CN110667896A - Micro-nano satellite integrated electronic system - Google Patents
Micro-nano satellite integrated electronic system Download PDFInfo
- Publication number
- CN110667896A CN110667896A CN201910973228.1A CN201910973228A CN110667896A CN 110667896 A CN110667896 A CN 110667896A CN 201910973228 A CN201910973228 A CN 201910973228A CN 110667896 A CN110667896 A CN 110667896A
- Authority
- CN
- China
- Prior art keywords
- module
- control
- computer
- measurement
- board
- 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
Images
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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
Abstract
The invention provides a micro-nano satellite integrated electronic system which comprises a power supply module, a computer module, a measurement and control module, a GPS module and a measurement and control transceiving front end plate, wherein the power supply module, the computer module, the measurement and control module, the GPS module and the measurement and control transceiving front end plate are integrated in a case by adopting a box-type structure; the power module, the computer module, the measurement and control module, the GPS module and the measurement and control transceiving front end plate are connected by adopting an industrial connector based on a PC104 bus; an internal communication bus is adopted among the power module, the computer module, the measurement and control module, the GPS module and the measurement and control transceiving front end plate, so that the modules are conveniently interconnected and expanded. The invention has the beneficial effects that: 1. the micro/nano satellite integrated electronic system disclosed by the invention integrates the power supply module, the computer module, the measurement and control module, the GPS module and the measurement and control transceiving front end into a case by adopting a box-type structure, so that the space and the weight of a satellite are saved, the effective load weight ratio of the satellite can be improved, and the bearing capacity of the satellite is improved.
Description
Technical Field
The invention relates to the field of micro/nano satellites, in particular to a micro/nano satellite integrated electronic system.
Background
The spacecraft integrated electronic system is designed and developed under a unified system framework by the design concept of system engineering, can coordinate and control the orderly operation of each device of a spacecraft platform and an effective load, provides information exchange and processing for each device or module unit of the whole spacecraft, and uniformly provides an integrated system for energy management, temperature environment control and safe object handling.
The integrated electronic concept itself is not a completely new concept, and it has been accompanied with the development of aerospace technology and has been evolving with the progress of electronic technology. In the middle of the 70 s, the electronic technology level is low, the idea of integrating electronics is to focus on components, and relatively integrated electronic devices are used for completing relatively simple independent functions; 80. in the 90 s, the electronic technology level has been formed, devices with a certain integration level have been formed, the key point of integrated electronics is to realize relatively complex functions with relatively independent electronic systems, and the systems are mutually independent; from the end of the 90 s to the beginning of the 21 st century, along with the higher integration level of electronic devices, the key point of integrated electronics is to perform system integration on each large function of a spacecraft to form independent subsystems, so that interfaces of the subsystems are clearer, and the overall design and integration are facilitated; however, in the last decade, high-integration electronic devices are more and more mature, and system integration technologies are more and more stable, and the latest spacecraft has the capability of applying an integrated electronic concept at the level of the whole large system, so that multiple functions are uniformly realized in an integrated electronic system. The integrated electronic system can be more function-intensive, intelligent and flexible, and all subsystems can be fully fused, integrated and complemented, so that the whole spacecraft is designed more vigorously and optimally.
The structural mass of the traditional satellite accounts for about 25% of the net mass of the satellite, the mass of a cable system (cables, leads and connectors) generally accounts for 6% -10% of the total mass of the satellite, and 30% of the mass of the traditional satellite accounts for the mass proportion of interconnections such as welding, plugging and the like. It follows that to achieve a payload weight ratio of above 70%, new design methods must be employed to reduce the structure and cable quality.
The diversity of the general class of satellite equipment leads to more and more development units and more complex technical state. Under the background of diversity of satellite application requirements, a set of comprehensive electronic system architecture meeting the requirements of rapid development, rapid assembly and rapid application is constructed to form a trend, so that the uniqueness of an interconnection communication interface among satellite systems is realized.
The traditional satellite, the housekeeping computer, the control computer, the measurement and control transponder, the thermal control lower computer, the GPS receiver and the power supply adopt independent single machine design and are connected by a cable network, so the volume is large, the self weight is large, and the weight ratio of the satellite payload can not be improved.
