CN205910547U - Star of integration carries integration electronic system - Google Patents
Star of integration carries integration electronic system Download PDFInfo
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- CN205910547U CN205910547U CN201620833483.8U CN201620833483U CN205910547U CN 205910547 U CN205910547 U CN 205910547U CN 201620833483 U CN201620833483 U CN 201620833483U CN 205910547 U CN205910547 U CN 205910547U
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Abstract
The utility model provides a star of integration carries integration electronic system, it includes that integration electronic unit summation passes the transmitter, the integration electronic unit includes the spaceborne computer module, observes and controls module, data transfer module, power control module, the spaceborne computer module includes star affair administrative unit, gesture and orbit controlling unit and thermistor( -ter) reason unit, it is connected with the spaceborne computer module through bus network respectively to observe and control module, data transfer module, power control module, power control module passes through bus network and observing and controlling module, data transfer module are connected, data transfer module passes the transmitter with the number and is connected. Adopt the technical scheme of the utility model, have advantages such as small, light in weight, function density height, can realize the platform device function of satellite, realize the purpose that the cable reduces, the satellite is miniaturized on the star, can satisfy well low orbit, long -life, highly reliable, the satellite task requirement more than the 100kg level.
Description
Technical field
This utility model is related to a kind of spaceborne Integrated Electronic System, more particularly, to a kind of spaceborne integrated electronicses system of integration
System.
Background technology
Spaceborne Integrated Electronic System is the core of satellite platform, and it is based on bus network on star, realizes the number between equipment
According to shared and interaction, complete the observing and controlling of satellite platform, the function such as energy conservation, number pipe, thermal control, rail control algorithm sum pass.With
The growth of microsatellite application demand and the development of satellite borne equipment technology, spaceborne Integrated Electronic System is sent out towards both direction respectively
Exhibition, a kind of trend is standardization, generalization, to realize quick, economic satellite development, meets rapid response to customer's need, risk will
Seek not high task；Another kind of trend is integrated, integrated, the satellite system to realize high functional density, meets integrated level
Task high, that reliability is high.
For the high task of reliability requirement, traditional spaceborne Integrated Electronic System adopts each subsystem independent design unit
Mode, using high-grade device in a large number in unit design, necessarily lead to whole star weight and size to increase.For microsatellite
How speech, entered the orbit by the way of carrying and launch, and whole star weight and size increase, and required delivery mounting space is required for increasing,
Satellite will be led to strong to the adaptability delivering it is difficult to select suitable delivery.
Utility model content
For above technical problem, this utility model provides a kind of spaceborne Integrated Electronic System of integration, has body
Long-pending little, lightweight, functional density is high etc. feature.
In this regard, the technical solution of the utility model is:
A kind of spaceborne Integrated Electronic System of integration, it includes an integrated electronicses unit and a number of units transmission transmitter,
Described integrated electronicses unit includes spaceborne computer module, control module, digital transmission module, energy supply control module, described spaceborne meter
Calculation machine module includes Star Service administrative unit, Attitude and orbit control unit and thermal control administrative unit；Described Attitude and orbit control
Unit and thermal control administrative unit are connected with spaceborne computer module；Described control module, digital transmission module, energy supply control module are respectively
It is connected with spaceborne computer module by bus network, described energy supply control module is passed through bus network and passed with control module, number
Module connects；Described digital transmission module is connected with number transmission transmitter.
Wherein, described bus network is standard can bus.Spaceborne computer module realize Star Service management function, attitude with
Orbits controlling and thermal control management function, the function of Star Service administrative unit include remote control, Telemetry Data Acquisition and framing, program control, when
Between management, Portable Batch System and the function such as in-orbit software modification and injection；The function of Attitude and orbit control unit includes appearance
The data acquisition of state sensor, attitude control actuator and thruster part and control function；The function of thermal control administrative unit presses heat
Control demand is realized the break-make to heater and is controlled.
Control module realizes the functions such as remote measurement, remote control and exterior measuring, and telemetry function includes telemetry encryption, downlink telemetry letter
Number spread spectrum, be modulated into radiofrequency signal and export；Distant control function includes the up radio signal reception in ground, despreading, demodulation
And deciphering, the decoding and exporting of direct instruction, and the forwarding capability of upstream data；Exterior measuring function includes upstream radio-frequency signal solution
Expand and demodulate, the deciphering of exterior measuring signal, resolving, framing and encryption, and by descending exterior measuring signal spread-spectrum, be modulated into radiofrequency signal
And export.
