CN105883012A - Satellite structure for realizing satellite-rocket vibration isolation based on elastic airbag - Google Patents
Satellite structure for realizing satellite-rocket vibration isolation based on elastic airbag Download PDFInfo
- Publication number
- CN105883012A CN105883012A CN201610254903.1A CN201610254903A CN105883012A CN 105883012 A CN105883012 A CN 105883012A CN 201610254903 A CN201610254903 A CN 201610254903A CN 105883012 A CN105883012 A CN 105883012A
- Authority
- CN
- China
- Prior art keywords
- satellite
- rocket
- vibration isolation
- air bag
- root
- 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
- 238000002955 isolation Methods 0.000 title claims abstract description 23
- 230000006378 damage Effects 0.000 claims abstract description 4
- 238000006073 displacement reaction Methods 0.000 claims abstract description 4
- 238000009434 installation Methods 0.000 claims abstract description 4
- 230000035939 shock Effects 0.000 claims description 8
- 239000007789 gas Substances 0.000 claims description 5
- 230000005540 biological transmission Effects 0.000 claims description 4
- 239000004677 Nylon Substances 0.000 claims description 3
- 229920006231 aramid fiber Polymers 0.000 claims description 3
- 230000003139 buffering effect Effects 0.000 claims description 3
- 229920001971 elastomer Polymers 0.000 claims description 3
- 229920001778 nylon Polymers 0.000 claims description 3
- 239000005060 rubber Substances 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 3
- 238000000926 separation method Methods 0.000 abstract description 3
- 238000010304 firing Methods 0.000 abstract 2
- 239000000203 mixture Substances 0.000 description 2
- 238000012856 packing Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Classifications
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- 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
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
-
- 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
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
- B64G1/2221—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state characterised by the manner of deployment
- B64G1/2227—Inflating
-
- 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
- B64G1/228—Damping of high-frequency vibration effects on spacecraft elements, e.g. by using acoustic vibration dampers
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention provides a satellite structure for realizing satellite-rocket vibration isolation based on an elastic airbag. The satellite structure comprises a satellite root vibration isolation airbag assembly fixed between a satellite-rocket connection separation device and a satellite body root, and a satellite top anti-collision airbag assembly, wherein one end of the satellite top anti-collision airbag assembly is fixed at corners at the top of the satellite body, and the other end of the satellite top anti-collision airbag assembly is close to the inner wall of a rocket firing; the satellite root vibration isolation airbag assembly comprises high-strength sealed airbags filled with high-pressure gas, and is used for isolating the vibration impact load of satellite-rocket installation interface transfer and supporting and fixing the satellite body; and the satellite top anti-collision airbag assembly also comprises high-strength sealed airbags filled with high-pressure gas, and is used as anti-collision cushion for the satellite and the inner wall of the rocket firing when the vibration displacement of the satellite top is overlarge, so as to avoid damage of the collision load on the satellite structure. The satellite structure is simple in structure mode and remarkable in vibration isolation effect, and can be used for effectively reducing the vibration load endured by a satellite product and greatly reducing the development cost of satellite components.
Description
Technical field
The invention belongs to satellite structure technical field, be specifically related to a kind of based on elastic bag realization
The satellite structure of satellite and the rocket vibration isolation.
Background technology
Satellite Product, at launching phase, can be affected by various vibrations, shock loading, excessive
Vibration, shock loading can directly result in destruction or the inefficacy of product on satellite.Its Satellite institute
The Main Load source being subject to is oscillating load, the rocket motor produced in rocket engine running
The shock loading that machine stage separation, the satellite and the rocket separate, this vibration, shock loading are tied by rocket
Structure is delivered to satellite-rocket docking face, is input to satellite body with the form of basic excitation, causes satellite
The structural vibration of product.Existing technology can't well solve vibration transmission between the satellite and the rocket
Problem, typically just by improve satellite structure intensity improve its vibration bearing capacity, this
To a certain extent it can be avoided that vibration, the structural failure that brings of shock environment, the result brought is but
It is that satellite structure weight, design cost are continuously increased.
Summary of the invention
For solving above-mentioned problems of the prior art, it is an object of the invention to provide one
Realize the satellite structure of satellite and the rocket vibration isolation based on elastic bag, vibration isolating effect is obvious, it is possible to effectively drop
The oscillating load that low Satellite Product is born, is substantially reduced satellite development cost.
For reaching above-mentioned purpose, the technical solution adopted in the present invention is:
A kind of satellite structure realizing satellite and the rocket vibration isolation based on elastic bag, including satellite body 3,
It is fixed on the satellite root vibration isolation air bag that satellite body 3 root is connected between separator 1 with the satellite and the rocket
Group；Each edges and corners, satellite body 3 top are fixed in one end, and the other end is in rocket radome fairing
Satellite top anticollision air bag group 4 at wall；Described satellite root vibration isolation air bag group 2 for every
From the satellite and the rocket installation interface transmission vibratory shock load, satellite body 3 is supported simultaneously and
Fixing；Described satellite top anticollision air bag group 4 is for excessive at satellite top vibration displacement
Time, as the crashproof buffering of satellite Yu rocket radome fairing inwall, it is to avoid satellite is tied by impact load
The destruction of structure.
Described satellite root vibration isolation air bag group 2 is made up of several high strength elastic pressure bladders,
Inside air bag is full of the gases at high pressure of preset pressure.
Described satellite top anti-collision air bag group 4 is made up of several high strength elastic pressure bladders,
Inside air bag is full of the gases at high pressure of preset pressure.
Described high strength elastic pressure bladder uses rubber, nylon, aramid fiber or metallic film
Make.
Compared to the prior art, the invention have the advantage that the satellite structure profit that the present invention is realized
The isolation of oscillating load between the satellite and the rocket, version letter is realized by the structure of elastic packing air bag
Single, vibration isolating effect is obvious, it is possible to effectively reduces the oscillating load that Satellite Product is born, significantly drops
Low satellite development cost.
Accompanying drawing explanation
Fig. 1 is that the present invention realizes the satellite structure schematic diagram of satellite and the rocket vibration isolation based on elastic bag.
Detailed description of the invention
With detailed description of the invention, the present invention is described in further detail below in conjunction with the accompanying drawings.
Realize the satellite system of satellite and the rocket vibration isolation based on elastic bag mainly wrap as it is shown in figure 1, a kind of
Include the satellite and the rocket and connect separator 1, satellite root vibration isolation air bag group 2, satellite body 3, satellite
Top 4 four parts of anticollision air bag group.
As it is shown in figure 1, the described satellite and the rocket connect separator 1 for being connected admittedly by satellite structure
Due to satellite and the rocket installation interface, the locking of satellite launch stage connects, and unlocks and separate after satellier injection,
Make satellite and Separation.
As it is shown in figure 1, described satellite root vibration isolation air bag group 2, by several high intensity bullets
Property pressure bladder composition, inside air bag is full of the gases at high pressure of preset pressure, the upper and lower two ends of air bag
It is individually fixed in the satellite and the rocket and connects separator 1 and satellite body 3, be used for isolating the satellite and the rocket and circle is installed
The vibratory shock load of face transmission, is supported satellite body 3 simultaneously and fixes.
As it is shown in figure 1, described satellite top anti-collision air bag group 4, also it is high-strength by several
Degree elastic packing air bag composition, each corner angle in satellite body 3 top are fixed in each air bag one end
Place, the other end is near rocket radome fairing inwall, when satellite top vibration displacement is excessive, as
Satellite and the crashproof buffering of rocket radome fairing inwall, it is to avoid satellite structure is broken by impact load
Bad.
As the preferred embodiment of the present invention, described high strength elastic pressure bladder uses rubber
Glue, nylon, aramid fiber or metallic film are made.
Claims (4)
1. the satellite structure realizing satellite and the rocket vibration isolation based on elastic bag, it is characterised in that: include that satellite is originally
Body (3), be fixed on satellite root that satellite body (3) root is connected with the satellite and the rocket between separator (1) every
Air bag group of shaking (2)；Each edges and corners, satellite body (3) top are fixed in one end, and the other end is near rocket rectification
Satellite top anticollision air bag group (4) at cover inwall；Described satellite root vibration isolation air bag group (2) for every
From the vibratory shock load of satellite and the rocket installation interface transmission, satellite body (3) is supported and fixes simultaneously；
Described satellite top anticollision air bag group (4) for when satellite top vibration displacement is excessive, as satellite with
The crashproof buffering of rocket radome fairing inwall, it is to avoid the impact load destruction to satellite structure.
A kind of satellite structure realizing satellite and the rocket vibration isolation based on elastic bag the most according to claim 1, its
It is characterised by: described satellite root vibration isolation air bag group (2) is made up of several high strength elastic pressure bladders,
Inside air bag is full of the gases at high pressure of preset pressure.
A kind of satellite structure realizing satellite and the rocket vibration isolation based on elastic bag the most according to claim 1, its
It is characterised by: described satellite top anti-collision air bag group (4) is made up of several high strength elastic pressure bladders,
Inside air bag is full of the gases at high pressure of preset pressure.
4. according to a kind of satellite structure realizing satellite and the rocket vibration isolation based on elastic bag described in Claims 2 or 3,
It is characterized in that: described high strength elastic pressure bladder uses rubber, nylon, aramid fiber or metallic film
Make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610254903.1A CN105883012B (en) | 2016-04-21 | 2016-04-21 | A kind of satellite structure that satellite and the rocket vibration isolation is realized based on elastic bag |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610254903.1A CN105883012B (en) | 2016-04-21 | 2016-04-21 | A kind of satellite structure that satellite and the rocket vibration isolation is realized based on elastic bag |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105883012A true CN105883012A (en) | 2016-08-24 |
| CN105883012B CN105883012B (en) | 2018-03-16 |
Family
ID=56704390
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610254903.1A Active CN105883012B (en) | 2016-04-21 | 2016-04-21 | A kind of satellite structure that satellite and the rocket vibration isolation is realized based on elastic bag |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105883012B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791814A (en) * | 2018-06-19 | 2018-11-13 | 吉林化工学院 | A kind of aircraft cowling that shock resistance is good |
| CN108983604A (en) * | 2018-07-06 | 2018-12-11 | 合肥工业大学 | A kind of adaptation control circuit for rocket radome fairing damping noise reduction |
| CN110234573A (en) * | 2016-12-13 | 2019-09-13 | 八河流资产有限责任公司 | Delivery vehicle emission system and method |
| CN113405410A (en) * | 2021-08-20 | 2021-09-17 | 中国科学院力学研究所 | Interstage separation device suitable for rocket cold separation |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1016898A (en) * | 1996-06-27 | 1998-01-20 | Toshiba Corp | Impact cushioning device for aerospace vehicle |
| EP0861780A1 (en) * | 1997-02-28 | 1998-09-02 | Daimler-Benz Aerospace Aktiengesellschaft | Roll-over preventing method during landing for an air or space vehicle |
| CN1824579A (en) * | 2006-03-31 | 2006-08-30 | 郑钢铁 | Integral vibration isolation platform of astrovehicle |
| CN104443445A (en) * | 2014-11-11 | 2015-03-25 | 上海宇航系统工程研究所 | Damping pipe support type damping adapter |
| 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 |
-
2016
- 2016-04-21 CN CN201610254903.1A patent/CN105883012B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1016898A (en) * | 1996-06-27 | 1998-01-20 | Toshiba Corp | Impact cushioning device for aerospace vehicle |
| EP0861780A1 (en) * | 1997-02-28 | 1998-09-02 | Daimler-Benz Aerospace Aktiengesellschaft | Roll-over preventing method during landing for an air or space vehicle |
| US6158691A (en) * | 1997-02-28 | 2000-12-12 | Daimlerchrysler Ag | Process for preventing turning over during the landing of an aircraft or spacecraft |
| CN1824579A (en) * | 2006-03-31 | 2006-08-30 | 郑钢铁 | Integral vibration isolation platform of astrovehicle |
| CN104443445A (en) * | 2014-11-11 | 2015-03-25 | 上海宇航系统工程研究所 | Damping pipe support type damping adapter |
| 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 |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110234573A (en) * | 2016-12-13 | 2019-09-13 | 八河流资产有限责任公司 | Delivery vehicle emission system and method |
| CN108791814A (en) * | 2018-06-19 | 2018-11-13 | 吉林化工学院 | A kind of aircraft cowling that shock resistance is good |
| CN108983604A (en) * | 2018-07-06 | 2018-12-11 | 合肥工业大学 | A kind of adaptation control circuit for rocket radome fairing damping noise reduction |
| CN113405410A (en) * | 2021-08-20 | 2021-09-17 | 中国科学院力学研究所 | Interstage separation device suitable for rocket cold separation |
| CN113405410B (en) * | 2021-08-20 | 2021-11-05 | 中国科学院力学研究所 | Interstage separation device suitable for rocket cold separation |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105883012B (en) | 2018-03-16 |
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