CN105549460A - Satellite-borne electronic equipment comprehensive management and control system - Google Patents

Satellite-borne electronic equipment comprehensive management and control system Download PDF

Info

Publication number
CN105549460A
CN105549460A CN201510896676.8A CN201510896676A CN105549460A CN 105549460 A CN105549460 A CN 105549460A CN 201510896676 A CN201510896676 A CN 201510896676A CN 105549460 A CN105549460 A CN 105549460A
Authority
CN
China
Prior art keywords
module
control
management
synthesization
data
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.)
Granted
Application number
CN201510896676.8A
Other languages
Chinese (zh)
Other versions
CN105549460B (en
Inventor
杨海峰
黄小华
柴霖
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
CETC 10 Research Institute
Original Assignee
CETC 10 Research Institute
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by CETC 10 Research Institute filed Critical CETC 10 Research Institute
Priority to CN201510896676.8A priority Critical patent/CN105549460B/en
Publication of CN105549460A publication Critical patent/CN105549460A/en
Application granted granted Critical
Publication of CN105549460B publication Critical patent/CN105549460B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • GPHYSICS
    • G05CONTROLLING; REGULATING
    • G05BCONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B19/00Programme-control systems
    • G05B19/02Programme-control systems electric
    • G05B19/04Programme control other than numerical control, i.e. in sequence controllers or logic controllers
    • G05B19/042Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
    • G05B19/0423Input/output
    • GPHYSICS
    • G05CONTROLLING; REGULATING
    • G05BCONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B2219/00Program-control systems
    • G05B2219/20Pc systems
    • G05B2219/25Pc structure of the system
    • G05B2219/25314Modular structure, modules

Abstract

The invention discloses a satellite-borne electronic equipment comprehensive management and control system and aims to provides the satellite-borne electronic equipment comprehensive management and control system which is high in integration, stable and reliable and capable of reducing a device number and redundant remote measurement and remote control interfaces. According to the technical field, each module in a comprehensive management and control unite and a comprehensive service unit is connected to a 1553B bus through a board-level management controller in the module so as to carry out data monitoring and instruction data transmission; by means of a J599 type connector, the comprehensive service unit realizes external gigabit Ethernet data communication among units and management and control data isolation and interaction; the comprehensive management and control unite receives platform remote control, time and attitude information and sends remote measurement and data transmission data through a management and control duty module; and the comprehensive management and control unite is configured to X1 or X4 mode through a Rapid IO management module, and a Rapid IO network topological structure in the unit is configured to a single satellite or double mode through the Rapid IO management module.

