CN102717900A - Micro satellite platform suitable for low orbit satellite constellation networking application - Google Patents
Micro satellite platform suitable for low orbit satellite constellation networking application Download PDFInfo
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Abstract
The invention discloses a satellite platform, which comprises a structural subsystem and solar wing subsystems, thermal control subsystems, attitude orbit control subsystems, a propulsion subsystem, a power supply and distribution subsystem, a measurement control subsystem and a data transmission subsystem which are respectively connected with a comprehensive electronic subsystem, wherein the structural subsystem comprises a top plate, a bottom plate, a middle plate, a partition plate and side plates; the side plates are connected with each other, and the top plate and the bottom plate are respectively connected with the side plates to form a capsule on the inner part; the middle plate and the partition plate are arranged in the side plates and partition the capsule into an upper capsule and a bottom capsule; the power supply and distribution subsystem, the measurement control subsystem, the comprehensive electronic subsystem and the attitude orbit control subsystems are arranged on the partition plate; the solar wing subsystems are arranged on the side plates; a part of the propulsion subsystem is arranged in the bottom capsule, and the other part of the propulsion subsystem is arranged outside the bottom; the thermal control subsystems are scattered in the capsule and on the surface of the capsule; and single parts of the measurement control subsystem and the data transmission subsystem are arranged in the capsule, measurement control and data transmission antennas are arranged on the ground, and inter-satellite measurement antennas are symmetrically arranged on the surfaces of satellites. The satellite platform can be applied to low orbit satellite constellations, and has the advantages of light mass and small size.
Description
Technical field
The present invention relates to space equipment, be specifically related to a kind of microsatellite platform applicable to the application of near-earth satellite constellation networking technology.
Background technology
At space industry; A lot of satellite platforms are arranged; Be mainly used in and carry out the service guarantee system that space science is surveyed; For scientific exploration instrument and equipment provide emission, in orbit, service such as working environment, power supply, attitude control, data storage and transmission, be the core technology of space exploration task.Along with the development of China's Aerospace Technology,, satellite constellation replace single star to be applied to every field such as military affairs more and more because having characteristics such as broad covered area, the recurrence interval is short, response is fast.
The domsat platform is a lot, all has to 5000 feather weight from 20 feather weight, and still, these satellite platforms are all to the mono-task design at present, and quantity is not seldom generally considered constellation networking application; High orbit and quality are heavy, volume is big, cost is high though the big-dipper satellite platform towards constellation networking Application Design, is arranged in, and are unfavorable for the widespread usage of low rail constellation networking.
The present invention provides a kind of microsatellite platform of using towards the networking of low orbit satellite constellation; Can be applicable near earth space scientific exploration, optical remote sensing, application such as communication over the ground; Possessing the ability of several satellite in a rocket emission or the top level of employing combined transmit, is a kind of satellite application platform of innovation.
Summary of the invention
The object of the present invention is to provide a kind of microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used, be inappropriate for the technical matters that the low orbit satellite constellation is used to solve existing satellite platform.
For achieving the above object; The object of the present invention is to provide a kind of microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used; Comprise: structure subsystem and respectively with integrated electronics subsystem bonded assembly sun wing subsystem, thermal control subsystem, rail control subsystem, propulsion subsystem, confession sub power distribution system, tracking-telemetry and command subsystem and data transmission subsystem; Wherein, structure subsystem comprises: top board, base plate, la m, dividing plate and some side plates, and each side plate interconnects; Top board is connected with side plate respectively with base plate, the inner cabin body that forms; La m and dividing plate are arranged in the side plate, and are connected with side plate, top board and base plate respectively, and the cabin body is divided into upper-deck cabin and following hold; Supply distribution, observing and controlling, integrated electronics and rail control subsystem all to be arranged on the dividing plate, sun wing subsystem is separately positioned on cooresponding two blocks of side plates; Propulsion subsystem partly is arranged on down in the hold, and part is arranged at the bottom surface outside; Thermal control divides system to adopt whole low temperature design, and it is inner and surperficial to disperse to be arranged on the cabin body; Observing and controlling and data transmission subsystem unit parts are arranged in the body of cabin, and the observing and controlling number passes antenna and is installed on the ground, and star measurements antenna symmetry is installed on the celestial body surface, form omnidirectional's coverage.
According to the described microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used of preferred embodiment of the present invention, this sun wing subsystem according to different classification of track and its capacity of illumination condition design, and possesses the one dimension rotating function.
According to the described microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used of preferred embodiment of the present invention; This thermal control subsystem; It is main adopting passive thermal control; Initiatively thermal control is the isothermal design plan of assisting, and takes independent thermal control technology for load that specific (special) requirements is arranged or platform device, adapts near earth space-90 ~ 90 ℃ temperature environment.
According to the described microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used of preferred embodiment of the present invention; This rail control subsystem; Adopt zero momentum three axis stabilization mode, comprise star sensor, high accuracy number sun angle meter and gyro to measure assembly, adopt the reckoning of getting on the right track of star sensor and star in order to backup scenario; Controlling schemes comprises 4 2Nms counteraction flybacks, and treater is incorporated in the whole star High Performance integrated electronics computing machine.
According to the described microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used of preferred embodiment of the present invention; This propulsion subsystem; Adopt pressure type unit hydrazine catalytic decomposition system; Comprise that a spherical surface tension force tank and 8-12 platform rated thrust, nominal thrust are the thruster of 1N, in order to satisfy mission requirementses such as the foundation of satellite initial attitude, preliminary orbit adjustment, track maintenance and flywheel unloading.
According to the described microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used of preferred embodiment of the present invention; This supplies the sub power distribution system; Employing efficient is 28.6% three-junction gallium arsenide solar battery sheet and 30Ah lithium ion battery group associating power supply plan; Bus voltage 28 ± 1V is full regulative mode.
According to the described microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used of preferred embodiment of the present invention; This integrated electronics subsystem; Adopt the stack of miniaturization to connect the formula structure, be made up of a plurality of modules, intermodule adopts stacked connection; And platform adopts CAN bus or 422 communication interfaces, adopts the LVDS interface between capacity weight and the treater.
According to the described microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used of preferred embodiment of the present invention, this tracking-telemetry and command subsystem adopts USB and spread spectrum observing and controlling mode, is aided with GPS and measures; And configuration S-band space router in order to information transfer between star, realizes that a star leads to the whole network.
According to the described microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used of preferred embodiment of the present invention; This data transmission subsystem; Adopt the X frequency range, number biography bit rate can reach and be 60-100Mbps, comprises that number passes the comprehensive treatment device, X-band counts transmission transmitter and the X-band number passes antenna; In order to realize the communication of device ground, pass detection data back ground.
According to the described microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used of preferred embodiment of the present invention, the about 280kg of this platform gross weight, the about 60kg-80kg of capacity weight load-carrying capacity, the about 750mm * 750mm of body dimension * 1000mm.
Compared with prior art; Beneficial effect of the present invention is: whole star adopts boxboard formula load-carrying construction; Optimize the configuration layout, and adopt integrated, modularization stack to connect formula integrated electronics subsystem unified management is carried out in whole star flow of information, have trouble diagnosing, processing and restore funcitons; Configuration space router on the star realizes that the command, control, communications, and information between the satellite is shared in the constellation, is suitable for the low orbit satellite constellation and uses.In addition, the present invention adopts the small-sized band of Φ 340mm to link to each other with carrier rocket, be applicable to several satellite in a rocket or with top level combined transmit.The present invention also has technical characterstics such as light weight, little, the parallel manufacturing of volume and test, lead time weak point.In sum, compared with prior art, the present invention can be applicable to that several satellite in a rocket is used, is applicable to the low orbit satellite constellation or with top level combined transmit and have an advantage that light weight, little, the parallel manufacturing of volume and test, lead time lacks.
Description of drawings
Fig. 1 is a microsatellite flat-bed structural principle block diagram of the present invention;
Fig. 2 is a microsatellite flat-bed perspective view of the present invention;
Fig. 3 is the annexation scheme drawing of each subsystem of the embodiment of the invention.
The specific embodiment
Below in conjunction with accompanying drawing, specify the present invention.
Please consult Fig. 1 to Fig. 3 simultaneously; A kind of microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used comprises: structure subsystem 1 with respectively with High Performance integrated electronics computing machine bonded assembly sun wing subsystem 2, thermal control subsystem 3, rail control subsystem 4, propulsion subsystem 5, confession sub power distribution system 6, integrated electronics subsystem 7, tracking-telemetry and command subsystem 8 and data transmission subsystem 9, wherein; Structure subsystem 1 comprises: top board 11, base plate 12, la m 13, dividing plate 14 and some side plates 15; Each side plate 15 interconnects, and top board 11 is connected with side plate 15 respectively with base plate 12, and la m 13 is arranged in the side plate 15 with dividing plate 14; And be connected with side plate 15, top board 11 and base plate 12 respectively; Dividing plate 14 adopts the primary load bearing mode, supplies the parts and the equipment of sub power distribution system 6, tracking-telemetry and command subsystem 8, integrated electronics subsystem 7 and rail control subsystem 4 to be installed on the dividing plate 14, and sun wing subsystem 2 is separately positioned on cooresponding two blocks of side plates 15; Fix through explosive bolt, launch the back of entering the orbit.The parts such as tank of propulsion subsystem 5 are installed under the platform in the hold, and to reduce barycenter, thruster is installed on the platform bottom surface outside.Thermal control subsystem 3 adopts whole low temperature design, comprises parts such as coating multilayer, coating, thermally dependent resistor, temperature booster, and it is inner and surperficial to disperse to be arranged on the cabin body.Tracking-telemetry and command subsystem 8 is installed in the body of cabin with data transmission subsystem 9 unit parts, and the observing and controlling number passes antenna 81 and is installed on the ground, and star measurements antenna 82 symmetries are installed on the celestial body surface, forms omnidirectional's coverage.
Sun wing subsystem 2 according to its capacity of different classification of track and illumination condition design, can possess the function that one dimension rotates as required, satisfies satellite for a long time in the requirement of rail work.
Supply sub power distribution system 6, employing efficient is 28.6% three-junction gallium arsenide solar battery sheet and 30Ah lithium ion battery group associating power supply plan, and bus voltage 28 ± 1V is full regulative mode.
Tracking-telemetry and command subsystem 8 adopts USB and spread spectrum observing and controlling mode, and is aided with the GPS measurement; Information transfer adopts S-band space router between star, realizes that a star leads to the whole network function.
Fig. 2 is microsatellite flat-bed outside drawing of the present invention, and is as shown in Figure 2, and microsatellite platform of the present invention is the hexahedron configuration, and the assembling back forms upper-deck cabin and two sections in following cabin, and the lower end links to each other with carrier rocket or top level through Φ 340mm band; Platform adopts the control of zero momentum three axis stabilization, realizes keeping and motor-driven function from the attitude stabilization and motor-driven, the track of entering the orbit to the processes such as the sun wing orientation, capacity weight work, data transmission; Platform through with USB with spread to the master, GPS is measured as auxilliary observing and controlling mode, passes under the telemetry data; Pass mode through X frequency range number, pass under the payload data.
Fig. 3 is that system of the present invention connects block diagram; As shown in Figure 3; The integrated electronics subsystem is installed on the interior data processing center as satellite platform of High Performance integrated electronics computing machine; Through the information of subsystems such as thermal control, propelling, observing and controlling, number biography is dispatched and managed, accomplish functions such as energy management, temperature treatment, data acquisition, data management, data distribution, programming control, realize detector flight course autonomous management function.
Although content of the present invention has been done detailed introduction through above-mentioned preferred embodiment, will be appreciated that above-mentioned description should not be considered to limitation of the present invention.After those skilled in the art have read foregoing, for multiple modification of the present invention with to substitute all will be conspicuous.Therefore, protection scope of the present invention should be limited appended claim.
Claims (10)
1. microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used; It is characterized in that; Comprise: structure subsystem and respectively with integrated electronics subsystem bonded assembly sun wing subsystem, thermal control subsystem, rail control subsystem, propulsion subsystem, confession sub power distribution system, tracking-telemetry and command subsystem and data transmission subsystem; Wherein, said structure subsystem comprises: top board, base plate, la m, dividing plate and some side plates, and said each side plate interconnects; Said top board is connected with said side plate respectively with base plate, the inner cabin body that forms; Said la m and dividing plate are arranged in the said side plate, and are connected with said side plate, top board and base plate respectively, and said cabin body is divided into upper-deck cabin and following hold; Said confession distribution, observing and controlling, integrated electronics and rail control subsystem all are arranged on the said dividing plate, and said sun wing subsystem is separately positioned on cooresponding two blocks of side plates; Said propulsion subsystem partly is arranged in the said hold down, and part is arranged at the bottom surface outside; Said thermal control divides system to adopt whole low temperature design, and it is inner and surperficial to disperse to be arranged on said cabin body; Said observing and controlling and data transmission subsystem unit parts are arranged in the body of cabin, and the observing and controlling number passes antenna and is installed on the ground, and star measurements antenna symmetry is installed on the celestial body surface, form omnidirectional's coverage.
2. the microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used as claimed in claim 1 is characterized in that, said sun wing subsystem according to different classification of track and its capacity of illumination condition design, and possesses the one dimension rotating function.
3. the microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used as claimed in claim 1; It is characterized in that; Said thermal control subsystem, it is main adopting passive thermal control, initiatively thermal control is the isothermal design plan of assisting; Take independent thermal control technology for load that specific (special) requirements is arranged or platform device, adapt near earth space-90 ~ 90 ℃ temperature environment.
4. the microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used as claimed in claim 1; It is characterized in that said rail control subsystem adopts zero momentum three axis stabilization mode; Comprise star sensor, high accuracy number sun angle meter and gyro to measure assembly; Adopt reckonings of getting on the right track of star sensor and star in order to backup scenario, controlling schemes comprises 4 2Nms counteraction flybacks, and treater is incorporated into to be put in order in the star High Performance integrated electronics computing machine.
5. the microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used as claimed in claim 1; It is characterized in that; Said propulsion subsystem; Adopt pressure type unit hydrazine catalytic decomposition system, comprise that a spherical surface tension force tank and 8-12 platform rated thrust, nominal thrust are the thruster of 1N, in order to satisfy mission requirementses such as the foundation of satellite initial attitude, preliminary orbit adjustment, track maintenance and flywheel unloading.
6. the microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used as claimed in claim 1; It is characterized in that; Said confession sub power distribution system; Employing efficient is 28.6% three-junction gallium arsenide solar battery sheet and 30Ah lithium ion battery group associating power supply plan, and bus voltage 28 ± 1V is full regulative mode.
7. the microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used as claimed in claim 1; It is characterized in that said integrated electronics subsystem adopts the stack of miniaturization to connect the formula structure; Form by a plurality of modules; Intermodule adopts stacked connection, and platform adopts CAN bus or 422 communication interfaces, employing LVDS interface between capacity weight and the treater.
8. the microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used as claimed in claim 1 is characterized in that, said tracking-telemetry and command subsystem adopts USB and spread spectrum observing and controlling mode, is aided with GPS and measures; And configuration S-band space router in order to information transfer between star, realizes that a star leads to the whole network.
9. the microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used as claimed in claim 1; It is characterized in that said data transmission subsystem adopts the X frequency range; Number biography bit rate can reach and be 60-100Mbps; Comprise that number passes the comprehensive treatment device, X-band counts transmission transmitter and the X-band number passes antenna,, pass detection data back ground in order to realize the communication of device ground.
10. the microsatellite platform that is applicable to that the networking of low orbit satellite constellation is used as claimed in claim 1 is characterized in that the about 280kg of said platform gross weight, the about 60kg-80kg of capacity weight load-carrying capacity, the about 750mm * 750mm of body dimension * 1000mm.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5779195A (en) * | 1996-05-03 | 1998-07-14 | Motorola, Inc. | Satellite assembly having modular common bus components |
| FR2789653A1 (en) * | 1999-02-16 | 2000-08-18 | Matra Marconi Space France | Low orbit satellite constellation solar panel support system having extending arm lengthened satellite body attached and solar panels arm end 360 degree rotatable with limited second axis movement. |
| FR2789652A1 (en) * | 1999-02-16 | 2000-08-18 | Matra Marconi Space France | Telecommunications payload low orbit satellite configuration having lengthened trapezoidal body with small upper rigid panel holding satellite controls and larger lower panel holding payload. |
| US20040031885A1 (en) * | 2001-07-30 | 2004-02-19 | D'ausilio Robert F. | In orbit space transportation & recovery system |
| GB2413861A (en) * | 2004-05-06 | 2005-11-09 | Vega Group Plc | Controlling power to satellite electric propulsion system during eclipses. |
-
2012
- 2012-06-26 CN CN201210215018.4A patent/CN102717900B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5779195A (en) * | 1996-05-03 | 1998-07-14 | Motorola, Inc. | Satellite assembly having modular common bus components |
| FR2789653A1 (en) * | 1999-02-16 | 2000-08-18 | Matra Marconi Space France | Low orbit satellite constellation solar panel support system having extending arm lengthened satellite body attached and solar panels arm end 360 degree rotatable with limited second axis movement. |
| FR2789652A1 (en) * | 1999-02-16 | 2000-08-18 | Matra Marconi Space France | Telecommunications payload low orbit satellite configuration having lengthened trapezoidal body with small upper rigid panel holding satellite controls and larger lower panel holding payload. |
| US20040031885A1 (en) * | 2001-07-30 | 2004-02-19 | D'ausilio Robert F. | In orbit space transportation & recovery system |
| GB2413861A (en) * | 2004-05-06 | 2005-11-09 | Vega Group Plc | Controlling power to satellite electric propulsion system during eclipses. |
Non-Patent Citations (3)
| Title |
|---|
| 姚骏等: "新型卫星结构设计技术", 《中国空间科学技术》, no. 3, 30 June 2010 (2010-06-30) * |
| 陈昌亚等: "基于萤火一号技术的自主发射火星探测器方案设想", 《中国宇航学会深空探测技术专业委员会第八届学术年会论文集》, 25 October 2011 (2011-10-25), pages 11 - 19 * |
| 陈昌亚等: "萤火一号探测器的关键技术与设计特点", 《空间科学学报》, no. 5, 15 September 2009 (2009-09-15), pages 456 - 461 * |
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