Energy supply control module realizes the function such as power supply management and thermal control management, and power supply management function is included once
Power supply adjusts and controls, and accumulator battery carries out additives for overcharge protection, over and Balance route, and primary power source is converted to secondary
Power supply, and distributing function；Thermal control management function is temperature information in collection star, according to the command switch of spaceborne computer module
Heater.
Digital transmission module realizes the functions such as data record, playback, encryption, scrambling, coding, modulation amplification and filtering, and changes
For the output of x frequency range conducted signal.
Energy supply control module by Integrated Electronic System energy flow be energy supply control module by outside primary power source through power supply
After conversion, output+5v, ± 12v secondary power supply, are each module of integrated electronicses assembly and external equipment provides the energy.
The spaceborne Integrated Electronic System internal flow of information of integration includes remote information stream, telemetry intelligence (TELINT) stream, thermal control information
Stream sum passes flow of information.Various information stream transmission processes are as follows.
(1) remote information stream
Remote information is sent to control module through up remote-control channel, through despreading, demodulation, deciphering after, direct instruction by
Answering machine directly decodes output, and for indirect instruction and upper note data block, control module gives spaceborne calculating by can Bus repeater
Machine module, after spaceborne computer module is processed further, gives each slave computer by can Bus repeater.
(2) telemetry intelligence (TELINT) stream
Telemetry intelligence (TELINT) gathers each bottom by spaceborne computer module by can bus, analog quantity interface, quantity of state interface etc.
The telemetry parameter of machine, is packed into telemetry by telemetry protocol, is sent to control module by can bus, through observing and controlling mould
The encryption of block, modulation, spread spectrum after, descend into ground.
(3) thermal control flow of information
In star, temperature is gathered by energy supply control module, re-sends to spaceborne computer module, by spaceborne computer module root
Require the break-make instruction of output heating circuit according to thermal control, energy supply control module executes specific computer heating control after receiving instruction.
(4) number passes flow of information
Digital transmission module passes through can bus record platform data, by lvds interface record load data, when satellite passes by
By the data readback of record, and x frequency range radio signal transmission is formed to ground by number transmission transmitter.
Using this technical scheme, with STD bus as core network, form distributed network structure, between module, pass through mark
Quasi- bus interconnection, and be integrated in integrated synthesis electronic system, the data interconnection between each module is realized by bus network,
It is achieved thereby that the Star Service management of satellite, observing and controlling response, rail control calculating and control, power supply management, data processing and biography
The functions such as defeated and thermal control management.Compared to the subsystem units of the equal functional performance of conventional satellite, this technical scheme has volume
The feature little, lightweight, functional density is high etc., solves the miniaturization of 100kg level satellite, the problems such as integrated, cable simplifies,
Low orbit in can meeting, long-life, satellite task more than highly reliable, 100kg level require.
As further improvement of the utility model, described integrated electronicses unit includes integrated electronicses motherboard, power supply
Plate, number pass baseband board, spaceborne computer panel, switch boards, advance power board, io plate, control and testing board, described power board,
Number pass baseband boards, spaceborne computer panel, switch boards, propulsion power board, io plate, control and testing board respectively pass through bus network with comprehensive
Close electronics motherboard to connect；Described number is passed baseband board and is connected with number transmission transmitter, and described several transmission transmitters pass through number and pass antenna transmission
Data.
As further improvement of the utility model, described power board includes primary power source adjustable plate, secondary power supply
With panel, power supply and thermal control management board, described primary power source adjustable plate, secondary power supply and panel, power supply and thermal control management
Plate is connected with integrated electronicses motherboard by bus network respectively.
As further improvement of the utility model, described number biography baseband board includes the first number biography baseband board, the second number passes
Baseband board, described first number passes baseband board, the second number is passed baseband board and is connected with integrated electronicses motherboard by bus network respectively；The
One number passes baseband board, the second number is passed baseband board and is connected with number transmission transmitter.
As further improvement of the utility model, described spaceborne computer panel includes a machine cpu plate and b machine cpu
Plate, described switch boards include the first switch boards, the second switch boards and the 3rd switch boards, described a machine cpu plate, b machine cpu plate, first
Switch boards, the second switch boards and the 3rd switch boards are connected with integrated electronicses motherboard by bus network respectively.
As further improvement of the utility model, described control and testing board includes the first control and testing board and the second control and testing board, described
First control and testing board and the second control and testing board are connected with integrated electronicses motherboard by bus network respectively.
