comprises the honeycomb of all kinds of specification, closed pore/Open-cell Aluminum Foam or aluminum pipe.
The relative two side ends of described cover plate stretches in a right-angle surface of the framework of rectangular bent angle shape respectively, thus with this right angle plane-plane contact of described framework, and there is relative displacement interval described contact position between cover plate and framework, when described framework is fixed, described cover plate produces impact displacement a little with carried object or by every rushing object.
Described cover plate is provided with and stretches into described enclosure space inside and extend to described base plate place, thus realize face with described base plate and contact, the enclosure space formed by described framework, cover plate and base plate is divided into three independently enclosure spaces simultaneously, described two pieces of energy-absorbing material blocks are respectively charged into the enclosure space being positioned at both sides, and the part stretched at described cover plate is provided with carried object or by every the interface rushing object.
Installed by screw between described base plate and framework.
The unidirectional shock isolating apparatus launching annex priming system blast impulse for protecting satellite provided by the present invention, while reliable and secure ensureing that rigidity, intensity and precision are installed, reach higher impact isolating efficiency, the transmission of the blast impulse reliably suppressing priming system to produce in certain direction, ensure by every the shock environment rushing object security work, have the following advantages:
(1) design configuration is simple, and adopt ripe heaven material, shock isolation performance is good, possesses the condition that heaven is applied in-orbit;
(2) there is good design flexibility, realize economy and assembly process process;
(3) there is good installation rigidity, intensity and precision, ensure that the safety of carried object powered-flight phase and the stability of section in-orbit.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is apparatus structure schematic diagram provided by the present invention;
Fig. 2 be Fig. 1 A-A to section-drawing;
Fig. 3 is the birds-eye view of Fig. 1;
Fig. 4 be Fig. 3 B-B to section-drawing.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
Shown in Fig. 1 ~ Fig. 4, the unidirectional shock isolating apparatus of satellite provided by the present invention, forms primarily of framework 1, base plate 2, cover plate 3 and energy-absorbing material block 4.
This device number of assembling steps is as follows:
The first step, loads framework 1 by cover plate 3, ensures that larger space does not appear in cover plate 3 and framework 1, slightly can be free to slide be as the criterion with one direction;
Two pieces of energy-absorbing material blocks 4 are loaded framework by second step, and flush fit assembles, and slight extruding energy-absorbing material makes local produce elastic deformation or small plastic deformation;
3rd step, by fastening to base plate 2 and framework 1, provides threaded screw to be fastenedly connected.
Wherein, cover plate 3 is arranged in framework 1, contacts with framework 1, and in cover plate plate face, there is relative displacement interval between cover plate 3 and framework 1, makes this direction there is the action space impacting energy-absorbing.Base plate 2 is arranged in framework 1, and for face contacts between base plate 2 with cover plate 3, energy-absorbing material block 4 loads in the enclosure space that formed by framework 1, cover plate 3 and base plate 2, and closely cooperates with framework 1 and cover plate 3.
Framework 1 is designed with external interface 6, represents the envelope size of shock isolating apparatus, and according to constraint adjustment space envelope size.
The impact isolating performance of unidirectional shock isolating apparatus of the present invention, is not limited to quantity and the type of energy-absorbing material block 4, comprises all kinds of specification honeycomb, the closed pore/impact property such as Open-cell Aluminum Foam or aluminum pipe material type.In less design space, adopt the energy-absorbing material such as honeycomb or foamed aluminium to make energy-absorbing material block, while can ensureing to impact energy absorbing efficiency, make carried or be guaranteed by every rushing the assembling rigidity of object, intensity and setting accuracy.There are energy-absorbing material degeneration energy-absorbing and friction energy-absorbing two kinds of modes in shock isolating apparatus, but main energy-absorbing mode is based on energy-absorbing material degeneration performance.
Shock isolating apparatus possesses the design size of adjustment framework, cover plate and base plate, can design the shock isolating apparatus reaching maximum impact energy-absorbing usefulness.
