CN108199759B - Satellite onboard electronic system with multiple cabin sections - Google Patents
Satellite onboard electronic system with multiple cabin sections Download PDFInfo
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- CN108199759B CN108199759B CN201711221332.2A CN201711221332A CN108199759B CN 108199759 B CN108199759 B CN 108199759B CN 201711221332 A CN201711221332 A CN 201711221332A CN 108199759 B CN108199759 B CN 108199759B
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18515—Transmission equipment in satellites or space-based relays
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L12/00—Data switching networks
- H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
- H04L12/40—Bus networks
- H04L12/40006—Architecture of a communication node
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L12/00—Data switching networks
- H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
- H04L12/40—Bus networks
- H04L2012/40208—Bus networks characterized by the use of a particular bus standard
- H04L2012/40215—Controller Area Network CAN
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Abstract
The invention discloses a multi-cabin satellite onboard electronic system, which solves the problems of high impedance matching error rate and low integration efficiency of the multi-cabin satellite onboard electronic system. The system includes a platform bay, a load bay, and a propulsion bay. A platform cabin bus is adopted in the platform cabin for communication, and a platform cabin computing unit is used as a main node of the platform cabin bus; the left end and the right end of the platform cabin are respectively provided with a platform cabin matching resistor which is connected to the platform cabin bus. A load cabin bus is adopted in the load cabin for communication, and a load cabin computing unit is used as a main node of the load cabin bus; and load compartment matching resistors are connected in parallel inside the load compartment calculation unit. A propulsion cabin bus is adopted in the propulsion cabin for communication, and a propulsion cabin computing unit is used as a main node of the propulsion cabin bus; and the propulsion cabin computing unit is internally connected with a propulsion cabin matching resistor in parallel. When the cabin sections are in a combined state, the load cabin calculation unit and the propulsion cabin calculation unit are connected to the platform cabin bus, and the platform cabin matching resistor is disconnected from the platform cabin bus.
Description
Technical Field
The invention relates to the technical field of satellite electronic systems, in particular to a multi-cabin satellite on-satellite electronic system.
Background
The multi-cabin fast assembly satellite is normally stored in a launching base or an equipment storehouse in a cabin mode, and cabin-level tests are regularly carried out; when a task is required, the whole star is assembled by temporary quick assembly, parameter binding, upper note software and the like, and quick launching, quick orbit entering and quick application are realized.
At present, the architecture of the on-board electronic system mostly adopts a star-based centralized system architecture and a bus-based distributed system architecture. The star-based centralized system architecture is mainly used for a micro spacecraft, and mainly takes a satellite-borne computer as a core, various interfaces are expanded to connect various sensors and actuating mechanisms, and the satellite-borne computer is used as a management and control core of the system. The distributed system architecture based on the bus is mainly used for large-scale spacecrafts, the expandability is good, the equipment is networked through the system control bus, in practical application, a satellite computer or a control computer is generally used as a manager of the satellite-borne bus, the system adopts a master-slave operation control mode, and node equipment on the bus respectively considers the redundancy backup design of the node equipment.
The CAN bus matching impedance is generally realized by increasing matching resistors at two ends of a CAN bus network, and is usually realized by inserting an impedance matching connector into the CAN bus connector of the equipment at the two ends. Fig. 1 shows a small satellite CAN bus connection method and a matching resistor installation method.
The multi-cabin fast assembly satellite onboard electronic system architecture can flexibly adapt to expansion and cutting of cabin levels, and not only supports information interaction and energy supply in independent cabins, but also supports information interaction and energy supply across cabins.
In the multi-cabin combination process, because the grid connection process of the CAN bus is involved, generally speaking, the matching resistor of the CAN bus needs to be placed at two nodes at the farthest end, so that the position of the matching impedance needs to be adjusted when the CAN bus is connected to the grid, manual operation is needed, errors are easily caused, and the integration efficiency of the satellite onboard electronic system is greatly reduced.
Disclosure of Invention
In view of this, the invention provides a multi-cabin satellite onboard electronic system, provides a topological structure suitable for the multi-cabin satellite onboard electronic system, and solves the problems of high impedance matching error rate and low integration efficiency of the multi-cabin satellite onboard electronic system.