As further improvement of the utility model, described control and testing board is located at the side of the cabinet of integrated electronicses unit,
Be externally provided with observing and controlling receiving and transmitting front end and TT＆C antenna positioned at the cabinet of the described integrated electronicses unit of control and testing board side, described control and testing board with
Described observing and controlling receiving and transmitting front end connects, and described observing and controlling receiving and transmitting front end is connected with TT＆C antenna.
Compared with prior art, the beneficial effects of the utility model are:
This utility model has the advantages that small volume, lightweight, functional density are high, the platform device work(of achievable satellite
Can, realize on star cable reduce, the purpose of satellite miniaturization, low orbit in can meeting, the long-life, more than highly reliable, 100kg level
Satellite task require.The technical solution of the utility model may extend away and several transmission transmitters are integrated in integrated electronicses unit, enters
One step improves the integrated level of on-board equipment, realizes the miniaturization of whole star.
Brief description
Fig. 1 is a kind of module diagram of embodiment of this utility model.
Fig. 2 is a kind of functional block diagram of embodiment of this utility model.
Fig. 3 is a kind of block diagram of system of embodiment of this utility model.
Specific embodiment
Below in conjunction with the accompanying drawings, preferably embodiment of the present utility model is described in further detail.
As shown in figure 1, a kind of spaceborne Integrated Electronic System of integration, it includes integrated electronicses unit sum and passes transmitting
Machine, described integrated electronicses unit includes spaceborne computer module, control module, digital transmission module, energy supply control module, described spaceborne
Computer module includes Star Service administrative unit, Attitude and orbit control unit and thermal control administrative unit；Described attitude and track control
Unit processed and thermal control administrative unit are connected with spaceborne computer module；Described control module, digital transmission module, energy supply control module divide
Tong Guo bus network not be connected with spaceborne computer module, described energy supply control module passes through bus network and control module, number
Transmission module connects；Described digital transmission module is connected with number transmission transmitter.
Spaceborne computer module realizes Star Service management function, Attitude and orbit control and thermal control management function, and Star Service manages
Function includes remote control, Telemetry Data Acquisition and framing, program control, time management, Portable Batch System and in-orbit software modification and note
The function such as enter；Attitude and orbit control function includes the data acquisition of attitude sensor, attitude control actuator and thruster part
With control function；Thermal control management function is pressed thermal control demand and is realized the break-make control to heater.
Control module realizes the functions such as remote measurement, remote control and exterior measuring, and telemetry function includes telemetry encryption, downlink telemetry letter
Number spread spectrum, be modulated into radiofrequency signal and export；Distant control function includes the up radio signal reception in ground, despreading, demodulation
And deciphering, the decoding and exporting of direct instruction, and the forwarding capability of upstream data；Exterior measuring function includes upstream radio-frequency signal solution
Expand and demodulate, the deciphering of exterior measuring signal, resolving, framing and encryption, and by descending exterior measuring signal spread-spectrum, be modulated into radiofrequency signal
And export.
Energy supply control module realizes the function such as power supply management and thermal control management, and power supply management function is included once
Power supply adjusts and controls, and accumulator battery carries out additives for overcharge protection, over and Balance route, and primary power source is converted to secondary
Power supply, and distributing function；Thermal control management function is temperature information in collection star, according to the command switch of spaceborne computer module
Heater.
Digital transmission module realizes the functions such as data record, playback, encryption, scrambling, coding, modulation amplification and filtering, and changes
For the output of x frequency range conducted signal.
Energy supply control module by Integrated Electronic System energy flow be energy supply control module by outside primary power source through power supply
After conversion, output+5v, ± 12v secondary power supply, are each module of integrated electronicses assembly and external equipment provides the energy.
The spaceborne Integrated Electronic System of described integration, based on can bus network, forms distributed network structure, collection
Become the major function of satellite platform, calculated and management, power supply including the Star Service management of satellite, observing and controlling response, rail control
With functions such as management, thermal control management function, data processing and transmission, functional block diagram is as shown in Figure 2.