The impact energy-absorbing mode of unidirectional shock isolating apparatus is embodied in, and there is relative displacement interval between cover plate 3 and framework 1 in cover plate plate face, makes this direction there is the action space impacting energy-absorbing.In the present embodiment, the relative two side ends of cover plate 3 stretches in a right-angle surface of the framework 1 of rectangular bent angle shape respectively, thus with this right angle plane-plane contact of framework 1, and there is relative displacement interval described contact position between cover plate 3 and framework 1.Cover plate 3 is provided with and extend into enclosure space inside and the part extending to base plate 2, this part realizes face with base plate 2 and contacts, by stretching into part, the enclosure space formed by framework 1, cover plate 3 and base plate 2 is divided into three independently enclosure spaces, two pieces of energy-absorbing material blocks 4 are respectively charged into the enclosure space being positioned at both sides simultaneously.The part that cover plate 3 stretches into offers with carried object or by every the interface 5 rushing object.By the relative motion between framework 1 and cover plate 3, extruding energy-absorbing material block makes it to produce plastic deformation and fracture, thus reaches impact energy-absorbing effect.Framework is fixed, and cover plate 3 produces impact displacement a little with carried object or by every rushing object.
Energy-absorbing material block 4 and being assembled by flush fit between framework 1 and cover plate 3, wherein between base plate 2 with cover plate 3, between cover plate 3 with framework 1, equal face contacts, and there is friction, implements assembling, can ensure enough assembling rigidity with flush fit.
It is simple that the present invention has design configuration, there is good design flexibility, realize economy and assembly process process, possess the features such as extensibility is strong, economy and durability, reliability are high, it is convenient, easy to use to assemble, applied range, can apply in various suspension apparatus.
Be more than the explanation to the specific embodiment of the invention, but be not used for limiting the present invention.Any those skilled in the art without departing from the spirit and scope of the present invention; the content of above-mentioned announcement can be utilized to make possible variation and amendment to scheme proposed by the invention; therefore; everyly do not depart from technology contents of the present invention; the any simple modification done above embodiment according to technical spirit of the present invention, equivalent variations and modification, all belong to protection scope of the present invention.
Claims (5)
1. the unidirectional shock isolating apparatus of satellite, it is characterized in that, primarily of framework, cover plate, base plate and two pieces of energy-absorbing material block compositions, wherein, described cover plate is arranged in described framework, contact with described framework face, and in cover plate plate face, there is relative displacement interval between cover plate and framework, this direction is made to there is the action space impacting energy-absorbing, described base plate is arranged in described framework, for face contacts between described base plate with described cover plate, described energy-absorbing material packaged enter by described framework, in two enclosure spaces that cover plate and base plate are formed, and closely cooperate with described framework and described cover plate.
2. the unidirectional shock isolating apparatus of satellite according to claim 1, is characterized in that, described energy-absorbing material block comprises the honeycomb of all kinds of specification, closed pore/Open-cell Aluminum Foam or aluminum pipe.
3. the unidirectional shock isolating apparatus of satellite according to claim 1, it is characterized in that, the relative two side ends of described cover plate stretches in a right-angle surface of the framework of rectangular bent angle shape respectively, thus with this right angle plane-plane contact of described framework, and there is relative displacement interval described contact position between cover plate and framework, when described framework is fixed, described cover plate produces impact displacement a little with carried object or by every rushing object.
4. the unidirectional shock isolating apparatus of satellite according to claim 1, it is characterized in that, described cover plate is provided with and stretches into described enclosure space inside and extend to described base plate place, thus realize face with described base plate and contact, the enclosure space formed by described framework, cover plate and base plate is divided into three independently enclosure spaces simultaneously, described two pieces of energy-absorbing material blocks are respectively charged into the enclosure space being positioned at both sides, and the part stretched at described cover plate is provided with carried object or by every the interface rushing object.