The off-the-shelf boards are adopted, but the sizes and interfaces of the boards provided by suppliers are often difficult to unify. Meanwhile, the reliability of the space equipment is influenced by the space single particle locking effect.
Disclosure of Invention
The invention provides a micro-nano satellite integrated electronic system which comprises a power supply module, a computer module, a measurement and control module, a GPS module and a measurement and control transceiving front end plate, wherein the power supply module, the computer module, the measurement and control module, the GPS module and the measurement and control transceiving front end plate are integrated in a case by adopting a box-type structure; the power module, the computer module, the measurement and control module, the GPS module and the measurement and control transceiving front end plate are connected by adopting an industrial connector based on a PC104 bus; the power module, computer module observe and control the module GPS module observe and control and adopted the internal communication bus between the front end plate, be convenient for module interconnection and extension.
As a further improvement of the invention, the computer module, the power supply module, the GPS module and the measurement and control module are all designed by adopting dual-mode redundancy and a fault detection module.
As a further improvement of the invention, the computer module, the power supply module, the GPS module and the measurement and control module are all designed by adopting dual-mode redundancy and a fault detection module.
As a further improvement of the invention, the internal communication bus comprises CAN, UART, I2C. 485, 1_ wire, power supply interface, the internal communication bus can satisfy the connection of the power and the information of the integrated electronics.
As a further improvement of the invention, the computer module comprises an on-board computer, and the on-board computer integrates the functions of a satellite affair computer, a control computer and a thermal control lower computer.
As a further improvement of the invention, the on-board computer integrates a control DA output interface for outputting a control quantity to drive the magnetic torquer, integrates a thermal control management function, and integrates a temperature measurement sensor and a heating loop for controlling temperature.
As a further improvement of the invention, the micro/nano satellite integrated electronic system further comprises an adapter board, and the adapter board enables the 1U board card to be compatible with the 4U micro/nano satellite integrated electronic system.
As a further improvement of the present invention, the power supply module includes a power supply module lower-level board, a power supply module PCU board, and a power supply module distribution board.
As a further improvement of the invention, the on-board computer comprises an on-board computer module interface board and an on-board computer module function board.
The invention has the beneficial effects that: 1. the micro/nano satellite integrated electronic system disclosed by the invention integrates the power supply module, the computer module, the measurement and control module, the GPS module and the measurement and control transceiving front end into a case by adopting a box-type structure, so that the space and the weight of a satellite are saved, the weight ratio of effective loads of the satellite can be improved, and the bearing capacity of the satellite is improved; 2. the micro/nano satellite integrated electronic system disclosed by the invention adopts an industrial connector based on a PC104 bus to connect all board cards, so that cables are reduced, the weight ratio of effective loads of satellites is improved, and the bearing capacity of the satellites is improved; 3. the invention discloses a micro/nano satellite integrated electronic system, which designs a system fault tolerance method and can improve the adaptability of an industrial-grade board in a space environment.
Drawings
FIG. 1 is a block diagram of a micro/nano satellite integrated electronic system according to the invention;
FIG. 2 is an information flow diagram of a micro/nano satellite integrated electronic system.
Detailed Description
As shown in fig. 1-2, the invention discloses a micro/nano satellite integrated electronic system, which comprises a power module, a computer module, a measurement and control module, a GPS module and a measurement and control transceiving front end plate, wherein the power module, the computer module, the measurement and control module, the GPS module and the measurement and control transceiving front end plate are integrated in a case by adopting a box-type structure; the power module, the computer module, the measurement and control module, the GPS module and the measurement and control transceiving front end plate are connected by adopting an industrial connector based on a PC104 bus, and the PC104 series connectors are adopted to connect the modules, so that the power module has the advantages of light weight, good vibration resistance, large overcurrent and the like; the power module, computer module observe and control the module GPS module observe and control and adopted the internal communication bus between the front end plate, be convenient for module interconnection and extension.
The computer module, the power module, the GPS module and the measurement and control module are all designed by adopting dual-mode redundancy and a fault detection module, so that the comprehensive electronic reliability is improved.
The internal communication bus adopts a dual redundancy design, and the internal communication bus adopts system-level single event locking prevention based on current monitoring.
The internal communication bus comprises CAN, UART and I2C. 485, 1_ wire, power supply interface, the internal communication bus can satisfy the connection of the power and the information of the integrated electronics.