Description

Electronic equipment on satellite synthesization managing and control system
Technical field
The invention belongs to space flight and aviation technical field, be specifically related to a kind of electronic equipment on satellite synthesization managing and control system, the high and low power consumption of a kind of integrated level, reliable and stable, strong extendability can be provided, can reduce the electronic equipment on satellite synthesization managing and control system of number of devices and redundancy remote measuring and controlling interface.
Background technology
Along with the development of large-scale manned space flight device, manned space flight device is long-term in-orbit, constantly will expand new task and new hardware, proposes more harsh demand to the integrated level of satellite borne electronic system, extensibility and synthesization ability.Traditional satellite borne electronic system is designed to main with association type, with each autonomous device for elementary cell constructing system, this system is once build up, be difficult to add new function, system does not possess lasting expansion, upgrading, business growth ability, and module and interface turn to master to customize, of a great variety, interface rate is low, information interface is complicated and unintelligible, and resource utilization is low, causes the problems such as volume is large, weight is high, power consumption is large, operability is poor, failsafe link is many, expensive, make Practical Project model task, especially manned space flight task faces excessive risk.Based on the active demand of above practical engineering application, at present, carry out the research of space flight integrate electrical system both at home and abroad, but spininess is to moonlet and Nano satellite platform, fundamental design idea with single board computer or monolithic embedded chip for core, interface rate and chip performance limited, be difficult to the functional parameter demand meeting large-scale task, scarcely possesses continuable extended capability, directive significance is not possessed to large-scale manned space flight task, thus the demand studying extensive degree of depth electronic equipment on satellite synthesization managing and control system is very urgent, imperative.
External typical space flight integrate electrical system, as " SNAP-1 " microsatellite that Britain Surrey launched in 2000, electronic system take board computer system as core, and business datum and control command are undertaken by CAN and other subsystems alternately.The and for example whole star electronic system of Ou Hang office GIOVE-A, is divided into communication system, number guard system, Attitude and orbit control system, propulsion system, power-supply system and base band useful load six Iarge-scale system.Whole star is managed CAN network by the several pipe computing machines based on Intel386CPU, and Attitude and orbit control system, propulsion system, power-supply system and base band load are equipped with CAN node.Two canonical systems all use CAN to carry out the mutual of all data, interface backup means are single, possesses extended capability hardly, and without unified massive store management function, it can comprehensive management and control limited in one's ability, several functions can not be realized load at same electric load, each System's composition independence, dispersion, limited to the supporting capacity of high-performance, extensive space mission.
Chinese Patent Application No. is 201410224895.7, the patent " total management system for platform load integration satellite " of Changchun Institute of Optics, Fine Mechanics and Physics, CAS's xuwei application proposes a kind of total management system for platform load integration satellite, but this total management system more designs for small satellite platform, data interaction is carried out by means of only dual-redundant CAN bus between unit, do not possess business datum, the interface separating power of steering order data, when CAN breaks down, data transmission is carried out without additional interface, efficient communication cannot be carried out between unit, load cell is caused to lose efficacy, in addition the total management system that relates to of this patented claim is countless according to memory management functions, management of overall importance and control cannot be carried out to the storage of data and retaking of a year or grade, data store and retaking of a year or grade, single particle effect detect and recovery function need rely on each module complete independently, integrated level is poor, cause intermediate link too much, the problem that failsafe link increases, the command control panel and instruction sending module realizing OC instruction of this patented claim adopts CAN transfer instruction in addition, because CAN is preemptive type bus, communication blocking and delay will be there is, the problem that operation delay is large and make a mistake is waited by causing all the other module switch electricity, affect task entirety to perform, and do not mention several functions to load in identical platform, synthesization without working-flow designs, low to electric load utilization factor, thus in large-scale space platform, actual use is limited, engineer applied is poor.
Summary of the invention
The present invention is directed to that prior art spaceborne electron tube Ore-controlling Role device category is various, functional independence, framework is closed, utilization factor is low, be difficult to unified allocation of resources, the poor problem of open and extendability, the high and low power consumption of a kind of integrated level, reliable and stable, strong extendability are provided, can reduce the electronic equipment on satellite synthesization managing and control system of number of devices and redundancy remote measuring and controlling interface.
The technical solution adopted in the present invention is: a kind of electronic equipment on satellite synthesization managing and control system, comprises integrated service unit and comprehensive control unit, and integrated service unit by outside 1553B bus 1., RapidIO interface 2., gigabit ethernet interface is interconnect synthesis control unit 3., and comprehensive control unit comprises and is arranged on high reliable tube control value class module on High speed rear panel, system management and control module, kilomega network administration module, RapidIO administration module, Data Storage, OC instruction module and secondary power supply module, it is characterized in that: in comprehensive control unit and integrated service unit, each module is connected to by the plate level Management Controller of inside modules the transmission that 1553B bus carries out Monitoring Data and instruction data, and integrated service unit realizes outside 1553B between unit by J599 type connector, RapidIO, the communication of gigabit Ethernet data, realizes at a high speed, the isolation of low-speed service data and management and control data with mutual, comprehensive control unit by the FC-AE-1553 Interface realization in management and control module on duty to platform remote control, time, the reception of attitude information and remote measurement pass the transmission of data with number, module in comprehensive control unit is undertaken at a high speed by RapidIO interface, the transmission of Large Copacity business datum, RapidIO interface by RapidIO administration module be configured to × 1 or × 4 patterns, in comprehensive control unit, RapidIO net topology structure configures single star or double mode by RapidIO administration module.
The present invention has following beneficial effect compared to prior art.
The present invention is directed to the global design of large-scale manned space flight device electric load system, changing tradition is designed to main with association type, the method for designing being elementary cell constructing system with each autonomous device and thinking, adopt open system framework, electric load is carried out synthesization design, design a kind of degree of depth synthesization managing and control system for extensive satellite borne electronic system, its advantage applies is:
The high and low power consumption of integrated level.High reliable tube control value class module, system management and control module, kilomega network administration module, RapidIO administration module, Data Storage, OC instruction module and secondary power supply module high integration are arranged on the High speed rear panel of comprehensive control unit by the present invention, subsystem management and control module, puppy parc and interface module will be comprised, general signal processing module, conventional data processing module, secondary power supply module high integration arrange integrated service unit, reduce power consumption.By unified with data-interface in unit between integrated service unit and comprehensive control unit be high speed business data-interface, low-speed service data interface, Inspect and control information interface, avoid that complex interfaces, redundancy are too much, the unsharp problem of data.
Reliable and stable, enhancing extendability.The present invention is based on modularization, the theory of open by design, each module in comprehensive control unit and integrated service unit is adopted to be connected to by the plate level Management Controller of inside modules the transmission that 1553B bus carries out Monitoring Data and instruction data, integrated service unit realizes outside 1553B between unit by J599 type connector, RapidIO, the communication of gigabit Ethernet data, realize at a high speed, the isolation of low-speed service data and management and control data is with mutual, comprehensive control unit by the FC-AE-1553 Interface realization in management and control module on duty to platform remote control, time, the reception of attitude information and remote measurement, number passes the transmission of data, under unified framework, realize the multi-functional ability loaded with task, comparatively complete synthesization management and controlling functions are realized to electric load system, stable and reliable for performance, enhance extendability.In CPU+FPGA board, carried out the transmission of point-to-point information, data by standard kilomega network protocol interface between CPU and FPGA, avoid the unreliable custom protocol transmission brought by local storage FIFO mode, it also avoid the competition using global bus to bring, overcome that prior art spaceborne electron tube Ore-controlling Role device category is various, functional independence, framework is closed, and utilization factor is low, be difficult to unified allocation of resources, open and extendability difference problem.Problem, reduces implementation complexity, improves reliability.
