CN109298660A - Control system for satellite effective load - Google Patents
Control system for satellite effective load Download PDFInfo
- Publication number
- CN109298660A CN109298660A CN201810925269.9A CN201810925269A CN109298660A CN 109298660 A CN109298660 A CN 109298660A CN 201810925269 A CN201810925269 A CN 201810925269A CN 109298660 A CN109298660 A CN 109298660A
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- 238000004891 communication Methods 0.000 claims abstract description 12
- 238000002955 isolation Methods 0.000 claims description 17
- 239000002184 metal Substances 0.000 claims description 6
- 238000002048 anodisation reaction Methods 0.000 claims description 3
- 230000005611 electricity Effects 0.000 claims description 2
- 238000012423 maintenance Methods 0.000 abstract description 4
- 230000006870 function Effects 0.000 description 8
- 238000013461 design Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 6
- LMDZBCPBFSXMTL-UHFFFAOYSA-N 1-ethyl-3-(3-dimethylaminopropyl)carbodiimide Chemical compound CCN=C=NCCCN(C)C LMDZBCPBFSXMTL-UHFFFAOYSA-N 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000007726 management method Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 238000013523 data management Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 239000003550 marker Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0423—Input/output
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/25—Pc structure of the system
- G05B2219/25257—Microcontroller
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
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Abstract
The invention provides a control system of satellite payload, which comprises a first host and a second host which are mutually backed up, wherein modular equipment which can be hot plugged and unplugged is arranged inside the first host and the second host, the modular equipment is connected by a cPCI bus, and the modular equipment comprises: the device comprises a processor module, a communication module and an instruction module. The system designed by the cPCI standard can be flexibly realized, is convenient for system maintenance and has certain expansion capability; and various communication and control interfaces and telemetering acquisition interfaces which are commonly used for supporting satellite loads are supported.
Description
Technical field
The present invention relates to avionics equipment fields, and in particular, to a kind of control system of Satellite Payloads.
Background technique
Satellite Payloads refer to instrument, equipment or the subsystem for loading and completing particular task on satellite, need one kind
Control system and method control it and management and running.
Since common cPCI bus can not achieve the reconstruct of system card, Redundancy Design not can be carried out, therefore never
Fusion application is in Satellite Payloads control system.In the research to Satellite Payloads control system, it can be improved and defend
Star payload control system performance, but difficult point is to guarantee its high reliability.Meanwhile to Satellite Payloads control system
Leading to the problem of in operation and carrying out positioning is also a key point.How to realize it is autonomous controllable and possess under same reliability compared with
High performance Satellite Payloads control system is one the challenge that faces increasingly complicated space mission and needs what is solved to ask
Topic.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of control systems of Satellite Payloads.
A kind of control system of the Satellite Payloads provided according to the present invention, including mutually redundant first host and
It is hot-swappable modularized equipment inside two hosts, first host and second host, between each modularized equipment
It is connected using cPCI bus, the modularized equipment includes: processor module, communication module and instruction module.
Preferably, the processor module includes: processor, memory, clock circuit, reset control circuit, debugging string
Mouth, Bus isolation driving circuit and FPGA；
The processor connects the memory and the FPGA, the clock electricity by the Bus isolation driving circuit
Road, the reset control circuit connect the processor with the debugging serial ports.
Preferably, the memory includes: FLASH, SRAM, SDRAM or EEPROM.
Preferably, the communication module includes: FPGA, Bus isolation driving circuit, 1553B bus control circuit, CAN total
Line control circuit, isa bus socket and cPCI bus interface；
The FPGA connects the 1553B bus control circuit by the Bus isolation driving circuit and the ISA is total
Line socket, the FPGA connection CAN bus control circuit and the cPCI bus interface.
Preferably, the CAN bus control circuit connects CAN bus by transceiver.
Preferably, described instruction module includes: that FPGA, Bus isolation driving circuit, isa bus interface and cPCI bus connect
Mouthful, the FPGA connects the isa bus interface by the Bus isolation driving circuit, and the cPCI bus interface connects institute
FPGA is stated, by FPGA control OC instruction output and acquisition External telemetry amount input.