The micro-nano satellite integrated electronic system further comprises an on-board computer, and the on-board computer integrates the functions of a satellite computer, a control computer and a thermal control lower computer.
The satellite-borne computer integrates a control DA output interface for outputting control quantity to drive the magnetic torquer, integrates a thermal control management function, integrates a temperature measurement sensor and a heating loop for controlling temperature, and improves the integration level to reduce the volume, weight and power consumption of comprehensive electrons.
And monitoring the current of each module circuit by adopting a satellite-borne computer, wherein the number of current detection points in the micro/nano satellite integrated electronic system is up to more than 20. If local circuit single event locking occurs in a space environment, switching to a backup module, and if the computer per se generates the single event locking, the computer arbitration circuit autonomously switches the computer to be active and standby. Important data of each module are cross backed up, and the working state is not interrupted after the cutting machine.
The power module includes a power module lower computer board, a power module PCU board, and a power module distribution board.
The on-board computer comprises an on-board computer module interface board and an on-board computer module function board.
The micro-nano satellite integrated electronic system further comprises an adapter board, and the adapter board enables a 1U board card (1U standard PC104 function board) to be compatible with the 4U micro-nano satellite integrated electronic system, so that the adaptability and the expandability of the integrated electronic system are improved.
The invention discloses a micro-nano satellite integrated electronic system, and provides a satellite integrated electronic system which is high in integration level, small in size, light in weight, plug-and-play, universal and modular.
The micro/nano satellite integrated electronic system disclosed by the invention is used for space application, the integrated level of the integrated electronic is improved by adopting design, the load ratio of the satellite is enhanced, and the space adaptability is improved.
The micro-nano satellite integrated electronic system disclosed by the invention adopts a box-section type integrated electronic layout, can integrate more functions, has more advantages in function bearing and expansion, and is easier to control the interference inside the integrated electronic system in a shielding mode due to the adoption of the box-section type layout.
The micro/nano satellite integrated electronic system disclosed by the invention is designed with a system fault-tolerant structure, can obviously improve the adaptive capacity of the integrated electronic space environment, is designed with an internal bus standard with rich interfaces, and has strong universality.
The micro-nano satellite integrated electronic system disclosed by the invention adopts the PC104 series connectors to connect the modules, and has the advantages of light weight, good vibration resistance, large overcurrent and the like.
The invention has the beneficial effects that: 1. the micro/nano satellite integrated electronic system disclosed by the invention integrates the power supply module, the computer module, the measurement and control module, the GPS module and the measurement and control transceiving front end into a case by adopting a box-type structure, so that the space and the weight of a satellite are saved, the weight ratio of effective loads of the satellite can be improved, and the bearing capacity of the satellite is improved; 2. the micro/nano satellite integrated electronic system disclosed by the invention adopts an industrial connector based on a PC104 bus to connect all board cards, so that cables are reduced, the weight ratio of effective loads of satellites is improved, and the bearing capacity of the satellites is improved; 3. the invention discloses a micro/nano satellite integrated electronic system, which designs a system fault tolerance method and can improve the adaptability of an industrial-grade board in a space environment.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (9)
1. A micro-nano satellite integrated electronic system is characterized by comprising a power module, a computer module, a measurement and control module, a GPS module and a measurement and control transceiving front end plate, wherein the power module, the computer module, the measurement and control module, the GPS module and the measurement and control transceiving front end plate are integrated in a case by adopting a box-type structure; the power module, the computer module, the measurement and control module, the GPS module and the measurement and control transceiving front end plate are connected by adopting an industrial connector based on a PC104 bus; the power module, computer module observe and control the module GPS module observe and control and adopted the internal communication bus between the front end plate, be convenient for module interconnection and extension.
2. A micro-nano satellite integrated electronic system according to claim 1, wherein the computer module, the power supply module, the GPS module and the measurement and control module are of a dual-mode redundancy design and a fault detection module.
3. The micro-nano satellite integrated electronic system according to any one of claims 1 or 2, wherein the internal communication bus adopts a dual redundancy design, and the internal communication bus adopts system-level single event locking prevention based on current monitoring.
4. A micro-nano satellite integrated electronic system according to claim 3, wherein the internal communication bus comprises CAN, UART, I2C. 485, 1_ wire, power supply interface, the internal communication bus can satisfy the connection of the power and the information of the integrated electronics.