Number of devices and redundancy remote measuring and controlling interface can be reduced.The comprehensive control unit of the present invention passes the transmission of data to the reception of platform remote control, time, attitude information and remote measurement, number by the FC-AE-1553 Interface realization in management and control module on duty; Module in comprehensive control unit is undertaken at a high speed by RapidIO interface, the transmission of Large Copacity business datum, RapidIO interface by RapidIO administration module be configured to × 1 or × 4 patterns, in unit, RapidIO net topology structure configures single star or double mode by RapidIO administration module, the plate level Management Controller designed by synthesization realize each module to the monitoring of internal information, gather and report, and realize low speed control command bus in inside; The loading as several functions such as microwave imaging, electronic reconnaissance, space-based information transmission can be realized in a set of synthesization payload platform, improve load utilization factor and standardization level.Reduce module number, decrease number of devices and redundancy remote measuring and controlling interface.
The synthesization that the present invention can be widely used in large-scale manned space flight platform and platform clectronic load is integrated.
Accompanying drawing explanation
Fig. 1 electronic equipment on satellite synthesization of the present invention managing and control system structural principle block diagram.
Fig. 2 is Fig. 1 high reliable tube control value class modular circuit theory diagram.
Fig. 3 is Fig. 1 integrated service unit and comprehensive management and control unit F PGA+CPU modular structure block diagram.
Fig. 4 is kilomega network administration module and RapidIO administration module structured flowchart in the comprehensive control unit of Fig. 1.
Fig. 5 is electronic equipment on satellite synthesization managing and control system arrangement works FB(flow block).
Embodiment
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.Below in conjunction with accompanying drawing, the present invention is further described.
Consult Fig. 1.In embodiment described below, electronic equipment on satellite synthesization managing and control system, comprising: integrated service unit and comprehensive control unit.Module physical form in comprehensive control unit and integrated service unit is standard VPX or LRM pluggable module.Comprehensive control unit and integrated service unit all adopt to be placed at synthesization load cabinet, by expansion, and multiple synthesization load cabinet composition synthesization rack.Synthesization load case side wall is connected with synthesization rack relevant position support rivet, front panel screw fastening, and synthesization load cabinet is connected with synthesization rack by installing slide rail.Integrated service unit by outside 1553B bus 1., RapidIO interface 2., 3. gigabit ethernet interface interconnect with comprehensive control unit, realize the isolation of high speed, low-speed service data and management and control data with mutual, in system, each module is connected to by the plate level Management Controller of inside modules the transmission that 1553B bus carries out Monitoring Data and instruction data.In comprehensive control unit and integrated service unit, each module is connected to by the plate level Management Controller of inside modules the transmission that 1553B bus carries out Monitoring Data and instruction data, integrated service unit realizes the communication of outside 1553B, RapidIO between unit, gigabit Ethernet data by J599 type connector, realize the isolation of high speed, low-speed service data and management and control data with mutual, comprehensive control unit passes the transmission of data to the reception of platform remote control, time, attitude information and remote measurement, number by the FC-AE-1553 Interface realization in management and control module on duty; Module in comprehensive control unit is undertaken at a high speed by RapidIO interface, the transmission of Large Copacity business datum, RapidIO interface by RapidIO administration module be configured to × 1 or × 4 patterns, in unit, RapidIO net topology structure configures single star or double mode by RapidIO administration module.
Comprehensive control unit described in present embodiment is by high reliable tube control value class module, system management and control module, kilomega network administration module, RapidIO administration module, Data Storage, secondary power supply module, OC instruction module form, except OC instruction module, each module backs up with the two redundant fashion of 1:1, and wherein high reliable tube control value class module is Hot Spare mode.Wherein:
High reliable tube control value class module is made up of two pieces of aerospace level CPU+FPGA boards of 1:1 redundancy backup, and system management and control module is made up of two pieces of CPU+FPGA boards of 1:1 redundancy backup.The reception of high reliable tube control value class module in charge whole star electronic apparatus system management steering order, decipher, there is provided process, interfaces interconnect and etc. resource, realized functions such as the basic management controls of the condition monitoring, monitoring resource, thermal control management etc. of whole star electronic apparatus system by upper layer software (applications), and be that the functions such as External telemetry, remote control, task scheduling, system reconfiguration provide support.
System management and control module receives the information such as state, execution result of each integrated service unit feedback, and sends management and steering order to each integrated service unit.
Kilomega network administration module exchanges board by two pieces of kilomega networks of 1:1 redundancy backup and forms.Kilomega network administration module is used for realizing system management messages transmission and distribution, for the functions such as task matching, code loading, system management provide support.
RapidIO administration module exchanges board by two pieces of RapidIO of 1:1 redundancy backup and forms.RapidIO administration module provides whole star electronic system high speed, Large Copacity business data transmission and the exchange communicated and management.
Data Storage is made up of two pieces of CPU+FPGA data storage management boards of 1:1 redundancy backup, Data Storage realizes high capacity data record, dump, deletion, directory management, failure monitoring, space single particle effect detect and the function such as fault-tolerant, when reading the data, this module can by receive, store or send to other module according to the data that certain algorithm produces.
Secondary power supply module is made up of two pieces of secondary power supply boards of 1:1 redundancy backup, and OC instruction module is made up of the FPGA board of one piece of device and passage redundancy.The confession distribution of each electricity consumption module of secondary power supply module in charge, and receive, resolve the instruction of OC instruction module transmission.OC instruction module receives the instruction from high reliable tube keyholed back plate control value class module, is corresponding OC output order by instructions parse, and control OC output circuit, OC instruction is exported to secondary power supply module, completes the functions such as each electricity consumption module switch electricity, active-standby switch.
High speed rear panel is supported for high reliable tube control value class module, system management and control module, kilomega network administration module, RapidIO administration module, Data Storage, OC instruction module and the secondary power supply module in comprehensive control unit provides to interconnect.
High reliable tube control value class module described in present embodiment, subsystem management and control module, system management and control module, Data Storage, puppy parc and interface module, general signal processing module, conventional data processing module form that to be with CPU be that the CPU+FPGA of core and peripheral circuit framework board form, the realization being carried out each module by plate level Management Controller is received, sends order, monitoring interface function, is carried out the transmission of point-to-point information, data between CPU and FPGA by standard kilomega network protocol interface.
Integrated service unit comprises subsystem management and control module, puppy parc and interface module, general signal processing module, conventional data processing module, secondary power supply module.
Subsystem management and control module receives, resolve steering order from system management and control module, realize the management of hardware module underlying resource and function thread component software two parts in integrated service unit, scheduling feature, the simultaneously parameter of management component and maintenance port, initiate the self-inspection of function thread, and unifiedly to collect, to report in integrated service unit each module status parameter to system management and control module.
General-purpose interface and protocol module are made up of 1553B bus circuit, RapidIO interface circuit, kilomega network interface circuit and protocol integrated test system decision circuit, wherein protocol control circuitry realizes photoelectricity, electro-optic conversion, the conversion of three kinds of interface protocols, Data dissemination and status monitoring function, and Monitoring Data is reported subsystem management and control module.
General signal processing module touches number conversion circuit by AD, DA D/A converting circuit, signal processing circuit form, and completes the signal level collection of data, transmission and processing capacity.
