CN109101452A - Integrated Electronic System hardware structure design method suitable for deep space probe - Google Patents
Integrated Electronic System hardware structure design method suitable for deep space probe Download PDFInfo
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- CN109101452A CN109101452A CN201810709127.9A CN201810709127A CN109101452A CN 109101452 A CN109101452 A CN 109101452A CN 201810709127 A CN201810709127 A CN 201810709127A CN 109101452 A CN109101452 A CN 109101452A
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F13/00—Interconnection of, or transfer of information or other signals between, memories, input/output devices or central processing units
- G06F13/38—Information transfer, e.g. on bus
- G06F13/42—Bus transfer protocol, e.g. handshake; Synchronisation
- G06F13/4282—Bus transfer protocol, e.g. handshake; Synchronisation on a serial bus, e.g. I2C bus, SPI bus
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F13/00—Interconnection of, or transfer of information or other signals between, memories, input/output devices or central processing units
- G06F13/38—Information transfer, e.g. on bus
- G06F13/40—Bus structure
- G06F13/4004—Coupling between buses
- G06F13/4009—Coupling between buses with data restructuring
- G06F13/4018—Coupling between buses with data restructuring with data-width conversion
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- General Engineering & Computer Science (AREA)
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- General Physics & Mathematics (AREA)
- Computer Hardware Design (AREA)
- Arrangements For Transmission Of Measured Signals (AREA)
- Testing Or Calibration Of Command Recording Devices (AREA)
Abstract
The present invention provides a kind of Integrated Electronic System hardware structure design methods suitable for deep space probe, using integrated hardware architecture design, computer is carried as core using device, as a whole by each subsystem of detector, plan as a whole distribution resource, by detector design in slave computer be merged into the functional module of single machine, the interaction of instruction and data is carried out eventually by control bus, realizes the shared of detector software and hardware resource.The method of the present invention is a kind of method of actual Integrated Electronic System hardware structure design of Engineering Oriented, has engineering practical value.
Description
Technical field
The present invention relates to Integrated Electronic System hardware structure design methods, and in particular to a kind of suitable for deep space probe
The method of Integrated Electronic System hardware structure design.
Background technique
Integrated Electronic System is deep space probe important component, mainly undertakes the processing of deep space probe integrated information
Task realizes that detector device business management, remote-control romote-sensing information processing, number pass information processing, energy management and thermal control management function,
Traditional detector master-plan is that whole device is decomposed into structure, thermal control, overall circuit, power supply, observing and controlling, number pipe, rail control, is pushed away
Into the subsystems such as, solar wing and payload, then each subsystem is carried out according to the technical requirements that detector totally proposes
All subsystem units equipment finally are connected to form detector by Subsystem Design and single machine development again, carry out general assembly and synthesis
Test.Each subsystem of detector is managed respectively by more independent slave computers, then is carried computer by device and carried out indirect control to it
And control.This traditional electronic system hardware structure design cannot achieve resource-sharing, cause command link on device, telemetering line
Road and data exchange line are complicated.
Based on deep space probe to the challenging needs of resource-sharing and decrement, the system design of integrated electronics is proposed very high
It is required that.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of integrated electronics suitable for deep space probe
System hardware architecture design method the characteristics of according to deep space exploration task, is realized between each subsystem units of deep space probe
Distribution, remote measuring and controlling and data exchange, the function of storage.
A kind of Integrated Electronic System hardware structure design method suitable for deep space probe provided according to the present invention, is adopted
With integrated hardware architecture design, computer is carried as core using device, as a whole by each subsystem of detector, plans as a whole distribution
Resource, by detector design in slave computer be merged into the functional module of single machine, carry out instruction sum number eventually by control bus
According to interaction, realize the shared of detector software and hardware resource.
Subsystem includes passing through System control bus and serial communication bus respectively using SMU unit as information processing maincenter,
It is connected with GMU unit, PLC unit, PDU unit, SEU unit, QDU unit and GEU unit, to realize and detector other systems
Between control instruction transmission and data exchange.
The SMU unit realizes detector data parsing decoding and remote-control romote-sensing, data storage function.
The GMU unit realizes detector posture orbits controlling and image processing function.
The PLC unit realizes the transmitting-receiving and store function of detector payload data.
The SEU unit realizes the hardware interface extension function of the SMU unit.
The QDU unit realizes detector mechanism driving and control function.
The GEU unit realizes the hardware interface extension function of the GMU unit.
The PDU unit realizes the power supply and distribution management function of detector.
Deep space exploration Integrated Electronic System hardware structure design method provided by the present invention is based on resource-sharing and mitigation
The Important Thought of weight breaks conventional satellite electronic equipment Distributed Design scheme, carries out multifunction comb to whole device electronics equipment
It manages and reintegrates, computer is carried as core using device, as a whole by each subsystem of detector, plans as a whole distribution telemetering, distant
The resources such as control and heater-driven control, by conventional detectors design in slave computer be merged into the functional module of single machine, most
The interaction for carrying out instruction and data by control bus eventually realizes the shared of detector software and hardware resource, simplifies hard
The complexity of part and cable, alleviates system weight, reduces the path of information transmission transfer, improves the information transmitting of system
Reliability.At the same time, using the design of this integrated hardware framework, each subsystem demand is optimized into integration and money
Source reasonable redistribution, to meet an urgent demand of deep space exploration space tasks loss of weight and quick response.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is the hard channel framework design drawing of integrated electronics distribution provided by the present invention；
Fig. 2 is the hard channel framework design drawing of integrated electronics remote measuring and controlling provided by the present invention.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
As shown in Figure 1, the Integrated Electronic System hardware structure design side provided by the present invention suitable for deep space probe
Method is powered SMU unit, SEU unit, QDU unit, GEU unit and PLC by PDU unit；It is mono- to GMU by GEU unit
Member is powered, to realize unified management and distribution that integrated electronics power to each system single machine.
As shown in Fig. 2, SMU unit is connect as core, with GMU unit, PLC unit by control bus, referred to realizing
Enable distribution, telemetry-acquisition and data broadcasting exchange；SMU unit and GMU unit, SEU unit, QDU unit and GEU unit pass through string
Row communication bus realizes instruction distribution and telemetry-acquisition；GMU unit is with PLC unit, QDU unit and GEU unit by serially leading to
Believe that bus realizes instruction distribution and telemetry-acquisition；SEU unit and PDU unit realize instruction distribution and distant by serial communication bus
Survey acquisition.
Working environment locating for deep space probe is very remote apart from the earth, objective compared with conventional artificial earth satellite
On there are device communication delay it is big, and there are the day Ling Xianxiang that the sun blocks with leading to device communication disruption, this just needs deep space to visit
The bus communication path for surveying the transmission of device therein instruction and data has flexibility and independence, to overcome earth tracking telemetry and command station
Remote-control romote-sensing not in time and cannot achieve the difficulty of remote-control romote-sensing.The information of the design of hardware structure transmits road through the invention
Diameter can guarantee that deep space probe plans as a whole distribution, efficiently transmission to various information, to realize the in-orbit each rank of flight of deep space probe
Section autonomous intelligence management creates conditions.
The method of the present invention needs during application by various information integrated treatment, according to information type, importance and
The attributes such as timeliness are classified, and are distributed rationally, sufficiently realize the timeliness of information transmitting routing and reliable, be deep space probe from
It saves oneself under the cases of emergency such as major error management and guarantee is provided.
The bus topology mode of dispersion, design synthesis electronic hardware configuration, according to each subsystem of detector are neutralized using collection
Function is divided, and reconfigurability is strong, catastrophic failure is encountered in deep space exploration and also ground troubleshooting not in time in the case where, energy
Enough autonomous isolation are broken down unit, can be realized the isolation control of whole device failure, be unlikely to cause whole device aerial mission at
It loses.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (9)
1. a kind of Integrated Electronic System hardware structure design method suitable for deep space probe, which is characterized in that using one
Change hardware structure design, computer carried as core using device, as a whole by each subsystem of detector, plans as a whole distribution resource,
By detector design in slave computer be merged into the functional module of single machine, the friendship of instruction and data is carried out eventually by control bus
Mutually, the shared of detector software and hardware resource is realized.
2. the Integrated Electronic System hardware structure design method according to claim 1 suitable for deep space probe, special
Sign is that subsystem includes passing through System control bus and serial communication bus respectively using SMU unit as information processing maincenter,
It is connected with GMU unit, PLC unit, PDU unit, SEU unit, QDU unit and GEU unit, to realize and detector other systems
Between control instruction transmission and data exchange.
3. the Integrated Electronic System hardware structure design method according to claim 1 suitable for deep space probe, special
Sign is that the SMU unit realizes detector data parsing decoding and remote-control romote-sensing, data storage function.
4. the Integrated Electronic System hardware structure design method according to claim 1 suitable for deep space probe, special
Sign is that the GMU unit realizes detector posture orbits controlling and image processing function.
5. the Integrated Electronic System hardware structure design method according to claim 1 suitable for deep space probe, special
Sign is that the PLC unit realizes the transmitting-receiving and store function of detector payload data.
6. the Integrated Electronic System hardware structure design method according to claim 1 suitable for deep space probe, special
Sign is that the SEU unit realizes the hardware interface extension function of the SMU unit.
7. the Integrated Electronic System hardware structure design method according to claim 1 suitable for deep space probe, special
Sign is that the QDU unit realizes detector mechanism driving and control function.
8. the Integrated Electronic System hardware structure design method according to claim 1 suitable for deep space probe, special
Sign is that the GEU unit realizes the hardware interface extension function of the GMU unit.
9. the Integrated Electronic System hardware structure design method according to claim 1 suitable for deep space probe, special
Sign is that the PDU unit realizes the power supply and distribution management function of detector.
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| CN201810709127.9A CN109101452B (en) | 2018-07-02 | 2018-07-02 | Design method of hardware architecture of integrated electronic system suitable for deep space probe |
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| CN109101452B CN109101452B (en) | 2020-12-11 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114520763A (en) * | 2021-12-31 | 2022-05-20 | 国网青海省电力公司 | Design method for overall architecture of intelligent comprehensive operation and maintenance system |
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| CN103368638A (en) * | 2012-03-29 | 2013-10-23 | 中国科学院空间科学与应用研究中心 | A measurement and control communication method for a deep space probe and a measurement and control communication system for a deep space probe |
| CN103984663A (en) * | 2014-06-03 | 2014-08-13 | 上海航天电子通讯设备研究所 | Diverse satellite-borne electronic equipment in parallel system |
| CN105137864A (en) * | 2015-07-31 | 2015-12-09 | 上海卫星工程研究所 | Lower computer coordinative control SoC chip for spacecraft |
| US9344268B1 (en) * | 2014-12-23 | 2016-05-17 | Broadcom Corporation | Phase alignment architecture for ultra high-speed data path |
| 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 |
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2018
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Patent Citations (5)
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| CN103368638A (en) * | 2012-03-29 | 2013-10-23 | 中国科学院空间科学与应用研究中心 | A measurement and control communication method for a deep space probe and a measurement and control communication system for a deep space probe |
| CN103984663A (en) * | 2014-06-03 | 2014-08-13 | 上海航天电子通讯设备研究所 | Diverse satellite-borne electronic equipment in parallel system |
| US9344268B1 (en) * | 2014-12-23 | 2016-05-17 | Broadcom Corporation | Phase alignment architecture for ultra high-speed data path |
| CN105137864A (en) * | 2015-07-31 | 2015-12-09 | 上海卫星工程研究所 | Lower computer coordinative control SoC chip for spacecraft |
| 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 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114520763A (en) * | 2021-12-31 | 2022-05-20 | 国网青海省电力公司 | Design method for overall architecture of intelligent comprehensive operation and maintenance system |
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