The technical scheme of the invention is as follows: a multi-cabin satellite onboard electronic system comprises a platform cabin, a load cabin and a propulsion cabin, and the system has a cabin independent state and a cabin combined state.
The system comprises a platform cabin, a satellite attitude control unit, a satellite energy management unit and a satellite energy management unit, wherein the platform cabin is internally provided with a platform cabin computing unit and a first functional module for satellite attitude control and satellite energy management; a platform cabin bus is adopted in the platform cabin for communication, and a platform cabin computing unit is used as a main node of the platform cabin bus; the left end and the right end of the platform cabin are respectively provided with a platform cabin matching resistor, and the platform cabin matching resistors are connected to a platform cabin bus.
The load cabin is internally provided with a load cabin calculation unit and a second functional module for processing load data; a load cabin bus is adopted in the load cabin for communication, and a load cabin computing unit is used as a main node of the load cabin bus; and load compartment matching resistors are connected in parallel inside the load compartment calculation unit.
The propulsion cabin is internally provided with a propulsion cabin computing unit and a third functional module for controlling the propulsion of the propulsion cabin; a propulsion cabin bus is adopted in the propulsion cabin for communication, and a propulsion cabin computing unit is used as a main node of the propulsion cabin bus; and the propulsion cabin computing unit is internally connected with a propulsion cabin matching resistor in parallel.
When the cabin sections are in an independent state, the platform cabin, the load cabin and the propulsion cabin are independent respectively.
When the cabin sections are in a combined state, the load cabin calculation unit and the propulsion cabin calculation unit are connected to the platform cabin bus, and the platform cabin matching resistor is disconnected from the platform cabin bus.
Furthermore, the platform cabin bus, the load cabin bus and the propulsion cabin bus all adopt CAN buses.
Furthermore, the end faces of the left end and the right end of the platform cabin further comprise a travel switch, and the travel switch is used for controlling the connection and disconnection between the platform cabin matching resistor at the end where the travel switch is located and a platform cabin bus.
The load cabin computing unit is internally provided with a load cabin relay, the load cabin relay is connected with the load cabin matching resistor in series, and the load cabin computing unit controls the load cabin relay.
The end face of the tail end of the load cabin further comprises load cabin combined signal detection equipment, and the load cabin combined signals are detected and sent to a load cabin calculation unit.
The propulsion cabin computing unit is internally provided with a propulsion cabin relay, the propulsion cabin relay is connected with the propulsion cabin matching resistor in series, and the propulsion cabin computing unit controls the propulsion cabin relay.
The end face of the tail end of the propulsion cabin further comprises propulsion cabin combined signal detection equipment, and the propulsion cabin combined signals are detected and then sent to a propulsion cabin calculation unit.
When the cabin sections are in an independent state, the travel switches are not tightly pressed and are in a closed state, and the platform cabin matching resistors are connected to the platform cabin bus; the load cabin computing unit controls the load cabin relay to be disconnected; and the propulsion cabin calculation unit controls the propulsion cabin relay to be disconnected.
When the cabin section is in a combined state, the end face of the tail end of the load cabin and the end face of the tail end of the propulsion cabin are respectively in contact combination with the end faces of the left and right tail ends of the platform cabin, the travel switch is pressed to be disconnected, and then the matching resistor of the platform cabin is disconnected; the load cabin computing unit and the propulsion cabin computing unit are both connected to the platform cabin bus, the load cabin combined signal detection equipment detects a load cabin combined signal and then sends the load cabin combined signal to the load cabin computing unit, and the load cabin computing unit controls the load cabin relay to be closed after receiving the load cabin combined signal, so that the load cabin matching resistance is connected to the platform cabin bus; and the propulsion cabin combination signal detection equipment detects a propulsion cabin combination signal and then sends the propulsion cabin combination signal to the propulsion cabin calculation unit, and the propulsion cabin calculation unit controls the propulsion cabin relay to be closed according to the received propulsion cabin combination signal, so that the propulsion cabin matching resistor is connected to the platform cabin bus.
Furthermore, the load cabin combined signal detection equipment and the propulsion cabin combined signal detection equipment both adopt travel switches.