Conventional data processing module receives the service data information that general signal processing module exports, and carries out aftertreatment, outgoing traffic result.
Plate level Management Controller comprises voltage collector, temperature sensor, 1553B interface control circuit and supervisory circuit, complete basic control function, basic test function, hardware testing function, for the ruuning situation of Real-Time Monitoring module measurand, to voltage and monitoring temperature, the informations such as module voltage, electric current, interface running status, to system management and control mould reporting information, and the control command that receiving tube control value class module sends.
Comprehensive control unit and integrated service unit all adopt to be placed at synthesization load cabinet, by expansion, and multiple synthesization load cabinet composition synthesization rack.
Synthesization load case side wall is connected with synthesization rack relevant position support rivet, front panel screw fastening, and synthesization load cabinet is connected with synthesization rack by installing slide rail.
Consult Fig. 2.High reliable tube control value class module described in present embodiment comprises the aerospace FPGA+CPU structure of redundancy backup, wherein, FPGA adopts a slice MicrosemiRTAX4000S/SL antifuse framework chip to carry out highly reliable Integration Design, CPU can adopt aerospace level CPU processor that is domestic or import SPARCV8RICS framework, with reset/Watchdog control circuit, plate has redundancy, ECC verification FLASH storage resources and config memory PROM resource.By the mutual detected state of heartbeat between CPU+FPGA two boards card, carry out board active-standby switch, the interface shape of heartbeat comprises but is not limited only to SPI, CAN, LVDS, UART.Carry out logical extension in FPGA inside to realize connecting the plate level Management Controller of kilomega network, there is 1 road external interface FC-AE-1553, the point-to-point high-speed serial channel of RapidIO that 2 tunnels have passage bridge function.External interface FC-AE-1553, physical form adopts wavelength to be that the photoelectric conversion module of 850 nanometers and the multimode optical fiber of 850 nanometers form, realize with the packing of satellite platform remote measuring and controlling data, unpack and transmission-receiving function, message transmission rate reaches 4Gbps, can be configured to 1Gbps, 4Gbps, 8Gbps Three models; Config memory resource is made up of 2 mutually redundant PROM nonvolatile memory XCF32P chips, loading for completing configuration file stores with solidification, and plate level Management Controller has the internal interface adaptive Ethernet of two redundancy 10/100/1000Mbps speed of the two redundancy 1553B interface in 1 tunnel and 2 tunnels support TCP/IP and UDP.
Consult Fig. 3.Use the module of FPGA+CPU structure to adopt standardized designs in the integrated service unit that present embodiment describes and comprehensive control unit, namely cpu chip is drawn 2 road kilomega networks, wherein 1 road kilomega network connects FPGA by CPU kilomega network interface chip bus.Carry out logical extension in FPGA inside and realize plate level Management Controller, RapidIO interface, SRIO bus and 2 road 1553B buses.Plate level Management Controller realizes the management of module board level health resources, and is received the supervisory instruction of this module health status and receiving tube control value class module by 1553B bus.Cpu chip is with watchdog circuit, the mutually redundant NORFLASHBootRom memory resource that the DDR3L memory resource that connecting band ECC verifies verifies with band ECC, 1 piece of NanoSSD memory resource connected by SATA bridge chip, wherein cpu chip adopts dominant frequency to be 1GHz, core number is 4, model is the domestic CPU of Loongson3A1000, DDR3L uses density to be 3 8Gbits, clock frequency is 800MHz, model is the chip composition of MicronMT41K1G8, NORFLASHBootRom uses 2 density to be 1Gbits, model is the NORFLASH composition of MicronMT28FW01GABA1LJS-0AAT, NanoSSD uses 1 capacity to be 8Gbits, model is the SLC type NANDFLASH chip composition of MicronMT29F8G08ABABAWP-IT,
Realize the storage to cpu firmware and BIOS information by NORFLASH memory resource, and carry out triplication redundancy backup design, by contrast NORFLASH data, read at least 2 identical NORFLASH data, effectively prevent space single-particle inversion; Connect NanoSSD memory resource by SATA bridge sheet, realize the storage to operating system nucleus and file system and access.
Consult Fig. 4.In comprehensive control unit described in present embodiment, kilomega network administration module and RapidIO Switching Module all realize in the mode of PowerPC+ exchange chip and peripheral circuit, adopt United design to reduce system implementation complexity.RapidIO exchange chip selects CPS-1848, support RapidIO2.1 agreement, exchange capacity reaches 240Gbps, can be configured to 1 × with 4 × pattern, there is the functions such as packet statistics, flow control, packet tracking and filtration, form 12 road switching ports and output to module and backplane connector, the maximum transmission rate of single port is 20Gbps.Gigabit Ethernet exchange chip selects VSC7429, externally support 20 tunnel thousand net network interfaces at most, wherein 12 road chip internal integrated network PHY chip, externally directly can connect kilomega network electricity mouth, other 8 roads are high speed serialization transceiver interface, connect 2 network PHY chips expand 6 road network mouths by outside.RapidIO exchange chip and gigabit Ethernet exchange chip carry out initial configuration by RapidIO interface and kilomega network interface, and MCU carries out initial configuration, status poll, fault detection and diagnosis by the corresponding interface to exchange chip.
The principle of work of this electronic equipment on satellite synthesization managing and control system is described with radar microwave imaging function below:
Consult Fig. 5, be the workflow block diagram of electronic equipment on satellite synthesization managing and control system, workflow is as follows:
Step S1: ground control centre needs according to radar microwave imaging task, forms task scheduling and arrives satellite platform by note on remote-control channel; High reliable tube control value class module forwards task scheduling information by FC-AE-1553 interface satellite platform, and enters task determinating mode;
Step S2: in comprehensive control unit, high reliable tube control value class module carries out task analysis and decision-making, feasible task is added task queue, waits pending.
Step S3: in comprehensive control unit, high reliable tube control value class module controls OC instruction module in comprehensive control unit for the previous period in task is that in integrated service unit and comprehensive control unit, each electricity consumption module powers up;
Step S4: system management and control module, subsystem management and control module Power-On Self-Test, and load respective management and control software; The ready backward active of each subsystem management and control module reports current state to system management and control module;
Step S5: in comprehensive control unit, high reliable tube control value class module assigns a task requirement;
Step S6: in comprehensive control unit, system management and control module receives an assignment requirement, is loaded into corresponding system operational parameters, according to system task finishing equipment Resourse Distribute;
Step S7: before tasks carrying, system management and control module completion system parameter configuration and running parameter decompose, and to assign a task configuration information to each subsystem management and control module;
Step S8: as broken down in said process, control center sends Defect Indication information earthward, waits for ground control centre feedback information, and makes system be in holding state, if non-fault, enter step S9;
Step S9: radar microwave imaging function task starts to perform: the process such as sampling, electro-optic conversion, transmission, opto-electronic conversion, down coversion of the general signal processing module settling signal in integrated service unit, and combine digital Wave beam forming, obtain radar return data, complete microwave signal transmitting-receiving process; In process, integrated service unit walks abreast settling signal process and data prediction, and according to needing to be transferred to conventional data processing module and data store management and control module; Conventional data processing module receiving radar echo data, and perform information processing, output image data, complete radar microwave imaging function; In comprehensive control unit, data store management and control module and complete data storage, until radar microwave imaging function task terminates, as broken down in operational process, control center sends Defect Indication information earthward, wait for ground control centre feedback information, and make system be in holding state, if non-fault, enter step S10.
Step S10: after radar microwave imaging function job end time arrives, integrated service unit neutron system management and control module reports tasks carrying to report to system management and control module in comprehensive control unit;
Step S11: system management and control module is finished the work comprehensive evaluation, generates debriefing;
Step S12: it is each electricity consumption module power-down in integrated service unit and comprehensive control unit that high reliable tube control value class module controls OC instruction module in comprehensive control unit, and make system be in holding state, radar microwave imaging function task terminates.
Obviously, those skilled in the art can carry out various change and distortion to the design of a kind of degree of depth synthesization managing and control system for extensive satellite borne electronic system of the present invention and not depart from the spirit and scope of the present invention.Like this, if these amendments and distortion belong within the scope of the claims in the present invention and equivalent technologies thereof, then the present invention is also intended to comprise these changes and distortion.

