CN102717900B - 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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- CN102717900B CN102717900B CN201210215018.4A CN201210215018A CN102717900B CN 102717900 B CN102717900 B CN 102717900B CN 201210215018 A CN201210215018 A CN 201210215018A CN 102717900 B CN102717900 B CN 102717900B
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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, there are a lot of satellite platforms, be mainly used in carrying out the service guarantee system of space science detection, for scientific exploration instrument and equipment provide transmitting, in orbit, the 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, due to satellite constellation have broad covered area, recurrence interval short, respond the feature such as fast and replace more and more single star to be applied to the every field such as military.
Domsat platform is a lot, all has to 5000 feather weight from 20 feather weight, and still, these satellite platforms are all for single task design at present, and quantity is little, does not generally consider constellation networking application; Although big-dipper satellite platform, towards constellation networking application design, is arranged in, high orbit and quality are heavy, volume is large, cost is high, is unfavorable for the generally application of low rail constellation networking.
The invention provides a kind of microsatellite platform towards Constellation of Low Earth Orbit Satellites networking application, can be applicable near earth space scientific exploration, optical remote sensing, the application such as communication over the ground, the ability that possesses several satellite in a rocket transmitting or employing Upper Stage 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 Constellation of Low Earth Orbit Satellites networking application, be unsuitable for the technical matters of Constellation of Low Earth Orbit Satellites application 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 Constellation of Low Earth Orbit Satellites networking application, comprise: structure subsystem and the sun wing subsystem being connected with integrated electronics subsystem respectively, 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, 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 side plate, and are connected with side plate, top board and base plate respectively, and cabin body is divided into upper-deck cabin and lower hold; All be arranged on dividing plate for distribution, observing and controlling, integrated electronics and rail control subsystem, sun wing subsystem is separately positioned on two blocks of corresponding side plates; Propulsion subsystem part is arranged in lower hold, and part is arranged at bottom surface outside; It is to adopt overall low temperature design that thermal control divides, and scattering device is inner and surperficial at cabin body; Observing and controlling and data transmission subsystem unit parts are arranged in the body of cabin, and observing and controlling number passes antenna and is installed on ground, measure antenna symmetry and be installed on celestial body surface between star, form omnidirectional's coverage.
According to the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application described in preferred embodiment of the present invention, this sun wing subsystem, designs its capacity according to different classification of track and illumination condition, and possesses one-dimensional rotation function.
According to the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application described in preferred embodiment of the present invention, this thermal control subsystem, it is main adopting passive thermal control, Active thermal control is auxiliary isothermal design plan, take independent thermal control technology for the load or the platform device that have particular/special requirement, adapt near earth space-90 ~ 90 DEG C temperature environment.
According to the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application described in 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, control program comprises 4 2Nms counteraction flybacks, and treater is incorporated in whole star High Performance integrated electronics computing machine.
According to the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application described in preferred embodiment of the present invention, this propulsion subsystem, adopt pressure type unit hydrazine catalytic decomposition system, comprise the thruster that a spherical surface tension force tank and 8-12 platform rated thrust, nominal thrust are 1N, in order to meet the mission requirementses such as the foundation of satellite initial attitude, preliminary orbit adjustment, track maintenance and flywheel unloading.
According to the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application described in preferred embodiment of the present invention, this is for sub power distribution system, adopt three-junction gallium arsenide solar battery sheet and 30Ah lithium ion battery group associating power supply plan that efficiency is 28.6%, bus voltage 28 ± 1V is full regulative mode.
According to the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application described in preferred embodiment of the present invention, this integrated electronics subsystem, adopt the stack of miniaturization to connect formula structure, formed by multiple modules, intermodule adopts stacked connection, and platform adopts CAN bus or 422 communication interfaces, adopts LVDS interface between capacity weight and treater.
According to the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application described in 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 communication between star, realizes the logical the whole network of a star.
According to the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application described in preferred embodiment of the present invention, this data transmission subsystem, adopt X frequency range, number passes bit rate and can reach for 60-100Mbps, comprise that number passes comprehensive treatment device, X-band counts transmission transmitter and X-band number passes antenna, communicate by letter in order to realize device, pass detection data back ground.