5. A micro-nano satellite integrated electronic system according to claim 1, wherein the computer module comprises an on-board computer, and the on-board computer integrates functions of a housekeeping computer, a control computer and a thermal control lower computer.
6. A micro-nano satellite integrated electronic system according to claim 5, wherein the on-board computer integrates a control DA output interface for outputting a control quantity to drive the magnetic torquer, integrates a thermal control management function, and integrates a temperature measurement sensor and a heating loop temperature control.
7. The integrated electronic system according to claim 1, further comprising an adapter board, wherein the adapter board is used for enabling 1U board card to be compatible with a 4U integrated electronic system.
8. A micro-nano satellite integrated electronic system according to claim 1, wherein the power supply module comprises a power supply module lower computer board, a power supply module PCU board and a power supply module distribution board.
9. A micro-nano satellite integrated electronic system according to claim 5, wherein the on-board computer comprises an on-board computer module interface board and an on-board computer module function board.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910973228.1A CN110667896A (en) | 2019-10-14 | 2019-10-14 | Micro-nano satellite integrated electronic system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910973228.1A CN110667896A (en) | 2019-10-14 | 2019-10-14 | Micro-nano satellite integrated electronic system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110667896A true CN110667896A (en) | 2020-01-10 |
Family
ID=69082406
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910973228.1A Pending CN110667896A (en) | 2019-10-14 | 2019-10-14 | Micro-nano satellite integrated electronic system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110667896A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116400580A (en) * | 2023-06-08 | 2023-07-07 | 上海航天空间技术有限公司 | Multi-redundancy control integrated electronic system and implementation method |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1760676A (en) * | 2004-10-14 | 2006-04-19 | 中国科学院空间科学与应用研究中心 | A kind of detector and method that detects capability of microprocessor for anti event of single particle |
| CN201115118Y (en) * | 2007-07-19 | 2008-09-10 | 上海航天局第八○九研究所 | Satellite electronic system standalone device |
| CN103064392A (en) * | 2012-12-28 | 2013-04-24 | 中国人民解放军国防科学技术大学 | Satellite borne integrated electronic system |
| CN103777526A (en) * | 2014-03-03 | 2014-05-07 | 上海科梁信息工程有限公司 | Simulation testing system of integrated electronic system of satellite |
| CN103944629A (en) * | 2014-04-28 | 2014-07-23 | 航天东方红卫星有限公司 | Satellite integrated electronic system |
| CN104460427A (en) * | 2014-10-31 | 2015-03-25 | 上海卫星工程研究所 | Integrated electronic system for modular microsatellite platform |
| CN104484272A (en) * | 2014-12-10 | 2015-04-01 | 深圳航天东方红海特卫星有限公司 | Satellite borne electronic system capable of being debugged on orbit and on-orbit debugging method |
| CN205910547U (en) * | 2016-08-03 | 2017-01-25 | 深圳航天东方红海特卫星有限公司 | Star of integration carries integration electronic system |
| CN108052420A (en) * | 2018-01-08 | 2018-05-18 | 哈尔滨工业大学 | Double-core arm processor anti-single particle overturning means of defence based on Zynq-7000 |
| CN108153183A (en) * | 2017-12-05 | 2018-06-12 | 山东航天电子技术研究所 | Integrated Electronic System on a kind of high functional density star of microminiature |
| 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 |
| US20180197038A1 (en) * | 2017-01-09 | 2018-07-12 | Commissariat A L'energie Atomique Et Aux Energies Alternatives | On-the-fly processing of data in an acouisition system |
| CN109240959A (en) * | 2018-09-13 | 2019-01-18 | 垣纬多媒体卫星通信（上海）有限公司 | A kind of spaceborne Integrated Electronic System |
-
2019
- 2019-10-14 CN CN201910973228.1A patent/CN110667896A/en active Pending
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1760676A (en) * | 2004-10-14 | 2006-04-19 | 中国科学院空间科学与应用研究中心 | A kind of detector and method that detects capability of microprocessor for anti event of single particle |
| CN201115118Y (en) * | 2007-07-19 | 2008-09-10 | 上海航天局第八○九研究所 | Satellite electronic system standalone device |