Claims (10)

1. an electronic equipment on satellite synthesization managing and control system, comprises integrated service unit and comprehensive control unit, and integrated service unit by outside 1553B bus 1., RapidIO interface 2., gigabit ethernet interface is interconnect synthesis control unit 3., and comprehensive control unit comprises and is arranged on high reliable tube control value class module on High speed rear panel, system management and control module, kilomega network administration module, RapidIO administration module, Data Storage, OC instruction module and secondary power supply module, it is characterized in that: in comprehensive control unit and integrated service unit, each module is connected to by the plate level Management Controller of inside modules the transmission that 1553B bus carries out Monitoring Data and instruction data, and integrated service unit realizes outside 1553B between unit by J599 type connector, RapidIO, the communication of gigabit Ethernet data, realizes at a high speed, the isolation of low-speed service data and management and control data with mutual, comprehensive control unit by the FC-AE-1553 Interface realization in management and control module on duty to platform remote control, time, the reception of attitude information and remote measurement pass the transmission of data with number, module in comprehensive control unit is undertaken at a high speed by RapidIO interface, the transmission of Large Copacity business datum, RapidIO interface by RapidIO administration module be configured to × 1 or × 4 patterns, in comprehensive control unit, RapidIO net topology structure configures single star or double mode by RapidIO administration module.
2. electronic equipment on satellite synthesization managing and control system according to claim 1, is characterized in that: the module physical form in comprehensive control unit and integrated service unit is standard VPX or LRM pluggable module.
3. electronic equipment on satellite synthesization managing and control system according to claim 1, it is characterized in that: comprehensive control unit and integrated service unit all adopt to be placed at synthesization load cabinet, by expansion, multiple synthesization load cabinet composition synthesization rack.
4. electronic equipment on satellite synthesization managing and control system according to claim 3, it is characterized in that: synthesization load case side wall is connected with synthesization rack relevant position support rivet, front panel screw fastening, synthesization load cabinet is connected with synthesization rack by installing slide rail.
5. electronic equipment on satellite synthesization managing and control system according to claim 1, it is characterized in that: in integrated service unit and comprehensive control unit, use the module of FPGA+CPU structure to adopt standardized designs, namely cpu chip is drawn 2 road kilomega networks, wherein 1 road kilomega network connects FPGA by CPU kilomega network interface chip bus; Carry out logical extension in FPGA inside and realize plate level Management Controller, RapidIO interface, SRIO bus and 2 road 1553B buses.
6. electronic equipment on satellite synthesization managing and control system according to claim 5, it is characterized in that: plate level Management Controller realizes the management of module board level health resources, and is received the supervisory instruction of this module health status and receiving tube control value class module by 1553B bus.
7. electronic equipment on satellite synthesization managing and control system according to claim 6, it is characterized in that: cpu chip is with watchdog circuit, the mutually redundant NORFLASHBootRom memory resource that the DDR3L memory resource that connecting band ECC verifies verifies with band ECC, 1 piece of NanoSSD memory resource connected by SATA bridge chip, wherein cpu chip adopts dominant frequency to be 1GHz, core number is 4, model is the domestic CPU of Loongson3A1000, DDR3L uses density to be 3 8Gbits, clock frequency is 800MHz, model is the chip composition of MicronMT41K1G8, NORFLASHBootRom uses 2 density to be 1Gbits, model is the NORFLASH composition of MicronMT28FW01GABA1LJS-0AAT, NanoSSD uses 1 capacity to be 8Gbits, model is the SLC type NANDFLASH chip composition of MicronMT29F8G08ABABAWP-IT.
8. electronic equipment on satellite synthesization managing and control system according to claim 1, is characterized in that: in comprehensive control unit, high reliable tube control value class module controls OC instruction module in comprehensive control unit for the previous period in task is that in integrated service unit and comprehensive control unit, each electricity consumption module powers up.
9. electronic equipment on satellite synthesization managing and control system according to claim 1, is characterized in that: in comprehensive control unit, system management and control module receives an assignment requirement, is loaded into corresponding system operational parameters, according to system task finishing equipment Resourse Distribute; Before tasks carrying, system management and control module completion system parameter configuration and running parameter decompose, and to assign a task configuration information to each subsystem management and control module; As broken down in said process, control center sends Defect Indication information earthward, wait for ground control centre feedback information, and make system be in holding state, if non-fault, radar microwave imaging function task starts to perform: the sampling of the general signal processing module settling signal in integrated service unit, electro-optic conversion, transmission, opto-electronic conversion, down-converted, and combine digital Wave beam forming, obtain radar return data, complete microwave signal transmitting-receiving process; Integrated service unit walks abreast settling signal process and data prediction, and according to needing to be transferred to conventional data processing module and data store management and control module; Conventional data processing module receiving radar echo data, and perform information processing, output image data, complete radar microwave imaging function.
10. electronic equipment on satellite synthesization managing and control system according to claim 9, it is characterized in that: in comprehensive control unit, data store management and control module and complete data storage, until radar microwave imaging function task terminates, as broken down in operational process, control center sends Defect Indication information earthward, wait for ground control centre feedback information, and make system be in holding state, if non-fault, after radar microwave imaging function job end time arrives, integrated service unit neutron system management and control module reports tasks carrying to report to system management and control module in comprehensive control unit, system management and control module is finished the work comprehensive evaluation, generates debriefing.
CN201510896676.8A 2016-03-10 2016-03-10 Electronic equipment on satellite synthesization managing and control system Active CN105549460B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201510896676.8A CN105549460B (en) 2016-03-10 2016-03-10 Electronic equipment on satellite synthesization managing and control system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201510896676.8A CN105549460B (en) 2016-03-10 2016-03-10 Electronic equipment on satellite synthesization managing and control system

Publications (2)

Publication Number Publication Date
CN105549460A true CN105549460A (en) 2016-05-04
CN105549460B CN105549460B (en) 2018-12-14

Family

ID=55828708

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201510896676.8A Active CN105549460B (en) 2016-03-10 2016-03-10 Electronic equipment on satellite synthesization managing and control system

Country Status (1)

Country Link
CN (1) CN105549460B (en)

