CN104358814A - Three-way shock isolation device for satellite - Google Patents
Three-way shock isolation device for satellite Download PDFInfo
- Publication number
- CN104358814A CN104358814A CN201410464945.9A CN201410464945A CN104358814A CN 104358814 A CN104358814 A CN 104358814A CN 201410464945 A CN201410464945 A CN 201410464945A CN 104358814 A CN104358814 A CN 104358814A
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- CN
- China
- Prior art keywords
- cover plate
- framework
- satellite
- energy
- base plate
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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
- F16F7/00—Vibration-dampers; Shock-absorbers
- F16F7/12—Vibration-dampers; Shock-absorbers using plastic deformation of members
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
-
- 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
- F16F7/00—Vibration-dampers; Shock-absorbers
- F16F7/12—Vibration-dampers; Shock-absorbers using plastic deformation of members
- F16F7/121—Vibration-dampers; Shock-absorbers using plastic deformation of members the members having a cellular, e.g. honeycomb, structure
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Vibration Dampers (AREA)
Abstract
The invention discloses a three-way shock isolation device for a satellite. The three-way shock isolation device mainly comprises a frame body, a cover plate, a bottom plate and four energy absorption material blocks, wherein the cover plate is mounted on the frame body, and is in surface contact with the frame body; the cover plate and the frame body relatively displace on the surface of the cover plate, so that a shock energy absorption action space is formed in the direction; the bottom plate is mounted on the frame body, and is not in contact with the cover plate; the four energy absorption material blocks are respectively mounted in four independent spaces formed by the frame body, the cover plate and the bottom plate, and are in tight fit with the frame body, the bottom plate and the cover plate. The three-way shock isolation device can bear objects subjected to shock isolation reliably and safely, ensures the mounting rigidity, the strength, the position precision and the like of the objects subjected to shock isolation, meanwhile, effectively isolates the shock transmission in three directions, ensures that the objects subjected to shock isolation are in a small enough shock environment reliably, and achieves the purpose that the objects subjected to shock isolation or shock sensitive parts are in on-track operation safely.
Description
Technical field
The present invention relates to space technology field, in particular, relate to a kind of satellite three-dimensional shock isolating apparatus.
Background technique
General satellite three-dimensional shock isolating apparatus, because satellite launches annex (as sun battle array, deployable antenna battle array etc.) be designed with honeycomb damping piece to fire-working article impact, can reduce the impact in certain direction, but cannot cover all directions.Therefore, be necessary to design a kind of satellite three-dimensional shock isolating apparatus, the impact launching the direction that annex self cannot cover is isolated and absorbed.And this three-dimensional 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 corresponding position, intensity and precision.Because present stage there is no the mature technology of such satellite three-dimensional shock isolating apparatus, and star existing more shock-sensitive parts, very easily damaging because withstanding shocks.Therefore, design a kind of development of satellite three-dimensional 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 problem existed in above-mentioned prior art, the invention provides a kind of satellite three-dimensional shock isolating apparatus, can reliable and secure carry by every rushing object, ensure by while rushing the installation rigidity of object, intensity and positional accuracy 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:
A kind of satellite three-dimensional shock isolating apparatus, primarily of framework, cover plate, base plate and four 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, described base plate does not contact with described cover plate, described four pieces of energy-absorbing material blocks are respectively charged into by described framework, in four separate space that cover plate and base plate are formed, and with described framework, base plate and cover plate closely cooperate.
Described energy-absorbing material block comprises the honeycomb of all kinds of specification, closed pore/Open-cell Aluminum Foam and 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 contacting point 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.
The compartition formed by described framework, cover plate and base plate is become five independently spaces by described cover plate, described four pieces of energy-absorbing material blocks are respectively charged into four separate space being wherein positioned at surrounding, described cover plate are provided with carried object or by every the interface rushing object.
Installed by screw between described base plate and framework.
The three-dimensional shock isolating apparatus launching annex fire-working article 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 fire-working article 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 Security of carried object powered 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 sectional drawing;
Fig. 3 is the plan view of Fig. 1;
Fig. 4 be Fig. 3 B-B to sectional drawing.
Embodiment
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, satellite three-dimensional shock isolating apparatus provided by the present invention, forms primarily of framework 1, base plate 2, cover plate 3 and four pieces of energy-absorbing material blocks 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, implements with four limit equal faces contacts, but slightly can be free to slide and be as the criterion;
Second step, loads framework by energy-absorbing material block 4, and drive fit is assembled, and slight extruding energy-absorbing material makes local produce resiliently deformable 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, does not contact between base plate 2 with cover plate 3, there is certain fit up gap.Four pieces of energy-absorbing material blocks 4 load formed by framework 1, cover plate 3 and base plate 2 four independently in space, and closely cooperate with framework 1, base plate 2 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 three-dimensional 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 installation precision.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 three-dimensional 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.And on the direction perpendicular to cover plate plate face, there is certain fit up gap, make three directions all 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 contacting point between cover plate 3 and framework 1.By the relative movement 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.