As shown in figure 3, described integrated electronicses unit includes integrated electronicses motherboard, power board, number pass baseband board, spaceborne
Computer panel, switch boards, propulsion power board, io plate, control and testing board, described power board, number pass baseband board, spaceborne calculating
Machine panel, switch boards, propulsion power board, io plate, control and testing board are connected with integrated electronicses motherboard by bus network respectively；Described
Number is passed baseband board and is connected with number transmission transmitter, and described several transmission transmitters pass through number and pass antenna transmission data.Described power board
Including primary power source adjustable plate, secondary power supply and panel, power supply and thermal control management board, described primary power source adjustable plate, secondary
Power supply is connected with integrated electronicses motherboard by bus network with thermal control management board respectively with panel, power supply.Described number passes base band
Plate includes the first number and passes baseband board, the second number biography baseband board, and described first number passes baseband board, the second number passes baseband board and passes through respectively
Bus network is connected with integrated electronicses motherboard, and the first number passes baseband board, the second number is passed baseband board and is connected with number transmission transmitter.Described
Spaceborne computer panel includes a machine cpu plate and b machine cpu plate, described switch boards include the first switch boards, the second switch boards and
3rd switch boards, described a machine cpu plate, b machine cpu plate, the first switch boards, the second switch boards and the 3rd switch boards are passed through total respectively
Gauze network is connected with integrated electronicses motherboard.Described control and testing board includes the first control and testing board and the second control and testing board, described first control and testing board
It is connected with integrated electronicses motherboard by bus network respectively with the second control and testing board.Described control and testing board is located at the machine of integrated electronicses unit
The side of case, is externally provided with observing and controlling receiving and transmitting front end and TT＆C antenna in the cabinet of the described integrated electronicses unit positioned at control and testing board side,
Described control and testing board is connected with described observing and controlling receiving and transmitting front end, and described observing and controlling receiving and transmitting front end is connected with TT＆C antenna.Pass through between module
STD bus interconnects, and is integrated in integrated synthesis electronic system, realizes the Star Service management of satellite, observing and controlling response, rail control
Calculate and control, power supply management, data processing and the function such as transmission and thermal control management.
Integrated Electronic System internal flow of information includes remote information stream, telemetry intelligence (TELINT) stream, thermal control flow of information sum biography information
Stream.Various information stream transmission processes are as follows:
(1) remote information stream
Remote information is sent to control module through up remote-control channel, through despreading, demodulation, deciphering after, direct instruction by
Answering machine directly decodes output, and for indirect instruction and upper note data block, control module gives spaceborne calculating by can Bus repeater
Machine module, after spaceborne computer module is processed further, gives each slave computer by can Bus repeater.
(2) telemetry intelligence (TELINT) stream
Telemetry intelligence (TELINT) gathers each bottom by spaceborne computer module by can bus, analog quantity interface, quantity of state interface etc.
The telemetry parameter of machine, is packed into telemetry by telemetry protocol, is sent to control module by can bus, through observing and controlling mould
The encryption of block, modulation, spread spectrum after, descend into ground.
(3) thermal control flow of information
In star, temperature is gathered by energy supply control module, re-sends to spaceborne computer module, by spaceborne computer module root
Require the break-make instruction of output heating circuit according to thermal control, energy supply control module executes specific computer heating control after receiving instruction.
(4) number passes flow of information
Digital transmission module passes through can bus record platform data, by lvds interface record load data, when satellite passes by
By the data readback of record, and x frequency range radio signal transmission is formed to ground by number transmission transmitter.
The specific embodiment of the above is better embodiment of the present utility model, not limits this practicality with this new
Type be embodied as scope, scope of the present utility model includes being not limited to this specific embodiment, all according to this utility model
Shape, the equivalence changes made of structure are all in protection domain of the present utility model.
Claims (7)
1. a kind of integration spaceborne Integrated Electronic System it is characterised in that: it includes integrated electronicses unit sum transmission transmitter,
Described integrated electronicses unit includes spaceborne computer module, control module, digital transmission module, energy supply control module, described spaceborne meter
Calculation machine module includes Star Service administrative unit, Attitude and orbit control unit and thermal control administrative unit；Described Attitude and orbit control
Unit and thermal control administrative unit are connected with spaceborne computer module；Described control module, digital transmission module, energy supply control module are respectively
It is connected with spaceborne computer module by bus network, described energy supply control module is passed through bus network and passed with control module, number
Module connects；Described digital transmission module is connected with number transmission transmitter.
2. according to claim 1 integration spaceborne Integrated Electronic System it is characterised in that: described integrated electronicses unit
Pass baseband board, spaceborne computer panel, switch boards, propulsion power board, io including integrated electronicses motherboard, power board, number
Plate, control and testing board, described power board, number pass baseband board, spaceborne computer panel, switch boards, propulsion power board, io plate,
Control and testing board is connected with integrated electronicses motherboard by bus network respectively；Described number is passed baseband board and is connected with number transmission transmitter, described
Number transmission transmitter passes through number and passes antenna transmission data.
3. according to claim 2 integration spaceborne Integrated Electronic System it is characterised in that: described power board bag
Include primary power source adjustable plate, secondary power supply and panel, power supply and thermal control management board, described primary power source adjustable plate, secondary electricity
Source is connected with integrated electronicses motherboard by bus network with thermal control management board respectively with panel, power supply.
4. according to claim 3 integration spaceborne Integrated Electronic System it is characterised in that: described number pass baseband board bags
Include the first number and pass baseband board, the second number biography baseband board, described first number passes baseband board, the second number passes baseband board respectively by bus
Network is connected with integrated electronicses motherboard；Described first number passes baseband board, the second number is passed baseband board and is connected with number transmission transmitter.
5. according to claim 3 integration spaceborne Integrated Electronic System it is characterised in that: described spaceborne computer control
Making sheet includes a machine cpu plate and b machine cpu plate, and described switch boards include the first switch boards, the second switch boards and the 3rd switch boards, institute
State a machine cpu plate, b machine cpu plate, the first switch boards, the second switch boards and the 3rd switch boards and pass through bus network and comprehensive electricity respectively
Mother baby plate connects.
6. integration according to claim 5 spaceborne Integrated Electronic System it is characterised in that: described control and testing board includes the
One control and testing board and the second control and testing board, described first control and testing board and the second control and testing board pass through bus network and integrated electronicses motherboard respectively
Connect.
7. according to claim 6 integration spaceborne Integrated Electronic System it is characterised in that: described control and testing board be located at comprehensive
Close the side of the cabinet of electronics unit, before the cabinet of the described integrated electronicses unit positioned at control and testing board side is externally provided with observing and controlling transmitting-receiving
End and TT＆C antenna, described control and testing board is connected with described observing and controlling receiving and transmitting front end, and described observing and controlling receiving and transmitting front end is connected with TT＆C antenna.
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| CN201620833483.8U CN205910547U (en) | 2016-08-03 | 2016-08-03 | Star of integration carries integration electronic system |
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Cited By (24)
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| CN107609210A (en) * | 2017-07-31 | 2018-01-19 | 中国空间技术研究院 | One kind is used for the emulation of spaceborne information system and verification platform |
| CN107741694A (en) * | 2017-11-20 | 2018-02-27 | 北京千乘探索科技有限公司 | A kind of satellite integrated controller |
| CN107957740A (en) * | 2017-11-15 | 2018-04-24 | 华南理工大学 | A kind of spaceborne temperature-controlling system using thermal conductive wire |
| CN108183741A (en) * | 2017-11-29 | 2018-06-19 | 山东航天电子技术研究所 | Electronic system on a kind of micro-nano satellite generalization star |
| CN108199759A (en) * | 2017-11-29 | 2018-06-22 | 山东航天电子技术研究所 | Electronic system on a kind of Satellite of multi cabin |
| CN108255772A (en) * | 2018-02-27 | 2018-07-06 | 北京微纳星空科技有限公司 | A kind of board computer system and micro-nano satellite |
| CN108932162A (en) * | 2018-06-14 | 2018-12-04 | 上海卫星工程研究所 | Multitask total management system and processing method based on integrated spaceborne computer |
| CN109002049A (en) * | 2018-06-26 | 2018-12-14 | 上海卫星工程研究所 | satellite platform based on modularized design |
| CN109002618A (en) * | 2018-07-25 | 2018-12-14 | 赛特雷德（重庆）科技有限公司 | A kind of spaceborne Integrated Electronic System the Automation Design method |
| CN109101452A (en) * | 2018-07-02 | 2018-12-28 | 上海卫星工程研究所 | Integrated Electronic System hardware structure design method suitable for deep space probe |
| CN109144945A (en) * | 2018-07-25 | 2019-01-04 | 赛特雷德（重庆）科技有限公司 | A kind of spaceborne Integrated Electronic System of flexibility of commercial presence satellite |