5. the unidirectional shock isolating apparatus of satellite according to claim 1, is characterized in that, is installed between described base plate and framework by screw.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410466522.0A CN104290927B (en) | 2014-09-12 | 2014-09-12 | A kind of unidirectional shock isolating apparatus of satellite |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410466522.0A CN104290927B (en) | 2014-09-12 | 2014-09-12 | A kind of unidirectional shock isolating apparatus of satellite |
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| CN104290927A true CN104290927A (en) | 2015-01-21 |
| CN104290927B CN104290927B (en) | 2016-11-16 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292523A (en) * | 2015-10-27 | 2016-02-03 | 浙江大学 | Separating device and satellite and rocket separating device with buffering structure |
| CN106882399A (en) * | 2015-12-16 | 2017-06-23 | 北京空间技术研制试验中心 | Spacecraft equipment surge guard device |
| CN109178347A (en) * | 2018-10-17 | 2019-01-11 | 长光卫星技术有限公司 | A kind of unidirectional shock isolating apparatus suitable for microsatellite |
| CN109229428A (en) * | 2018-10-17 | 2019-01-18 | 长光卫星技术有限公司 | A kind of three-dimensional shock isolating apparatus suitable for microsatellite |
| CN114291304A (en) * | 2021-12-31 | 2022-04-08 | 北京国电高科科技有限公司 | One-way impact isolation device suitable for microsatellite |
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| US5197707A (en) * | 1991-07-29 | 1993-03-30 | Kohan Barry A | Isolation platform and method |
| JP2006066410A (en) * | 2004-08-24 | 2006-03-09 | Sharp Corp | Drop shock buffer structure |
| CN202627441U (en) * | 2012-07-11 | 2012-12-26 | 中国人民解放军总参谋部工程兵科研三所 | Rapid assembling type shock-insulating floor |
| KR101321270B1 (en) * | 2011-10-28 | 2013-11-04 | 삼성전기주식회사 | Inertial Sensor |
| CN203512062U (en) * | 2013-10-08 | 2014-04-02 | 北京航天长征飞行器研究所 | Instrument overall vibration reduction structure used under long-time vibration environment |
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2014
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US5197707A (en) * | 1991-07-29 | 1993-03-30 | Kohan Barry A | Isolation platform and method |
| JP2006066410A (en) * | 2004-08-24 | 2006-03-09 | Sharp Corp | Drop shock buffer structure |
| KR101321270B1 (en) * | 2011-10-28 | 2013-11-04 | 삼성전기주식회사 | Inertial Sensor |
| CN202627441U (en) * | 2012-07-11 | 2012-12-26 | 中国人民解放军总参谋部工程兵科研三所 | Rapid assembling type shock-insulating floor |
| CN203512062U (en) * | 2013-10-08 | 2014-04-02 | 北京航天长征飞行器研究所 | Instrument overall vibration reduction structure used under long-time vibration environment |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292523A (en) * | 2015-10-27 | 2016-02-03 | 浙江大学 | Separating device and satellite and rocket separating device with buffering structure |
| CN106882399A (en) * | 2015-12-16 | 2017-06-23 | 北京空间技术研制试验中心 | Spacecraft equipment surge guard device |
| CN106882399B (en) * | 2015-12-16 | 2018-12-25 | 北京空间技术研制试验中心 | Spacecraft equipment surge guard device |
| CN109178347A (en) * | 2018-10-17 | 2019-01-11 | 长光卫星技术有限公司 | A kind of unidirectional shock isolating apparatus suitable for microsatellite |
| CN109229428A (en) * | 2018-10-17 | 2019-01-18 | 长光卫星技术有限公司 | A kind of three-dimensional shock isolating apparatus suitable for microsatellite |
| CN109178347B (en) * | 2018-10-17 | 2023-08-29 | 长光卫星技术股份有限公司 | Unidirectional impact isolation device suitable for microsatellite |
| CN109229428B (en) * | 2018-10-17 | 2024-02-20 | 长光卫星技术股份有限公司 | Three-way impact isolation device suitable for microsatellite |
| CN114291304A (en) * | 2021-12-31 | 2022-04-08 | 北京国电高科科技有限公司 | One-way impact isolation device suitable for microsatellite |
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| CN104290927B (en) | 2016-11-16 |
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