| CN103064392A (en) * | 2012-12-28 | 2013-04-24 | 中国人民解放军国防科学技术大学 | Satellite borne integrated electronic system |
| CN103777526A (en) * | 2014-03-03 | 2014-05-07 | 上海科梁信息工程有限公司 | Simulation testing system of integrated electronic system of satellite |
| CN103944629A (en) * | 2014-04-28 | 2014-07-23 | 航天东方红卫星有限公司 | Satellite integrated electronic system |
| CN104460427A (en) * | 2014-10-31 | 2015-03-25 | 上海卫星工程研究所 | Integrated electronic system for modular microsatellite platform |
| CN104484272A (en) * | 2014-12-10 | 2015-04-01 | 深圳航天东方红海特卫星有限公司 | Satellite borne electronic system capable of being debugged on orbit and on-orbit debugging method |
| CN205910547U (en) * | 2016-08-03 | 2017-01-25 | 深圳航天东方红海特卫星有限公司 | Star of integration carries integration electronic system |
| US20180197038A1 (en) * | 2017-01-09 | 2018-07-12 | Commissariat A L'energie Atomique Et Aux Energies Alternatives | On-the-fly processing of data in an acouisition system |
| 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 |
| CN108153183A (en) * | 2017-12-05 | 2018-06-12 | 山东航天电子技术研究所 | Integrated Electronic System on a kind of high functional density star of microminiature |
| CN108052420A (en) * | 2018-01-08 | 2018-05-18 | 哈尔滨工业大学 | Double-core arm processor anti-single particle overturning means of defence based on Zynq-7000 |
| CN109240959A (en) * | 2018-09-13 | 2019-01-18 | 垣纬多媒体卫星通信（上海）有限公司 | A kind of spaceborne Integrated Electronic System |
Non-Patent Citations (1)
| Title |
|---|
| 丛佃伟: "《GNSS高动态定位性能检定理论及关键技术研究》", 31 January 2017, 测绘出版社 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116400580A (en) * | 2023-06-08 | 2023-07-07 | 上海航天空间技术有限公司 | Multi-redundancy control integrated electronic system and implementation method |
| CN116400580B (en) * | 2023-06-08 | 2023-08-08 | 上海航天空间技术有限公司 | Multi-redundancy control integrated electronic system and implementation method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101071327B (en) | Modular electronic systems and methods using flexible power distribution unit interface | |
| CN102122276B (en) | Double-processor borne computer | |
| CN102662904B (en) | Plug-and-play system based on controller area network (CAN) bus and design method thereof | |
| CN111309477A (en) | Satellite on-orbit data processing system and method | |
| US11404905B2 (en) | Self configuring modular electrical system | |
| CN110187657B (en) | Electromechanical integrated intelligent backboard satellite architecture | |
| CN103822539B (en) | A kind of rocket ground test control system based on redundancy structure | |
| CN107112795B (en) | Modular uninterruptible power supply and power distribution system | |
| CN112046787A (en) | Domain-based microsatellite system | |
| CN217904243U (en) | Adapter for aerospace | |
| CN110667896A (en) | Micro-nano satellite integrated electronic system | |
| CN104691761A (en) | Multi-mode hybrid power supply system and method for ICP (integrated core processor) | |
| CN111506044A (en) | General off-line detection device for spacecraft | |
| CN103901881A (en) | Device compatible with multiple test states for carrier rocket equivalent device system | |
| CN209895300U (en) | Power supply adapter plate applied to power supply of server | |
| CN108199759B (en) | Satellite onboard electronic system with multiple cabin sections | |
| CN112072778A (en) | Power distribution management system and method for double-engine aircraft | |
| CN111682644A (en) | Power management system based on manned and unmanned modification | |
| CN117639908B (en) | Space-based intelligent network connection device based on VPX architecture | |
| Boncyk | Developing a distributed power and grounding architecture for PnPSat | |
| Özkaya et al. | Next Generation power distribution module featuring uygar | |
| CN203786493U (en) | Connect-and-use onboard integrated processing platform debug and maintenance interface module | |
| CN219105480U (en) | Block chain processing module for airborne operation environment | |
| Oeftering | Standardized Modular Power Interfaces for Future Space Explorations Missions | |
| Senior et al. | A space wire active backplane specification for space systems |
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: 20200110 |
|
| RJ01 | Rejection of invention patent application after publication |