Cited By (44)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104079354A (en) * 2014-06-25 2014-10-01 唐智勇 Optical fiber communication system for airship
CN105739416A (en) * 2016-05-06 2016-07-06 上海航天测控通信研究所 Satellite-borne comprehensive electronic computer
CN106502957A (en) * 2016-12-09 2017-03-15 中国电子科技集团公司第三十八研究所 A kind of spaceborne radar data processing and control device based on VPX buses
CN106919153A (en) * 2017-01-12 2017-07-04 西南电子技术研究所(中国电子科技集团公司第十研究所) Electronic equipment on satellite Integrated system management and control framework
CN107544392A (en) * 2017-09-25 2018-01-05 上海卫星工程研究所 The graphical monitoring system and method for the in-orbit distributed-network monitoring platform state of satellite
CN107919903A (en) * 2017-11-21 2018-04-17 中国电子科技集团公司第五十四研究所 A kind of multi-mode satellite communication apparatus based on VPX frameworks
CN108075824A (en) * 2018-01-02 2018-05-25 中国商用飞机有限责任公司北京民用飞机技术研究中心 Common core resource cabinet and comprehensively modularized avionics system
CN108234397A (en) * 2016-12-14 2018-06-29 中国航空工业集团公司西安航空计算技术研究所 A kind of heterogeneous network data transmission method for uplink and method of reseptance based on channel
CN108664433A (en) * 2018-05-11 2018-10-16 成都坤恒顺维科技股份有限公司 A kind of low time delay shake high speed signal switching technology and the backboard using the Technology design
CN108832990A (en) * 2018-06-08 2018-11-16 上海微小卫星工程中心 A kind of space single particle effect instant recovery method for real time communication device
CN109194497A (en) * 2018-07-17 2019-01-11 中国航空无线电电子研究所 Double SRIO Network Backup Systems of software-oriented radio system
CN109189624A (en) * 2018-09-11 2019-01-11 西安微电子技术研究所 A kind of magnanimity information processing device single particle experiment implementation method and single particle test plate
CN109407573A (en) * 2018-09-17 2019-03-01 西北工业大学 A kind of CAN bus based moonlet Integrated Electronic System and method for allocating tasks
CN109462509A (en) * 2018-12-03 2019-03-12 杭州迪普科技股份有限公司 A kind of method and apparatus of the batch backup of board
CN109542063A (en) * 2018-11-21 2019-03-29 上海航天计算机技术研究所 A kind of Complex interface control equipment and spaceborne Integrated Electronic System
CN109660291A (en) * 2019-01-08 2019-04-19 上海卫星工程研究所 A kind of general hardware architecture of load reuse satellite
CN109669397A (en) * 2018-12-07 2019-04-23 北京精密机电控制设备研究所 A kind of FC-AE-1553 fiber buss communication servo controller
CN109687925A (en) * 2019-02-01 2019-04-26 中电科仪器仪表有限公司 A kind of multichannel baseband channel simulator and method
CN109688017A (en) * 2019-01-31 2019-04-26 山东超越数控电子股份有限公司 A kind of dual star topology redundant topology architecture system and framework implementation method
CN109698824A (en) * 2019-02-14 2019-04-30 北京计算机技术及应用研究所 A kind of FC-AE-1553 protocol conversion multi-protocols multi-channel data record system
CN109933374A (en) * 2019-01-23 2019-06-25 西安微电子技术研究所 A kind of computer starting method
CN110542958A (en) * 2019-09-10 2019-12-06 中国电子科技集团公司第四十四研究所 High-temperature-resistant photoelectric conversion module for data communication
CN110661687A (en) * 2019-08-14 2020-01-07 熊猫电子集团有限公司 Full-communication double-bus exchange platform
CN110855581A (en) * 2019-11-18 2020-02-28 天津津航计算技术研究所 Domestic exchange blade device suitable for VPX framework 40G and SRIO multiplexing
CN110996031A (en) * 2019-11-22 2020-04-10 天津津航计算技术研究所 Data recording and playback device based on Ethernet and SRIO
CN110996032A (en) * 2019-11-22 2020-04-10 天津津航计算技术研究所 Data recording and playback method based on Ethernet and SRIO
CN111327508A (en) * 2020-01-19 2020-06-23 浙江中控研究院有限公司 FC-AE-1553 and BLVDS bus bridging system and method
CN111404750A (en) * 2020-03-20 2020-07-10 上海航天测控通信研究所 Centralized parameter management device and method for advanced on-orbit system
CN111506044A (en) * 2020-04-23 2020-08-07 北京空间技术研制试验中心 General off-line detection device for spacecraft
CN111538263A (en) * 2020-04-02 2020-08-14 华东计算技术研究所(中国电子科技集团公司第三十二研究所) On-board computer module operation system and method and aerospace device
CN111611114A (en) * 2020-03-30 2020-09-01 西南电子技术研究所(中国电子科技集团公司第十研究所) Integrated avionics PHM system
CN111930353A (en) * 2020-08-12 2020-11-13 Oppo(重庆)智能科技有限公司 Sensor driving architecture implementation method, device, architecture, terminal equipment and medium
CN111951150A (en) * 2020-07-16 2020-11-17 中国人民解放军军事科学院国防科技创新研究院 Satellite-borne data processing system
CN112099833A (en) * 2020-08-07 2020-12-18 北京控制工程研究所 Remote updating method for firmware of satellite-borne computer
CN113341814A (en) * 2021-06-11 2021-09-03 哈尔滨工业大学 Unmanned aerial vehicle flight control computer evaluation system
CN113612742A (en) * 2021-07-23 2021-11-05 中国人民解放军军事科学院国防科技创新研究院 Multi-mode search and rescue signal processing device based on VPX framework
CN113806290A (en) * 2021-08-27 2021-12-17 中国航空无线电电子研究所 High-integrity system-on-chip for comprehensive modular avionics system
CN114697321A (en) * 2022-01-12 2022-07-01 中国电子科技集团公司第十研究所 Distributed comprehensive reconfigurable electronic system platform architecture
CN115102602A (en) * 2022-05-25 2022-09-23 中国电子科技集团公司第十研究所 Domestic satellite-borne resource management and task scheduling equipment and method
CN115185877A (en) * 2022-07-29 2022-10-14 中航机载系统共性技术有限公司 Dual-redundancy general processing module and information synchronization method thereof
CN115484123A (en) * 2022-08-03 2022-12-16 中国空间技术研究院 Communication satellite integrated electronic network communication method based on high-speed bus
CN115793551A (en) * 2023-02-08 2023-03-14 中国电子科技集团公司第十研究所 Space electronic load super-large scale multifunctional comprehensive processing platform
CN115902980A (en) * 2023-02-15 2023-04-04 东方空间(西安)宇航技术有限公司 Flight target space-based monitoring and predicting method and device capable of being updated online
CN117375062A (en) * 2023-11-23 2024-01-09 中铁电气化勘测设计研究院有限公司 Intelligent control system of flexible direct-current traction substation

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101833536A (en) * 2010-04-16 2010-09-15 北京航空航天大学 Reconfigurable on-board computer of redundancy arbitration mechanism
CN104015939A (en) * 2014-05-26 2014-09-03 中国科学院长春光学精密机械与物理研究所 Comprehensive management system for platform and load integrated satellite