Preferably, the control system of the Satellite Payloads further includes power module, the power module includes each other
Two DC-DC modules of backup, are separately connected first host and second host, described two DC-DC modules pass through
The switching of relay channel.
Preferably, first host and modularized equipment in second host and the power module are pacified respectively
Loaded in metal module box, in the chassis, the cabinet surface anodization is handled for each pluggable electrical connection of metal module box.
Compared with prior art, the present invention have it is following the utility model has the advantages that
The present invention is effectively carried using the design method of domestic aerospace grade device and the cold standby of complete machine grade to improve satellite
High reliability, the long-life solution of lotus control method.It supports ReWorks and VxWorks real time operating system simultaneously, has
Instruction output, CAN bus and 1553B bus carry out task schedule and control ability, internal health control, redundancy backup, application
The functions such as note on software.The invention aims under outer space environments requirement, the reception and parsing, task meter to control instruction
It calculates and handles.Complete machine borrows the cPCI bus structures of standard, realizes spaceborne computer module (6U) standardized designs, and have one
Fixed extended capability；The more previous spaceborne computer flexible design of the structure, facilitates system maintenance.
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 structural diagram of the present invention；
Fig. 2 is complete machine block diagram of the invention；
Fig. 3 is the structural schematic diagram of processor module of the present invention；
Fig. 4 is the structural schematic diagram of communication module of the present invention；
Fig. 5 is the structural schematic diagram of instruction module of the present invention；
Fig. 6 is the structural schematic diagram of power module of 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 and Figure 2, a kind of control system of the Satellite Payloads provided according to the present invention, including be mutually backups
The first host and the second host, support cold standby and hot standby.It is hot-swappable modularization inside first host and the second host
Equipment is connected between each modularized equipment using cPCI bus, convenient for the extension of system and the replacement of module.Modularized equipment packet
It includes: processor module, communication module and instruction module.Software section includes guidance software and FPGA software.The operation of FPGA software
In encoded control, communication interface management, instruction control, the data management etc. on the FPGA of each module, be responsible in each functional module
Function.Guidance software mainly realizes the hardware initialization after processor module powers on, hardware check survey and direct application journey
Sequence after running successfully, is guided from EEPROM according to promissory marker or is guided from FLASH.In first host and the second host
Modularized equipment and power module are respectively arranged in metal module box, to increase the reliability and Flouride-resistani acid phesphatase and anti-of product
Simple grain subfunction.In the chassis, cabinet surface anodization is handled for each pluggable electrical connection of metal module box.
As shown in figure 3, processor module include: processor BM3803MG, memory (FLASH, SRAM, SDRAM or
EEPROM), clock circuit, reset control circuit, debugging serial ports, Bus isolation driving circuit and FPGA；Processor passes through bus
Isolated drive circuit connects memory and FPGA, and clock circuit, reset control circuit connect processor with debugging serial ports, utilize
FPGA realizes standard cPCI interface.The distribution of the memory of processor module and service condition are as follows:
A) SRAM size is 8MB, has the function of EDAC, is made of 4 chips of 512K × 32, and SRAM (512K × 32) is respectively
Distribute the band EDAC error correction and detection function inside 4 RAM block the sections nRAMCS0~3, SRAM of CPU.
B) PROM size is 32KB, is made of the chip of 1 32K × 8, is distributed in the memory field Boot PROM of CPU
Between, it is substituted using the EEPROM of same size when debugging；
C) E2PROM/FLASH size is respectively 2MB, is made of the E2PROM chip of 2 1024K*8bit, 4 512K*
The FLASH chip composition of 8bit is for storing data or program.
As shown in figure 4, communication module includes: FPGA, Bus isolation driving circuit, 1553B bus control circuit, CAN total
Line control circuit, isa bus socket and cPCI bus interface；FPGA connects the total line traffic control of 1553B by Bus isolation driving circuit
Circuit and isa bus socket processed, FPGA connection CAN bus control circuit and cPCI bus interface.CAN bus control circuit passes through
Transceiver connects CAN bus.Communication module+5V ,+3.3V are inputted by power module, the voltages such as 2.5V, 1.8V used in module by
Low voltage difference three terminal regulator is provided by the conversion of+5V supply voltage.