The compartition formed by framework 1, cover plate 3 and base plate 2 is become five independently spaces by cover plate 3, and four pieces of energy-absorbing material blocks 4 are respectively charged into four separate space being wherein positioned at surrounding.Cover plate 3 is provided with carried object or by every the interface 5 rushing object.
Energy-absorbing material block 4 and framework 1, to be assembled by drive fit between base plate 2 and cover plate 3, enough assembling rigidity can be ensured.
Design configuration of the present invention is simple, 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 device.
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; any simple three amendments 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. a satellite three-dimensional shock isolating apparatus, it is characterized in that, primarily of framework, cover plate, base plate and four 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, described base plate does not contact with described cover plate, there is gap, described four pieces of energy-absorbing material blocks are respectively charged into by described framework, in four separate space that cover plate and base plate are formed, and with described framework, base plate and cover plate closely cooperate.
2. satellite three-dimensional shock isolating apparatus 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 and aluminum pipe.
3. satellite three-dimensional shock isolating apparatus 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 contacting point 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. satellite three-dimensional shock isolating apparatus according to claim 1, it is characterized in that, the compartition formed by described framework, cover plate and base plate is become five independently spaces by described cover plate, described four pieces of energy-absorbing material blocks are respectively charged into four separate space being wherein positioned at surrounding, described cover plate are provided with carried object or by every the interface rushing object.
5. satellite three-dimensional shock isolating apparatus according to claim 1, be is characterized in that, installed between described base plate and framework by screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410464945.9A CN104358814B (en) | 2014-09-12 | 2014-09-12 | Three-way shock isolation device for satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410464945.9A CN104358814B (en) | 2014-09-12 | 2014-09-12 | Three-way shock isolation device for satellite |
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| Publication Number | Publication Date |
|---|---|
| CN104358814A true CN104358814A (en) | 2015-02-18 |
| CN104358814B CN104358814B (en) | 2017-01-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410464945.9A Active CN104358814B (en) | 2014-09-12 | 2014-09-12 | Three-way shock isolation device for satellite |
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| CN (1) | CN104358814B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105134874A (en) * | 2015-07-31 | 2015-12-09 | 上海卫星工程研究所 | Vibration isolation and buffering combined support for satellite flywheel |
| CN106122687A (en) * | 2016-08-12 | 2016-11-16 | 上海卫星工程研究所 | A kind of electric blasting valve for satellite booster pipeline is every rushing support |
| CN106246800A (en) * | 2016-08-12 | 2016-12-21 | 上海卫星工程研究所 | For the priming system of satellite antenna development mechanism every flushing device |
| 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 |
| JP2017185861A (en) * | 2016-04-04 | 2017-10-12 | 株式会社Ｉｈｉエアロスペース | Instrument loading device for satellite |
| 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS56151073A (en) * | 1980-03-20 | 1981-11-21 | Bekaert Sa Nv | Structure damping vibration and sliding shoe |
| JP2010116945A (en) * | 2008-11-11 | 2010-05-27 | Kihei Ito | Three-dimensional base isolation support |
| CN202991989U (en) * | 2012-12-10 | 2013-06-12 | 中国飞机强度研究所 | Integral installation type metal mesh vibration isolator |
| CN203463534U (en) * | 2013-08-13 | 2014-03-05 | 吴昊 | Combined type vibration isolator |
-
2014
- 2014-09-12 CN CN201410464945.9A patent/CN104358814B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS56151073A (en) * | 1980-03-20 | 1981-11-21 | Bekaert Sa Nv | Structure damping vibration and sliding shoe |
| JP2010116945A (en) * | 2008-11-11 | 2010-05-27 | Kihei Ito | Three-dimensional base isolation support |
| CN202991989U (en) * | 2012-12-10 | 2013-06-12 | 中国飞机强度研究所 | Integral installation type metal mesh vibration isolator |
| CN203463534U (en) * | 2013-08-13 | 2014-03-05 | 吴昊 | Combined type vibration isolator |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105134874A (en) * | 2015-07-31 | 2015-12-09 | 上海卫星工程研究所 | Vibration isolation and buffering combined support for satellite flywheel |
| 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 |
| JP2017185861A (en) * | 2016-04-04 | 2017-10-12 | 株式会社Ｉｈｉエアロスペース | Instrument loading device for satellite |
| CN106122687A (en) * | 2016-08-12 | 2016-11-16 | 上海卫星工程研究所 | A kind of electric blasting valve for satellite booster pipeline is every rushing support |
| CN106246800A (en) * | 2016-08-12 | 2016-12-21 | 上海卫星工程研究所 | For the priming system of satellite antenna development mechanism every flushing device |
| CN106246800B (en) * | 2016-08-12 | 2018-08-03 | 上海卫星工程研究所 | Priming system for satellite antenna unfolding mechanism is every flushing device |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104358814B (en) | 2017-01-25 |
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