Has the advantages that:
the invention provides a topological structure of a multi-cabin satellite onboard electronic system, which can be used for constructing a multi-cabin combined satellite onboard electronic system, and equipment is interconnected through a bus, so that the expansion and cutting of the system are facilitated; the satellite on-satellite electronic system provided by the invention can perform automatic impedance matching, replaces manual operation, reduces the possibility of introducing errors by manual operation, and improves the integration efficiency of the satellite system.
Drawings
Fig. 1 is a schematic block diagram of the matched impedance installation of an electronic system on a small satellite.
Fig. 2 is a topological structure diagram of a multi-cabin satellite onboard electronic system according to an embodiment of the present invention.
Fig. 3 is a combined state diagram of a multi-cabin satellite onboard electronic system according to an embodiment of the present invention.
Fig. 4 is a topological structure diagram of a multi-bay satellite onboard electronic system according to another embodiment of the present invention.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
Example 1
The embodiment of the invention provides a multi-cabin satellite onboard electronic system, a topological structure of the system is shown in figure 2, the system comprises a platform cabin, a load cabin and a propulsion cabin, and the system has a cabin independent state and a cabin combined state.
The system comprises a platform cabin, a satellite attitude control unit, a satellite energy management unit and a satellite energy management unit, wherein the platform cabin is internally provided with a platform cabin computing unit and a first functional module for satellite attitude control and satellite energy management; a platform cabin bus is adopted in the platform cabin for communication, and a platform cabin computing unit is used as a main node of the platform cabin bus; the left end and the right end of the platform cabin are respectively provided with a platform cabin matching resistor, and the platform cabin matching resistors are connected to a platform cabin bus.
The load cabin is internally provided with a load cabin calculation unit and a second functional module for processing load data; a load cabin bus is adopted in the load cabin for communication, and a load cabin computing unit is used as a main node of the load cabin bus; and load compartment matching resistors are connected in parallel inside the load compartment calculation unit.
The propulsion cabin is internally provided with a propulsion cabin computing unit and a third functional module for controlling the propulsion of the propulsion cabin; a propulsion cabin bus is adopted in the propulsion cabin for communication, and a propulsion cabin computing unit is used as a main node of the propulsion cabin bus; the inside of the propulsion cabin computing unit is connected with a propulsion cabin matching resistor in parallel;
when the cabin sections are in an independent state, the platform cabin, the load cabin and the propulsion cabin are independent respectively. When the platform cabin, the load cabin and the propelling cabin are independently stored, tasks such as data management, parameter binding configuration, rapid test support and the like of the cabin can be completed through respective computing units and buses.
When the cabin sections are in a combined state, the load cabin calculation unit and the propulsion cabin calculation unit are connected to the platform cabin bus, and the platform cabin matching resistor is disconnected from the platform cabin bus. After the cabin section combination is completed, the platform cabin computing unit is used as a main node of a platform cabin bus, and the load cabin computing unit and the propulsion cabin computing unit are used as slave nodes of the platform cabin bus.
In the embodiment of the invention, the platform cabin bus, the load cabin bus and the propulsion cabin bus adopt CAN buses.