As shown in figure 5, instruction module includes: that FPGA, Bus isolation driving circuit, isa bus interface and cPCI bus connect
Mouthful, FPGA connects isa bus interface by Bus isolation driving circuit, and cPCI bus interface connects FPGA, controls OC by FPGA
Instruction output and acquisition External telemetry amount input.Command output module realizes the control of external executing agency's terminal device, by translating
Code circuit, the instruction functions such as output driving and filtering composition, the way of output are designed as open collector control, are used for switch order
Output control.Instruction module+5V ,+3.3V power supply are inputted by power module, and the low-voltages such as 2.5V used in instruction module are by low
Pressure difference three terminal regulator is provided by the conversion of+5V voltage.
As shown in fig. 6, the control system of Satellite Payloads further includes power module, power module includes mutually redundant
Two DC-DC modules, are separately connected the first host and the second host, and two DC-DC modules are switched by relay channel.Complete machine
Supply input voltage is+28V, and two power modules are respectively to main part, backup functionality module for power supply.The side switched using relay
Formula controls the power-on and power-off of master backup circuit, relay working voltage+28V, and control switching uses pulse control, and pulse amplitude is
12Vdc, pulsewidth 100ms.
Advantage is the present embodiment compared with the prior art:
1. complete machine structure flexible design facilitates system maintenance, and has certain extended capability；
2. problem can be accurately positioned by health control and telemetering output to system；
3. the spaceborne computer processing speed than previous identical reliability is higher, integer arithmetic ability reaches 60MIPS, floats
Point processing ability: 20MFLOPS.
The present invention realize Satellite Payloads control computing system totally-domestic, using cPCI standard design system,
It can flexibly realize the system, facilitate system maintenance；Support the common a variety of communications of satellite load and control interface, telemetry-acquisition
Interface, while by the inside health control circuit to this system, it can be achieved that the working state real-time monitoring of satellite control system.
One skilled in the art will appreciate that in addition to realizing system provided by the invention in a manner of pure computer readable program code
It, completely can be by the way that method and step be carried out programming in logic come so that the present invention provides and its other than each device, module, unit
System and its each device, module, unit with logic gate, switch, specific integrated circuit, programmable logic controller (PLC) and embedding
Enter the form of the controller that declines etc. to realize identical function.So system provided by the invention and its every device, module, list
Member is considered a kind of hardware component, and to include in it can also for realizing the device of various functions, module, unit
To be considered as the structure in hardware component；It can also will be considered as realizing the device of various functions, module, unit either real
The software module of existing method can be the structure in hardware component again.
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 (8)
1. a kind of control system of Satellite Payloads, which is characterized in that including mutually redundant first host and the second host,
It is hot-swappable modularized equipment inside first host and second host, uses cPCI between each modularized equipment
Bus connection, the modularized equipment includes: processor module, communication module and instruction module.
2. the control system of Satellite Payloads according to claim 1, which is characterized in that the processor module packet
It includes: processor, memory, clock circuit, reset control circuit, debugging serial ports, Bus isolation driving circuit and FPGA；
The processor connects the memory and the FPGA by the Bus isolation driving circuit, the clock circuit,
The reset control circuit connects the processor with the debugging serial ports.
3. the control system of Satellite Payloads according to claim 2, which is characterized in that the memory includes:
FLASH, SRAM, SDRAM or EEPROM.
4. the control system of Satellite Payloads according to claim 1, which is characterized in that the communication module includes:
FPGA, Bus isolation driving circuit, 1553B bus control circuit, CAN bus control circuit, isa bus socket and cPCI bus
Interface；
The FPGA connects the 1553B bus control circuit by the Bus isolation driving circuit and the isa bus is inserted
Seat, the FPGA connection CAN bus control circuit and the cPCI bus interface.
5. the control system of Satellite Payloads according to claim 4, which is characterized in that the CAN bus control electricity
Road connects CAN bus by transceiver.
6. the control system of Satellite Payloads according to claim 1, which is characterized in that described instruction module includes:
FPGA, Bus isolation driving circuit, isa bus interface and cPCI bus interface, the FPGA are driven by the Bus isolation
Isa bus interface described in circuit connection, the cPCI bus interface connect the FPGA, by FPGA control OC instruction output and adopt
Collect the input of External telemetry amount.
7. the control system of Satellite Payloads according to claim 1, which is characterized in that the Satellite Payloads
Control system further includes power module, and the power module includes mutually redundant two DC-DC modules, is separately connected described
One host and second host, described two DC-DC modules are switched by relay channel.
8. the control system of Satellite Payloads according to claim 7, which is characterized in that first host and described
Modularized equipment and the power module in second host are respectively arranged in metal module box, and each metal module box can
In the chassis, the cabinet surface anodization is handled for plug electrical connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810925269.9A CN109298660A (en) | 2018-08-14 | 2018-08-14 | Control system for satellite effective load |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810925269.9A CN109298660A (en) | 2018-08-14 | 2018-08-14 | Control system for satellite effective load |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109298660A true CN109298660A (en) | 2019-02-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810925269.9A Pending CN109298660A (en) | 2018-08-14 | 2018-08-14 | Control system for satellite effective load |
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| Country | Link |
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| CN (1) | CN109298660A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111668916A (en) * | 2020-05-26 | 2020-09-15 | 中国科学院西安光学精密机械研究所 | Satellite load power supply backup system |
| CN113485087A (en) * | 2021-06-16 | 2021-10-08 | 航天东方红卫星有限公司 | Microsatellite DC-DC module active/standby switching device based on PXI bus technology |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104991879A (en) * | 2015-08-14 | 2015-10-21 | 上海航天测控通信研究所 | Spaceborne computer system capable of be assembled on orbit |
| US20160062936A1 (en) * | 2014-08-26 | 2016-03-03 | Bull Sas | Server comprising a plurality of modules |
| CN105549464A (en) * | 2015-12-10 | 2016-05-04 | 中国电子科技集团公司第三十二研究所 | Management and control system for medium and high orbit satellite payload |
| CN105739416A (en) * | 2016-05-06 | 2016-07-06 | 上海航天测控通信研究所 | Satellite-borne comprehensive electronic computer |
| CN106776468A (en) * | 2016-12-23 | 2017-05-31 | 山东航天电子技术研究所 | A kind of dual redundant reconfigurable satellite-borne computer system based on cpci bus |
-
2018
- 2018-08-14 CN CN201810925269.9A patent/CN109298660A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160062936A1 (en) * | 2014-08-26 | 2016-03-03 | Bull Sas | Server comprising a plurality of modules |
| CN104991879A (en) * | 2015-08-14 | 2015-10-21 | 上海航天测控通信研究所 | Spaceborne computer system capable of be assembled on orbit |
| CN105549464A (en) * | 2015-12-10 | 2016-05-04 | 中国电子科技集团公司第三十二研究所 | Management and control system for medium and high orbit satellite payload |
| CN105739416A (en) * | 2016-05-06 | 2016-07-06 | 上海航天测控通信研究所 | Satellite-borne comprehensive electronic computer |
| CN106776468A (en) * | 2016-12-23 | 2017-05-31 | 山东航天电子技术研究所 | A kind of dual redundant reconfigurable satellite-borne computer system based on cpci bus |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111668916A (en) * | 2020-05-26 | 2020-09-15 | 中国科学院西安光学精密机械研究所 | Satellite load power supply backup system |
| CN113485087A (en) * | 2021-06-16 | 2021-10-08 | 航天东方红卫星有限公司 | Microsatellite DC-DC module active/standby switching device based on PXI bus technology |
| CN113485087B (en) * | 2021-06-16 | 2023-11-10 | 航天东方红卫星有限公司 | Small satellite DC-DC module active-standby switching device based on PXI bus technology |
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Application publication date: 20190201 |
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