CN107323694A - Modular satellite booster cabin - Google Patents
Modular satellite booster cabin Download PDFInfo
- Publication number
- CN107323694A CN107323694A CN201710353839.7A CN201710353839A CN107323694A CN 107323694 A CN107323694 A CN 107323694A CN 201710353839 A CN201710353839 A CN 201710353839A CN 107323694 A CN107323694 A CN 107323694A
- Authority
- CN
- China
- Prior art keywords
- satellite
- loaded cylinder
- bottom plate
- polygon
- cabin
- 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.)
- Pending
Links
- 230000001737 promoting effect Effects 0.000 claims abstract description 4
- 239000000463 material Substances 0.000 claims description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 230000001413 cellular effect Effects 0.000 claims description 3
- 239000000835 fiber Substances 0.000 claims description 3
- 239000011229 interlayer Substances 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 9
- 238000012360 testing method Methods 0.000 abstract description 6
- 238000011161 development Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 235000013399 edible fruits Nutrition 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- 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
- B64G1/40—Arrangements or adaptations of propulsion systems
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
Abstract
The invention discloses a kind of modular satellite booster cabin, it includes promoting cabin structure, propulsion system, forward controller, cabin structure is promoted to include satellite and the rocket connection ring, bottom plate, polygon loaded cylinder, propulsion system includes tank, latching valve, pressure sensor, filter, pushing pipe, thruster, bottom plate lower end and satellite and the rocket connection ring, polygon loaded cylinder is connected, tank, latching valve, pressure sensor, filter is all located on bottom plate, two pushing pipes are located on bottom plate and polygon loaded cylinder respectively, thruster is located on polygon loaded cylinder, forward controller is located on polygon loaded cylinder.The present invention can carry out general assembly, integrated and test job parallel with other bay sections of satellite, largely reduce operation difficulty, shorten the satellite lead time and the present invention designs succinct, functional independence, interface standard, can be selected as the standalone module of design of satellites.
Description
Technical field
The present invention relates to a kind of satellite booster cabin, more particularly to a kind of modular satellite booster cabin.
Background technology
With continuing to develop for space technology and Space Industry, one side design of satellites tends to integrated, standardization and mould
Block, on the other hand requires that satellite realizes quick design, rapid development, rapid fire and quick application.
Satellite propulsion system is as power set, and it, which is served as, sends satellite into working track, and makes satellite in the work phase
Between be maintained on required position, and the adjustment of track and posture is carried out according to satellite task requirement at any time, appointing of changing
Business.As the systems such as Attitude and orbit control system, number guard system, the TT＆C system of satellite propulsion system and satellite platform, have as satellite
The service equipment of effect load is generally mounted to satellite service cabin.In satellite development process, the general assembly of propulsion system, integrated and survey
Try the general assembly with satellite, integrated and test intersects progress.The product of propulsion system is installed, pipeline welding and verification test work all
Carried out on star, one side operating difficulties, the another aspect lead time is long.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of modular satellite booster cabin, its can with satellite other
Bay section carries out general assembly, integrated and test job parallel, largely reduces operation difficulty, shorten the satellite lead time and
Present invention design is succinct, functional independence, interface standard, can be selected as the standalone module of design of satellites.
The present invention is to solve above-mentioned technical problem by following technical proposals：A kind of modular satellite booster cabin,
Characterized in that, it includes promoting cabin structure, propulsion system, forward controller, cabin structure is promoted to include satellite and the rocket connection ring, bottom
Plate, polygon loaded cylinder, propulsion system include tank, latching valve, pressure sensor, filter, pushing pipe, thruster, bottom
Plate lower end is connected with satellite and the rocket connection ring, polygon loaded cylinder, and tank, latching valve, pressure sensor, filter are all located at bottom plate
On, latching valve, pressure sensor, filter are all located at the side of tank, and two pushing pipes are located at bottom plate and polygon respectively
On loaded cylinder, thruster is located at the bottom of polygon loaded cylinder, and forward controller is located on polygon loaded cylinder.
Preferably, the satellite and the rocket connection ring is using the 660 type mechanical interfaces for meeting international aerospace standard.
Preferably, the bottom plate uses light weight cellular sandwich plate material.
Preferably, the polygon loaded cylinder is regular hexagon loaded cylinder and uses the carbon fibre material of high specific strength.
The positive effect of the present invention is：First, cabin structure is promoted to be that propulsion system and forward controller provide installation
Basis, propelling module can carry out general assembly, integrated and test job parallel, largely as separate modular with other bay sections of satellite
On reduce operation difficulty, shorten the satellite lead time.2nd, propelling module functional independence, is used as holding for Satellite attitude and orbit control system
Row part, momentum is provided for it；Meanwhile, propelling module interface standard promotes cabin structure to include satellite and the rocket connection ring, and satellite and the rocket connection ring is adopted
With the mechanical interface for meeting international aerospace standard.So the propelling module can be selected as the standalone module of design of satellites.
Brief description of the drawings
Fig. 1 is schematic diagram of the invention.
Embodiment
Present pre-ferred embodiments are provided below in conjunction with the accompanying drawings, to describe technical scheme in detail.
As shown in figure 1, modular satellite booster cabin of the invention includes promoting cabin structure 1, propulsion system 2, Solid rocket engine
Device 3, promotes cabin structure 1 to include satellite and the rocket connection ring 101, bottom plate 102, polygon loaded cylinder 103, and propulsion system 2 includes tank
201st, latching valve 202, pressure sensor 203, filter 204, pushing pipe 205, thruster 206, the lower end of bottom plate 102 and the satellite and the rocket
Connection ring 101, polygon loaded cylinder 103 are connected, and tank 201, latching valve 202, pressure sensor 203, filter 204 are all located at
On bottom plate 102, latching valve 202, pressure sensor 203, filter 204 are all located at the side of tank 201, two pushing pipes
205 are located on bottom plate 102 and polygon loaded cylinder 103 respectively, and thruster 206 is located at the bottom of polygon loaded cylinder 103, promote
Controller 3 is located on polygon loaded cylinder 103.
Satellite and the rocket connection ring 101 can be more preferably attached using the 660 type mechanical interfaces for meeting international aerospace standard.
Bottom plate 102 uses light weight cellular sandwich plate material, so more light.
Polygon loaded cylinder 103 is regular hexagon loaded cylinder and uses the carbon fibre material of high specific strength, and such load is imitated
Fruit is more preferably.
The present invention can carry out general assembly, integrated and test job parallel with other bay sections of satellite, largely reduce behaviour
Make difficulty, shorten the satellite lead time and the present invention designs succinct, functional independence, interface standard, design of satellites can be used as
Standalone module is selected.
Particular embodiments described above, technical problem, technical scheme and beneficial effect to the solution of the present invention are carried out
It is further described, should be understood that the specific embodiment that the foregoing is only of the invention, be not limited to
The present invention, within the spirit and principles of the invention, any modification, equivalent substitution and improvements done etc. should be included in this
Within the protection domain of invention.
Claims (4)
1. a kind of modular satellite booster cabin, it is characterised in that it includes promoting cabin structure, propulsion system, forward controller,
Cabin structure is promoted to include satellite and the rocket connection ring, bottom plate, polygon loaded cylinder, propulsion system includes tank, latching valve, pressure sensing
Device, filter, pushing pipe, thruster, bottom plate lower end are connected with satellite and the rocket connection ring, polygon loaded cylinder, tank, latching valve,
Pressure sensor, filter are all located on bottom plate, and latching valve, pressure sensor, filter are all located at the side of tank, and two push away
Enter pipeline to be respectively located on bottom plate and polygon loaded cylinder, thruster is located at the bottom of polygon loaded cylinder, forward controller position
In on polygon loaded cylinder.
2. modular satellite booster cabin as claimed in claim 1, it is characterised in that the satellite and the rocket connection ring, which is used, meets state
660 type mechanical interfaces of border aerospace standard.
3. modular satellite booster cabin as claimed in claim 1, it is characterised in that the bottom plate uses light weight cellular interlayer
Plate material.
4. modular satellite booster cabin as claimed in claim 1, it is characterised in that the polygon loaded cylinder is positive six side
Shape loaded cylinder and the carbon fibre material for using high specific strength.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710353839.7A CN107323694A (en) | 2017-05-18 | 2017-05-18 | Modular satellite booster cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710353839.7A CN107323694A (en) | 2017-05-18 | 2017-05-18 | Modular satellite booster cabin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107323694A true CN107323694A (en) | 2017-11-07 |
Family
ID=60192779
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710353839.7A Pending CN107323694A (en) | 2017-05-18 | 2017-05-18 | Modular satellite booster cabin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107323694A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108298111A (en) * | 2017-12-26 | 2018-07-20 | 中国空间技术研究院 | A kind of common platform satellite chemical propulsion subsystem modular layout method |
| CN109635378A (en) * | 2018-11-27 | 2019-04-16 | 上海空间推进研究所 | Integrated modular system |
| CN114229040A (en) * | 2021-12-17 | 2022-03-25 | 中国长城工业集团有限公司 | Separable independent propulsion cabin system |
| CN114379825A (en) * | 2020-08-11 | 2022-04-22 | 中国科学院微小卫星创新研究院 | Small-sized high-orbit satellite public platform propulsion system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101907041A (en) * | 2010-07-23 | 2010-12-08 | 北京航空航天大学 | A propane liquefied gas micro-propulsion device suitable for micro-nano satellites |
| CN103963997A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Small satellite polygonal force bearing barrel |
| CN203806152U (en) * | 2014-04-29 | 2014-09-03 | 上海卫星工程研究所 | Novel star rocket adapter ring structure |
| CN104260901A (en) * | 2014-09-11 | 2015-01-07 | 上海卫星工程研究所 | Modular two-component propulsion system |
| CN106467176A (en) * | 2016-09-08 | 2017-03-01 | 上海卫星工程研究所 | The temp. control method in satellite booster cabin |
-
2017
- 2017-05-18 CN CN201710353839.7A patent/CN107323694A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101907041A (en) * | 2010-07-23 | 2010-12-08 | 北京航空航天大学 | A propane liquefied gas micro-propulsion device suitable for micro-nano satellites |
| CN203806152U (en) * | 2014-04-29 | 2014-09-03 | 上海卫星工程研究所 | Novel star rocket adapter ring structure |
| CN103963997A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Small satellite polygonal force bearing barrel |
| CN104260901A (en) * | 2014-09-11 | 2015-01-07 | 上海卫星工程研究所 | Modular two-component propulsion system |
| CN106467176A (en) * | 2016-09-08 | 2017-03-01 | 上海卫星工程研究所 | The temp. control method in satellite booster cabin |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108298111A (en) * | 2017-12-26 | 2018-07-20 | 中国空间技术研究院 | A kind of common platform satellite chemical propulsion subsystem modular layout method |
| CN109635378A (en) * | 2018-11-27 | 2019-04-16 | 上海空间推进研究所 | Integrated modular system |
| CN114379825A (en) * | 2020-08-11 | 2022-04-22 | 中国科学院微小卫星创新研究院 | Small-sized high-orbit satellite public platform propulsion system |
| CN114229040A (en) * | 2021-12-17 | 2022-03-25 | 中国长城工业集团有限公司 | Separable independent propulsion cabin system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20171107 |
|
| RJ01 | Rejection of invention patent application after publication |