According to the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application described in 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 × 1000mm of body dimension.
Compared with prior art, beneficial effect of the present invention is: whole star adopts boxboard typed load-carrying construction, optimize configuration layout, and adopt integrated, modularization stack to connect formula integrated electronics subsystem whole star flow of information is carried out to unified management, there is trouble diagnosing, processing and restore funcitons; Configuration space router on star, the command, control, communications, and information of realizing between constellation Satellite is shared, and is suitable for Constellation of Low Earth Orbit Satellites application.In addition, the present invention adopts the small-sized band of Φ 340mm to be connected with carrier rocket, be applicable to several satellite in a rocket or with Upper Stage combined transmit.The technical characterstics such as the present invention also has that quality is light, volume is little, parallel manufacture and test, lead time are short.In sum, compared with prior art, the present invention can be applicable to Constellation of Low Earth Orbit Satellites application, be applicable to several satellite in a rocket or with Upper Stage combined transmit and have advantages of that quality is light, volume is little, parallel manufacture and test, lead time is short.
Brief description of the drawings
Fig. 1 is the structural principle block diagram of microsatellite platform of the present invention;
Fig. 2 is the perspective view of microsatellite platform of the present invention;
Fig. 3 is the annexation schematic diagram of each subsystem of the embodiment of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, illustrate the present invention.
Please refer to Fig. 1 to Fig. 3, a kind of microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application, comprising: structure subsystem 1 and the sun wing subsystem 2 being connected with High Performance integrated electronics computing machine respectively, thermal control subsystem 3, rail control subsystem 4, propulsion subsystem 5, for 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, top board 11 is connected with side plate 15 respectively with base plate 12, la m 13 and dividing plate 14 are arranged in side plate 15, and respectively with side plate 15, top board 11 is connected with base plate 12, and dividing plate 14 adopts primary load bearing mode, for sub power distribution system 6, tracking-telemetry and command subsystem 8, the parts of integrated electronics subsystem 7 and rail control subsystem 4 and equipment are arranged on dividing plate 14, and sun wing subsystem 2 is separately positioned on two blocks of corresponding side plates 15, fix by explosive bolt, after entering the orbit, launch.The parts such as the tank of propulsion subsystem 5 are installed under platform in hold, and to reduce barycenter, thruster is installed on platform bottom surface outside.Thermal control subsystem 3 adopts overall low temperature design, comprises the parts such as coated multilayer, coating, thermally dependent resistor, temperature booster, and scattering device is inner and surperficial at cabin body.Tracking-telemetry and command subsystem 8 and data transmission subsystem 9 unit parts are installed in the body of cabin, and observing and controlling number passes antenna 81 and is installed on ground, measure antenna 82 symmetries and be installed on celestial body surface between star, form omnidirectional's coverage.
Structure subsystem 1, formed by top board, base plate, la m, dividing plate and four blocks of side plates etc., adopt dividing plate primary load bearing mode, for parts and the equipment of power supply, observing and controlling, integrated electronics and rail control subsystem are installed, base plate 12 lower ends connect satellite and the rocket coupling link 10, satellite and the rocket coupling link 10 is specially Φ 340mm band, in order to be connected with carrier rocket or Upper Stage, be applicable to several satellite in a rocket or with Upper Stage combined transmit.
Sun wing subsystem 2, designs its capacity according to different classification of track and illumination condition, can possess as required the function of one-dimensional rotation, meets the requirement of the long-term operation on orbit of satellite.
Thermal control subsystem 3, it is main adopting passive thermal control, Active thermal control is auxiliary isothermal design plan, takes independent thermal control technology for the load or the platform device that have particular/special requirement, adapts near earth space-90 ~ 90 DEG C temperature environment.
Rail control subsystem 4, adopts zero momentum three axis stabilization mode.Utilize star sensor, high accuracy number sun angle meter, gyro as measuring assembly, backup scenario adopts reckonings of getting on the right track of star sensor and star, and control program adopts 4 2Nms counteraction flybacks realizations, and treater is incorporated in whole star High Performance integrated electronics computing machine.
Propulsion subsystem 5, adopt pressure type unit hydrazine catalytic decomposition system, by a spherical surface tension force tank, the main portion compositions such as the thruster that 8-12 platform rated thrust, nominal thrust is 1N, meet the mission requirementses such as the foundation of satellite initial attitude, preliminary orbit adjustment, track maintenance and flywheel unloading.
For sub power distribution system 6, adopt three-junction gallium arsenide solar battery sheet and 30Ah lithium ion battery group associating power supply plan that efficiency is 28.6%, bus voltage 28 ± 1V, is full regulative mode.
Integrated electronics subsystem 7, adopts the stack of miniaturization to connect formula structure, and platform can adopt CAN bus or 422 communication interfaces, between capacity weight and treater, can adopt LVDS interface.Cabinet is made up of multiple modules, and intermodule adopts stacked connection.
Tracking-telemetry and command subsystem 8, adopts USB and spread spectrum observing and controlling mode, and is aided with GPS measurement; Between star, communication adopts S-band space router, realizes the logical the whole network function of a star.
Data transmission subsystem 9, employing X frequency range, number passes bit rate and can reach for 60-100Mbps, counts the major part such as transmission transmitter and X-band number biography antenna form by number biography comprehensive treatment device, X-band.
Fig. 2 is the outside drawing of microsatellite platform of the present invention, and as shown in Figure 2, microsatellite platform of the present invention is hexahedron configuration, forms two sections, upper-deck cabin and lower cabin after assembling, and lower end is connected with carrier rocket or Upper Stage by Φ 340mm band; Platform adopts the control of zero momentum three axis stabilization, realizes attitude stabilization and motor-driven, track maintenance and motor-driven function from entering the orbit to the processes such as sun wing orientation, capacity weight work, data transmission; Platform is by with USB and spread to master, and GPS is measured as auxiliary observing and controlling mode, passes under telemetry data; Pass mode by X band number, pass under payload data.
Fig. 3 is that system of the present invention connects block diagram, as shown in Figure 3, integrated electronics subsystem is installed on the data processing center as satellite platform in High Performance integrated electronics computing machine, by the information of the subsystems such as thermal control, propelling, observing and controlling, number biography is dispatched and is managed, complete the functions such as energy management, temperature treatment, data acquisition, data management, Data dissemination, programming control, realize detector flight course autonomous management function.
Although content of the present invention has been done detailed introduction by above preferred embodiment, will be appreciated that above-mentioned description should not be considered to limitation of the present invention.Read after foregoing those skilled in the art, for multiple amendment of the present invention and substitute will be all apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (10)
1. one kind is applicable to the microsatellite platform of Constellation of Low Earth Orbit Satellites networking application, it is characterized in that, comprise: structure subsystem and the sun wing subsystem being connected with integrated electronics subsystem respectively, thermal control subsystem, rail control subsystem, propulsion subsystem, confession sub power distribution system, tracking-telemetry and command subsystem and data transmission subsystem, wherein, described structure subsystem comprises: top board, base plate, la m, dividing plate and some side plates, described each side plate interconnects, described top board is connected with described side plate respectively with base plate, the inner cabin body that forms; Described la m and dividing plate are arranged in described side plate, and are connected with described side plate, top board and base plate respectively, and described cabin body is divided into upper-deck cabin and lower hold; Described distribution, observing and controlling, integrated electronics and the rail control subsystem of supplying is all arranged on described dividing plate, and described sun wing subsystem is separately positioned on two blocks of corresponding side plates; Described propulsion subsystem part is arranged in described lower hold, and part is arranged at bottom surface outside; It is to adopt overall low temperature design that described thermal control divides, and scattering device is inner and surperficial at described cabin body; Described observing and controlling and data transmission subsystem unit parts are arranged in the body of cabin, and observing and controlling number passes antenna and is installed on ground, measure antenna symmetry and be installed on celestial body surface between star, form omnidirectional's coverage.
2. the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application as claimed in claim 1, is characterized in that, described sun wing subsystem, designs its capacity according to different classification of track and illumination condition, and possesses one-dimensional rotation function.
3. the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application as claimed in claim 1, it is characterized in that, described thermal control subsystem, it is main adopting passive thermal control, Active thermal control is auxiliary isothermal design plan, take independent thermal control technology for the load or the platform device that have particular/special requirement, adapt near earth space-90～90 DEG C temperature environment.