| CN109407573A (en) * | 2018-09-17 | 2019-03-01 | 西北工业大学 | A kind of CAN bus based moonlet Integrated Electronic System and method for allocating tasks |
| CN109634190A (en) * | 2019-01-21 | 2019-04-16 | 上海微小卫星工程中心 | Satellite processing terminal and satellite processing terminal design method |
| CN109669472A (en) * | 2018-12-26 | 2019-04-23 | 上海微小卫星工程中心 | A kind of generic concept star verification platform |
| CN109703784A (en) * | 2019-01-10 | 2019-05-03 | 深圳航天东方红海特卫星有限公司 | Microsatellite based on the comprehensive cabinet of integrated electric |
| CN110667896A (en) * | 2019-10-14 | 2020-01-10 | 深圳航天东方红海特卫星有限公司 | Micro-nano satellite integrated electronic system |
| CN110816889A (en) * | 2019-11-14 | 2020-02-21 | 中国科学院微小卫星创新研究院 | Remote sensing micro-nano satellite system |
| CN110837093A (en) * | 2019-11-14 | 2020-02-25 | 中国科学院微小卫星创新研究院 | Remote sensing micro-nano satellite integrated information processing platform |
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| CN111629548A (en) * | 2020-06-08 | 2020-09-04 | 中国电子科技集团公司第十四研究所 | Framework of satellite-borne high-integration secondary power supply |
| CN112859687A (en) * | 2021-01-13 | 2021-05-28 | 航天行云科技有限公司 | Integrated satellite integrated electronic system |
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| CN113610424A (en) * | 2021-08-18 | 2021-11-05 | 北京微纳星空科技有限公司 | Satellite full-function modularized simulation system, simulation processing method and electronic equipment |
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| CN107609210A (en) * | 2017-07-31 | 2018-01-19 | 中国空间技术研究院 | One kind is used for the emulation of spaceborne information system and verification platform |
| CN107957740A (en) * | 2017-11-15 | 2018-04-24 | 华南理工大学 | A kind of spaceborne temperature-controlling system using thermal conductive wire |
| CN107957740B (en) * | 2017-11-15 | 2023-03-10 | 华南理工大学 | Satellite-borne temperature control system using heat conducting wires |
| CN107741694A (en) * | 2017-11-20 | 2018-02-27 | 北京千乘探索科技有限公司 | A kind of satellite integrated controller |
| CN108183741A (en) * | 2017-11-29 | 2018-06-19 | 山东航天电子技术研究所 | Electronic system on a kind of micro-nano satellite generalization star |
| CN108199759A (en) * | 2017-11-29 | 2018-06-22 | 山东航天电子技术研究所 | Electronic system on a kind of Satellite of multi cabin |
| CN108199759B (en) * | 2017-11-29 | 2020-12-08 | 山东航天电子技术研究所 | Satellite onboard electronic system with multiple cabin sections |
| CN108183741B (en) * | 2017-11-29 | 2021-07-13 | 山东航天电子技术研究所 | Micro-nano satellite universal on-satellite electronic system |
| CN108255772B (en) * | 2018-02-27 | 2021-04-30 | 北京微纳星空科技有限公司 | Satellite-borne computer system and micro-nano satellite |
| CN108255772A (en) * | 2018-02-27 | 2018-07-06 | 北京微纳星空科技有限公司 | A kind of board computer system and micro-nano satellite |
| CN108932162A (en) * | 2018-06-14 | 2018-12-04 | 上海卫星工程研究所 | Multitask total management system and processing method based on integrated spaceborne computer |
| CN109002049A (en) * | 2018-06-26 | 2018-12-14 | 上海卫星工程研究所 | satellite platform based on modularized design |
| CN109101452B (en) * | 2018-07-02 | 2020-12-11 | 上海卫星工程研究所 | Design method of hardware architecture of integrated electronic system suitable for deep space probe |
| CN109101452A (en) * | 2018-07-02 | 2018-12-28 | 上海卫星工程研究所 | Integrated Electronic System hardware structure design method suitable for deep space probe |
| CN109144945A (en) * | 2018-07-25 | 2019-01-04 | 赛特雷德（重庆）科技有限公司 | A kind of spaceborne Integrated Electronic System of flexibility of commercial presence satellite |
| CN109002618A (en) * | 2018-07-25 | 2018-12-14 | 赛特雷德（重庆）科技有限公司 | A kind of spaceborne Integrated Electronic System the Automation Design method |
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| CN109669472A (en) * | 2018-12-26 | 2019-04-23 | 上海微小卫星工程中心 | A kind of generic concept star verification platform |
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| CN109634190A (en) * | 2019-01-21 | 2019-04-16 | 上海微小卫星工程中心 | Satellite processing terminal and satellite processing terminal design method |
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| CN110816889A (en) * | 2019-11-14 | 2020-02-21 | 中国科学院微小卫星创新研究院 | Remote sensing micro-nano satellite system |
| CN110816889B (en) * | 2019-11-14 | 2021-03-26 | 中国科学院微小卫星创新研究院 | Remote sensing micro-nano satellite system |
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