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101833536A (en) * 2010-04-16 2010-09-15 北京航空航天大学 Reconfigurable on-board computer of redundancy arbitration mechanism
CN104015939A (en) * 2014-05-26 2014-09-03 中国科学院长春光学精密机械与物理研究所 Comprehensive management system for platform and load integrated satellite

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
兰盛昌,王松,徐国栋: "一种面向任务优化的多核心星务管理系统设计", 《哈尔滨工业大学学报》 *
高朝辉,张琦,陈金勇,颜博: "支持插件扩展的卫星任务管控平台研究", 《无线电工程》 *

Cited By (66)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104079354A (en) * 2014-06-25 2014-10-01 唐智勇 Optical fiber communication system for airship
CN105739416A (en) * 2016-05-06 2016-07-06 上海航天测控通信研究所 Satellite-borne comprehensive electronic computer
CN106502957A (en) * 2016-12-09 2017-03-15 中国电子科技集团公司第三十八研究所 A kind of spaceborne radar data processing and control device based on VPX buses
CN106502957B (en) * 2016-12-09 2019-10-18 中国电子科技集团公司第三十八研究所 A kind of spaceborne radar data processing and control device based on VPX bus
CN108234397A (en) * 2016-12-14 2018-06-29 中国航空工业集团公司西安航空计算技术研究所 A kind of heterogeneous network data transmission method for uplink and method of reseptance based on channel
CN106919153A (en) * 2017-01-12 2017-07-04 西南电子技术研究所(中国电子科技集团公司第十研究所) Electronic equipment on satellite Integrated system management and control framework
CN107544392A (en) * 2017-09-25 2018-01-05 上海卫星工程研究所 The graphical monitoring system and method for the in-orbit distributed-network monitoring platform state of satellite
CN107919903A (en) * 2017-11-21 2018-04-17 中国电子科技集团公司第五十四研究所 A kind of multi-mode satellite communication apparatus based on VPX frameworks
CN108075824A (en) * 2018-01-02 2018-05-25 中国商用飞机有限责任公司北京民用飞机技术研究中心 Common core resource cabinet and comprehensively modularized avionics system
CN108664433A (en) * 2018-05-11 2018-10-16 成都坤恒顺维科技股份有限公司 A kind of low time delay shake high speed signal switching technology and the backboard using the Technology design
CN108832990B (en) * 2018-06-08 2021-03-16 上海微小卫星工程中心 Space single event effect instant recovery method for real-time communication equipment
CN108832990A (en) * 2018-06-08 2018-11-16 上海微小卫星工程中心 A kind of space single particle effect instant recovery method for real time communication device
CN109194497A (en) * 2018-07-17 2019-01-11 中国航空无线电电子研究所 Double SRIO Network Backup Systems of software-oriented radio system
CN109189624B (en) * 2018-09-11 2022-02-01 西安微电子技术研究所 Mass information processor single particle test implementation method and single particle test board
CN109189624A (en) * 2018-09-11 2019-01-11 西安微电子技术研究所 A kind of magnanimity information processing device single particle experiment implementation method and single particle test plate
CN109407573A (en) * 2018-09-17 2019-03-01 西北工业大学 A kind of CAN bus based moonlet Integrated Electronic System and method for allocating tasks
CN109542063A (en) * 2018-11-21 2019-03-29 上海航天计算机技术研究所 A kind of Complex interface control equipment and spaceborne Integrated Electronic System
CN109462509A (en) * 2018-12-03 2019-03-12 杭州迪普科技股份有限公司 A kind of method and apparatus of the batch backup of board
CN109462509B (en) * 2018-12-03 2022-07-29 杭州迪普科技股份有限公司 Method and device for batch backup of board cards
CN109669397A (en) * 2018-12-07 2019-04-23 北京精密机电控制设备研究所 A kind of FC-AE-1553 fiber buss communication servo controller
CN109660291A (en) * 2019-01-08 2019-04-19 上海卫星工程研究所 A kind of general hardware architecture of load reuse satellite
CN109660291B (en) * 2019-01-08 2021-06-11 上海卫星工程研究所 General hardware system of load multiplexing satellite
CN109933374A (en) * 2019-01-23 2019-06-25 西安微电子技术研究所 A kind of computer starting method
CN109688017A (en) * 2019-01-31 2019-04-26 山东超越数控电子股份有限公司 A kind of dual star topology redundant topology architecture system and framework implementation method
CN109687925A (en) * 2019-02-01 2019-04-26 中电科仪器仪表有限公司 A kind of multichannel baseband channel simulator and method
CN109698824B (en) * 2019-02-14 2022-02-22 北京计算机技术及应用研究所 FC-AE-1553 protocol conversion multi-protocol multi-channel data recording system
CN109698824A (en) * 2019-02-14 2019-04-30 北京计算机技术及应用研究所 A kind of FC-AE-1553 protocol conversion multi-protocols multi-channel data record system
CN110661687A (en) * 2019-08-14 2020-01-07 熊猫电子集团有限公司 Full-communication double-bus exchange platform
CN110661687B (en) * 2019-08-14 2021-11-05 熊猫电子集团有限公司 Full-communication double-bus exchange platform
CN110542958A (en) * 2019-09-10 2019-12-06 中国电子科技集团公司第四十四研究所 High-temperature-resistant photoelectric conversion module for data communication
CN110855581A (en) * 2019-11-18 2020-02-28 天津津航计算技术研究所 Domestic exchange blade device suitable for VPX framework 40G and SRIO multiplexing
CN110996031B (en) * 2019-11-22 2021-11-16 天津津航计算技术研究所 Data recording and playback device based on Ethernet and SRIO
CN110996032B (en) * 2019-11-22 2021-11-16 天津津航计算技术研究所 Data recording and playback method based on Ethernet and SRIO
CN110996032A (en) * 2019-11-22 2020-04-10 天津津航计算技术研究所 Data recording and playback method based on Ethernet and SRIO
CN110996031A (en) * 2019-11-22 2020-04-10 天津津航计算技术研究所 Data recording and playback device based on Ethernet and SRIO
CN111327508A (en) * 2020-01-19 2020-06-23 浙江中控研究院有限公司 FC-AE-1553 and BLVDS bus bridging system and method
CN111404750B (en) * 2020-03-20 2022-11-01 上海航天测控通信研究所 Centralized parameter management device and method for advanced on-orbit system
CN111404750A (en) * 2020-03-20 2020-07-10 上海航天测控通信研究所 Centralized parameter management device and method for advanced on-orbit system
CN111611114A (en) * 2020-03-30 2020-09-01 西南电子技术研究所(中国电子科技集团公司第十研究所) Integrated avionics PHM system
CN111611114B (en) * 2020-03-30 2023-04-07 西南电子技术研究所(中国电子科技集团公司第十研究所) Integrated avionics PHM system
CN111538263A (en) * 2020-04-02 2020-08-14 华东计算技术研究所(中国电子科技集团公司第三十二研究所) On-board computer module operation system and method and aerospace device
CN111506044A (en) * 2020-04-23 2020-08-07 北京空间技术研制试验中心 General off-line detection device for spacecraft
CN111506044B (en) * 2020-04-23 2021-05-18 北京空间技术研制试验中心 General off-line detection device for spacecraft
CN111951150A (en) * 2020-07-16 2020-11-17 中国人民解放军军事科学院国防科技创新研究院 Satellite-borne data processing system
CN111951150B (en) * 2020-07-16 2022-02-18 中国人民解放军军事科学院国防科技创新研究院 Satellite-borne data processing system
CN112099833A (en) * 2020-08-07 2020-12-18 北京控制工程研究所 Remote updating method for firmware of satellite-borne computer
CN112099833B (en) * 2020-08-07 2023-07-14 北京控制工程研究所 Remote updating method for firmware of spaceborne computer
CN111930353A (en) * 2020-08-12 2020-11-13 Oppo(重庆)智能科技有限公司 Sensor driving architecture implementation method, device, architecture, terminal equipment and medium
CN111930353B (en) * 2020-08-12 2023-12-15 Oppo(重庆)智能科技有限公司 Sensor driving architecture implementation method, device, architecture, terminal equipment and medium
CN113341814A (en) * 2021-06-11 2021-09-03 哈尔滨工业大学 Unmanned aerial vehicle flight control computer evaluation system
CN113341814B (en) * 2021-06-11 2022-08-23 哈尔滨工业大学 Unmanned aerial vehicle flight control computer evaluation system
CN113612742A (en) * 2021-07-23 2021-11-05 中国人民解放军军事科学院国防科技创新研究院 Multi-mode search and rescue signal processing device based on VPX framework
CN113612742B (en) * 2021-07-23 2023-04-18 中国人民解放军军事科学院国防科技创新研究院 Multi-mode search and rescue signal processing device based on VPX framework
CN113806290A (en) * 2021-08-27 2021-12-17 中国航空无线电电子研究所 High-integrity system-on-chip for comprehensive modular avionics system
CN113806290B (en) * 2021-08-27 2023-10-27 中国航空无线电电子研究所 High-integrity system-on-a-chip for integrated modular avionics systems
CN114697321A (en) * 2022-01-12 2022-07-01 中国电子科技集团公司第十研究所 Distributed comprehensive reconfigurable electronic system platform architecture
CN114697321B (en) * 2022-01-12 2023-05-12 中国电子科技集团公司第十研究所 Distributed comprehensive reconfigurable electronic system platform architecture
CN115102602A (en) * 2022-05-25 2022-09-23 中国电子科技集团公司第十研究所 Domestic satellite-borne resource management and task scheduling equipment and method
CN115102602B (en) * 2022-05-25 2023-08-15 中国电子科技集团公司第十研究所 Scheduling method of domestic satellite-borne resource management and task scheduling equipment
CN115185877B (en) * 2022-07-29 2023-09-05 中航机载系统共性技术有限公司 Dual-redundancy general processing module and information synchronization method thereof
CN115185877A (en) * 2022-07-29 2022-10-14 中航机载系统共性技术有限公司 Dual-redundancy general processing module and information synchronization method thereof
CN115484123A (en) * 2022-08-03 2022-12-16 中国空间技术研究院 Communication satellite integrated electronic network communication method based on high-speed bus
CN115793551A (en) * 2023-02-08 2023-03-14 中国电子科技集团公司第十研究所 Space electronic load super-large scale multifunctional comprehensive processing platform
CN115793551B (en) * 2023-02-08 2023-06-02 中国电子科技集团公司第十研究所 Ultra-large-scale multifunctional comprehensive processing platform for space electronic load
CN115902980A (en) * 2023-02-15 2023-04-04 东方空间(西安)宇航技术有限公司 Flight target space-based monitoring and predicting method and device capable of being updated online
CN117375062A (en) * 2023-11-23 2024-01-09 中铁电气化勘测设计研究院有限公司 Intelligent control system of flexible direct-current traction substation