4. the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application as claimed in claim 1, it is characterized in that, described 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, control program comprises 4 2Nms counteraction flybacks, and treater is incorporated in whole star High Performance integrated electronics computing machine.
5. the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application as claimed in claim 1, it is characterized in that, described propulsion subsystem, adopt pressure type unit hydrazine catalytic decomposition system, comprise the thruster that a spherical surface tension force tank and 8-12 platform rated thrust, nominal thrust are 1N, in order to meet the foundation of satellite initial attitude, preliminary orbit adjustment, track maintenance and flywheel unloading mission requirements.
6. the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application as claimed in claim 1, it is characterized in that, described for sub power distribution system, adopt three-junction gallium arsenide solar battery sheet and 30Ah lithium ion battery group associating power supply plan that efficiency is 28.6%, bus voltage 28 ± 1V is full regulative mode.
7. the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application as claimed in claim 1, it is characterized in that, described integrated electronics subsystem, adopt the stack of miniaturization to connect formula structure, formed by multiple modules, intermodule adopts stacked connection, and platform employing CAN bus or 422 communication interfaces, adopts LVDS interface between capacity weight and treater.
8. the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application as claimed in claim 1, is characterized in that, described 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 communication between star, realizes the logical the whole network of a star.
9. the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application as claimed in claim 1, it is characterized in that, described data transmission subsystem, adopt X frequency range, it is 60-100Mbps that number passes bit rate, comprise that number passes comprehensive treatment device, X-band counts transmission transmitter and X-band number passes antenna, communicates by letter in order to realize device, passes detection data back ground.
10. the microsatellite platform that is applicable to Constellation of Low Earth Orbit Satellites networking application as claimed in claim 1, is characterized in that, the about 280kg of described platform gross weight, and capacity weight load-carrying capacity is 60kg-80kg, the about 750mm × 750mm × 1000mm of body dimension.
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| CN201210215018.4A CN102717900B (en) | 2012-06-26 | 2012-06-26 | Micro satellite platform suitable for low orbit satellite constellation networking application |
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| CN115158706A (en) * | 2022-06-17 | 2022-10-11 | 北京控制工程研究所 | Distributed space propulsion system capable of being assembled on orbit |
| CN115123584B (en) * | 2022-06-27 | 2024-06-07 | 山东大学 | Structure suitable for satellite S-axis and control dual-backup reaction flywheel system and control method |
| CN115352651A (en) * | 2022-08-08 | 2022-11-18 | 长光卫星技术股份有限公司 | Modularized mechanical and thermal integrated service cube satellite system suitable for batch production |
| CN115258194A (en) * | 2022-08-08 | 2022-11-01 | 长光卫星技术股份有限公司 | Business cubic satellite configuration and assembly method suitable for multiple separation modes |
Citations (4)
| 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. |
| GB2413861A (en) * | 2004-05-06 | 2005-11-09 | Vega Group Plc | Controlling power to satellite electric propulsion system during eclipses. |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040031885A1 (en) * | 2001-07-30 | 2004-02-19 | D'ausilio Robert F. | In orbit space transportation & recovery system |
-
2012
- 2012-06-26 CN CN201210215018.4A patent/CN102717900B/en active Active
Patent Citations (4)
| 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. |
| GB2413861A (en) * | 2004-05-06 | 2005-11-09 | Vega Group Plc | Controlling power to satellite electric propulsion system during eclipses. |
Non-Patent Citations (6)
| Title |
|---|
| 基于萤火一号技术的自主发射火星探测器方案设想;陈昌亚等;《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》;20111025;11-19 * |
| 姚骏等.新型卫星结构设计技术.《中国空间科学技术》.2010,(第3期),70-75,83. |
| 新型卫星结构设计技术;姚骏等;《中国空间科学技术》;20100630(第3期);70-75 * |
| 萤火一号探测器的关键技术与设计特点;陈昌亚等;《空间科学学报》;20090915(第5期);456-461 * |
| 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》.2011,11-19. |
| 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》.2009,(第5期),456-461. |
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