In the embodiment of the invention, in the process of combining multiple cabin segments, the grid connection problem of a system CAN bus is involved, the system CAN bus is additionally provided with two nodes, namely a propulsion cabin satellite-borne computing unit (OBC) and a load cabin satellite-borne computing unit (OBC), and after grid connection, the nodes are positioned at the farthest end of the system CAN bus and need to be subjected to impedance matching again, which requires that: shielding or short-circuiting two matching resistors on a CAN bus of an original platform cabin system; and secondly, switching in the matching resistor again at the newly added node. According to the analysis, the impedance matching method for automatically realizing CAN bus grid connection by adopting the travel switch and the relay is provided to replace the conventional method for manually plugging and unplugging the CAN bus impedance matching plug, so that the manual operation links in the assembling process are reduced, and the integration process is accelerated. The implementation process and principle are shown in fig. 3:
the end faces of the left and right tail ends of the platform cabin further comprise a travel switch, and the travel switch is used for controlling the connection and disconnection between the platform cabin matching resistor at the tail end and a platform cabin bus;
the load cabin computing unit also comprises a load cabin relay, the load cabin relay is connected with the load cabin matching resistor in series, and the load cabin computing unit controls the load cabin relay;
the end face of the tail end of the load cabin also comprises load cabin combined signal detection equipment, and the load cabin combined signal is detected and sent to a load cabin calculation unit;
the propulsion cabin computing unit is internally provided with a propulsion cabin relay, the propulsion cabin relay is connected with the propulsion cabin matching resistor in series, and the propulsion cabin computing unit controls the propulsion cabin relay;
the end surface of the tail end of the propulsion cabin also comprises propulsion cabin combined signal detection equipment, and the propulsion cabin combined signal is detected and then sent to a propulsion cabin calculation unit;
when the cabin sections are in an independent state, the travel switches are not tightly pressed and are in a closed state, and the platform cabin matching resistors are connected to the platform cabin bus; the load cabin computing unit controls the load cabin relay to be disconnected; the propulsion cabin computing unit controls the propulsion cabin relay to be disconnected;
when the cabin section is in a combined state, the end face of the tail end of the load cabin and the end face of the tail end of the propulsion cabin are respectively in contact combination with the end faces of the left and right tail ends of the platform cabin, the travel switch is pressed to be disconnected, and then the matching resistor of the platform cabin is disconnected; the load cabin computing unit and the propulsion cabin computing unit are both connected to the platform cabin bus, the load cabin combined signal detection equipment detects a load cabin combined signal and then sends the load cabin combined signal to the load cabin computing unit, and the load cabin computing unit controls the load cabin relay to be closed after receiving the load cabin combined signal, so that the load cabin matching resistance is connected to the platform cabin bus; and the propulsion cabin combination signal detection equipment detects a propulsion cabin combination signal and then sends the propulsion cabin combination signal to the propulsion cabin calculation unit, and the propulsion cabin calculation unit controls the propulsion cabin relay to be closed according to the received propulsion cabin combination signal, so that the propulsion cabin matching resistor is connected to the platform cabin bus.
The load cabin combined signal detection equipment and the propulsion cabin combined signal detection equipment both adopt travel switches. The combined state of the load cabin can be determined by acquiring a state signal generated by a travel switch of the load cabin by a load cabin computing unit; the combined state of the propulsion pods can be determined by the pod computing unit acquiring state signals generated by travel switches of the propulsion pods.
The topological structure of the multi-cabin satellite onboard electronic system provided by the embodiment of the invention can be used for constructing the multi-cabin combined satellite onboard electronic system, and the devices are interconnected through the bus, so that the expansion and cutting of the system are facilitated; the satellite on-satellite electronic system provided by the invention can perform automatic impedance matching, replaces manual operation, reduces the possibility of introducing errors by manual operation, and improves the integration efficiency of the satellite system.
Example 2
Based on the foregoing embodiment 1, this embodiment provides a specific implementation manner of each functional module, and fig. 4 shows a topology structure diagram of the satellite onboard electronic system provided in this embodiment. As shown in fig. 4:
in the embodiment of the invention, the first functional module is a functional module for realizing satellite attitude control and satellite energy management, and is the same as the conventional satellite electronic system. In an actual on-board electronic system, the first functional module may generally include an attitude and orbit control functional sub-module, an on-board energy management sub-module and a comprehensive information processing sub-module;
the attitude and orbit control functional sub-module comprises an attitude sensor, an attitude and orbit control actuating mechanism, an attitude and orbit control propelling component and an attitude and orbit control secondary power supply; the attitude and orbit control actuating mechanism is used for carrying out attitude and orbit control according to the attitude and orbit control instruction, the attitude and orbit control propelling component is used for controlling the propeller according to the attitude and orbit control instruction, and the attitude and orbit control secondary power supply is used for supplying power to the attitude and orbit control functional submodule.
The satellite energy management submodule comprises a power management unit, a power control unit PCU, a primary power distribution unit, a storage battery pack, a solar battery array, an initiating explosive device management unit and an energy management secondary power supply; the power management unit and the power control unit PCU are used for sending energy storage power supply information in the storage battery pack and the solar battery array to the platform cabin computing unit, managing and controlling the energy storage power supply in the storage battery pack and the solar battery array according to an energy control instruction of the platform cabin computing unit, the primary power distribution unit is used for performing primary power distribution on the energy storage power supply in the storage battery pack and the solar battery array, the storage battery pack and the solar battery array are energy storage equipment, the initiating explosive device management unit is used for managing energy use of on-satellite initiating explosive devices, and the energy management secondary power supply is used for providing power supply for the on-satellite energy management submodule.
The comprehensive information processing submodule is used for carrying out comprehensive information processing and comprises a plurality of comprehensive radio frequency units, a platform interface unit and a comprehensive secondary power supply; the integrated radio frequency unit is used for carrying out radio frequency processing, the platform interface unit is used for providing a platform interface, and the integrated secondary power supply is used for supplying power to the integrated information processing submodule.
The platform cabin calculation unit is communicated with the attitude and orbit control function submodule and the satellite energy management submodule through a platform cabin bus, on one hand, the attitude information is received, the energy information is obtained, on the other hand, an attitude and orbit control instruction or an energy control instruction is obtained through comprehensive calculation, and management and control of the attitude and orbit control function submodule and the satellite energy management submodule are achieved.
The second functional module in the embodiment of the invention is a functional module for realizing load data processing, and is the same as the existing on-board electronic system. In a practical satellite electronic system, the second functional module may generally include a data processing unit, a routing and storage unit, an integrated radio frequency unit, a load compartment interface unit, and a load compartment secondary power supply. The data processing unit is used for processing the load data, the routing and storage unit is used for routing and storing the load data, the load data comprehensive radio frequency unit is used for carrying out radio frequency emission on the load data, the load cabin interface unit is used for providing a load cabin interface, and the load cabin secondary power supply is used for providing a secondary power supply for the functional module in the load cabin.
The third functional module in the embodiment of the invention is a functional module for realizing propulsion control, and is the same as the existing onboard satellite electronic system. In a practical onboard electronic system, the third functional module may typically comprise a propulsion interface unit for providing an interface to a propulsion assembly, the propulsion pod secondary power supply being used to provide secondary power to the functional module within the propulsion pod.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (1)
1. A multi-cabin satellite onboard electronic system is characterized by comprising a platform cabin, a load cabin and a propulsion cabin, wherein the system has a cabin independent state and a cabin combined state;
the system comprises a platform cabin, a satellite attitude control module, a satellite energy management module and a satellite energy management module, wherein the platform cabin is internally provided with a platform cabin computing unit and a first functional module for satellite attitude control and satellite energy management; a platform cabin bus is adopted in the platform cabin for communication, and the platform cabin computing unit is used as a main node of the platform cabin bus; the left end and the right end of the platform cabin are respectively provided with a platform cabin matching resistor, and the platform cabin matching resistors are connected to the platform cabin bus;
the load cabin is internally provided with a load cabin calculation unit and a second functional module for processing load data; a load cabin bus is adopted in the load cabin for communication, and the load cabin computing unit is used as a main node of the load cabin bus; load cabin matching resistors are connected in parallel inside the load cabin computing unit;
the propulsion cabin is internally provided with a propulsion cabin computing unit and a third functional module for controlling the propulsion of the propulsion cabin; a propulsion cabin bus is adopted in the propulsion cabin for communication, and the propulsion cabin computing unit is used as a main node of the propulsion cabin bus; the propulsion cabin computing unit is internally connected with a propulsion cabin matching resistor in parallel;
when the cabin sections are in an independent state, the platform cabin, the load cabin and the propulsion cabin are independent respectively;
when the cabin section is in a combined state, the load cabin computing unit and the propulsion cabin computing unit are connected to the platform cabin bus, and the platform cabin matching resistor is disconnected from the platform cabin bus;
the platform cabin bus, the load cabin bus and the propulsion cabin bus are all CAN buses;
the end faces of the left and right tail ends of the platform cabin further comprise a travel switch, and the travel switch is used for controlling the connection and disconnection between the platform cabin matching resistor at the tail end and the platform cabin bus;
the load cabin computing unit is internally provided with a load cabin relay, the load cabin relay is connected with the load cabin matching resistor in series, and the load cabin computing unit controls the load cabin relay;
the end face of the tail end of the load cabin further comprises load cabin combined signal detection equipment, and the load cabin combined signal is detected and sent to the load cabin calculation unit;
the propulsion cabin computing unit is internally provided with a propulsion cabin relay, the propulsion cabin relay is connected with the propulsion cabin matching resistor in series, and the propulsion cabin computing unit controls the propulsion cabin relay;
the end surface of the tail end of the propulsion cabin further comprises propulsion cabin combined signal detection equipment, and the propulsion cabin combined signal is sent to the propulsion cabin calculation unit after being detected;
when the cabin sections are in an independent state, the travel switches are not tightly pressed and are in a closed state, and then the platform cabin matching resistors are connected to the platform cabin bus; the load compartment computing unit controls the load compartment relay to be disconnected; the propulsion cabin computing unit controls the propulsion cabin relay to be disconnected;
when the cabin section is in a combined state, the end surface of the tail end of the load cabin and the end surface of the tail end of the propulsion cabin are respectively in contact combination with the end surfaces of the left and right tail ends of the platform cabin, the travel switch is pressed to be disconnected, and then the platform cabin matching resistor is disconnected; the load compartment computing unit and the propulsion compartment computing unit are both connected to the platform compartment bus, the load compartment combined signal detection equipment detects a load compartment combined signal and sends the load compartment combined signal to the load compartment computing unit, and the load compartment computing unit controls the load compartment relay to be closed after receiving the load compartment combined signal, so that the load compartment matching resistance is connected to the platform compartment bus; the propulsion cabin combination signal detection equipment detects a propulsion cabin combination signal and then sends the propulsion cabin combination signal to the propulsion cabin calculation unit, and the propulsion cabin calculation unit controls the propulsion cabin relay to be closed according to the received propulsion cabin combination signal, so that the propulsion cabin matching resistor is connected to the platform cabin bus;
the load cabin combined signal detection equipment and the propulsion cabin combined signal detection equipment both adopt travel switches.
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101727431A (en) * | 2009-12-15 | 2010-06-09 | 杭州华三通信技术有限公司 | Bus impedance self-adaptive matching method and equipment thereof |
| US8016240B2 (en) * | 2007-03-29 | 2011-09-13 | The Boeing Company | Satellites and satellite fleet implementation methods and apparatus |
| CN202217270U (en) * | 2011-09-01 | 2012-05-09 | 中国空间技术研究院 | Bus for useful load subsystem data transmission |
| CN103253381B (en) * | 2013-05-17 | 2015-04-15 | 北京空间飞行器总体设计部 | Grounding design method of multi-cabin combined type spacecraft |
| CN204697075U (en) * | 2015-06-24 | 2015-10-07 | 安徽江淮汽车股份有限公司 | A kind of CAN terminal resistance control device |
| CN105072008A (en) * | 2015-07-31 | 2015-11-18 | 上海卫星工程研究所 | Bus topology-based modularized satellite platform electronic integrated information processing system |
| 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 |
-
2017
- 2017-11-29 CN CN201711221332.2A patent/CN108199759B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8016240B2 (en) * | 2007-03-29 | 2011-09-13 | The Boeing Company | Satellites and satellite fleet implementation methods and apparatus |
| CN101727431A (en) * | 2009-12-15 | 2010-06-09 | 杭州华三通信技术有限公司 | Bus impedance self-adaptive matching method and equipment thereof |
| CN202217270U (en) * | 2011-09-01 | 2012-05-09 | 中国空间技术研究院 | Bus for useful load subsystem data transmission |
| CN103253381B (en) * | 2013-05-17 | 2015-04-15 | 北京空间飞行器总体设计部 | Grounding design method of multi-cabin combined type spacecraft |
| CN204697075U (en) * | 2015-06-24 | 2015-10-07 | 安徽江淮汽车股份有限公司 | A kind of CAN terminal resistance control device |
| CN105072008A (en) * | 2015-07-31 | 2015-11-18 | 上海卫星工程研究所 | Bus topology-based modularized satellite platform electronic integrated information processing system |
| 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 |
Non-Patent Citations (2)
| Title |
|---|
| 卫星夹层结构分析与结构设计研究;张铁亮;《中国博士学位论文全文数据库》;20121215(第12期);正文第2-4页，图1.1-1.3 * |
| 未来空间站控制系统信息体系结构研究;于丹;《中国优秀硕士论文全文数据库》;20111215(第12期);全文 * |
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