Also Published As

Publication number Publication date
CN105549460B (en) 2018-12-14

Similar Documents

Publication Publication Date Title
CN105549460A (en) Satellite-borne electronic equipment comprehensive management and control system
CN105279133B (en) VPX Parallel DSP Signal transacting board analysis based on SoC on-line reorganizations
WO2015180000A1 (en) Comprehensive management system for platform and payload integrated satellite
CN111309477A (en) Satellite on-orbit data processing system and method
CN109885526B (en) Information processing platform based on OpenVPX bus
CN102567273A (en) Miniature integrated core processor based on fiber channel (FC) network
CN101819556A (en) Signal-processing board
CN109271330A (en) General BMC system based on synthesization information system
CN103197231A (en) Field programmable gate array (FPGA) device for diagnosing and predicting artificial circuit faults
CN105549901A (en) Satellite-borne integrated mass data storage and playback equipment
CN105138495A (en) ARINC659 bus controller with embedded microcontroller
CN105515673B (en) A kind of optical-fibre channel node card
CN105137864A (en) Lower computer coordinative control SoC chip for spacecraft
CN103984394A (en) High-density and energy-saving blade server system
CN105045566B (en) A kind of embedded type parallel computation system and the parallel calculating method using it
CN211149445U (en) High-speed data processing platform
CN103294025A (en) Intelligent management and control system and method of energy consumption of internet of things
CN105550131A (en) Finite-state machine and ARINC659 bus based interface data processing system and method
CN105471652A (en) Big data integrated machine and redundant management unit thereof
CN102541810A (en) Miniature low-power consumption comprehensive kernel processor based on avionics full duplex switched Ethernet (AFDX)
CN102638306A (en) 1394b optical bus monitor and monitoring method thereof
CN111796507A (en) Rocket-borne full-redundancy comprehensive electronic system
CN110166334B (en) Spatial information system based on SpaceVPX standard
CN104750581A (en) Redundant interconnection memory-shared server system
CN212849980U (en) Intelligent fusion device for power distribution network

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant