CN103116285B - For the dual processors unibus computer system of deep space probe - Google Patents
For the dual processors unibus computer system of deep space probe Download PDFInfo
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- CN103116285B CN103116285B CN201110366041.9A CN201110366041A CN103116285B CN 103116285 B CN103116285 B CN 103116285B CN 201110366041 A CN201110366041 A CN 201110366041A CN 103116285 B CN103116285 B CN 103116285B
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Abstract
The present invention relates to Aerospace Control equipment, disclose a kind of dual processors unibus computer system for deep space probe.Comprise power module (101), CPU module (102) form two redundancy by CPUA plate and CPUB plate, internal bus (103), functional module (104), autonomous supervision module (105) have the observation circuit of A machine health signal and cut machine control circuit, handover module (106) is subject to autonomous supervision module controls from master instruction, carries out out the action that B closes A.The present invention adopts incomplete redundancy and single bus architecture, possess automatic fault diagnosis and system reconfiguration function, reliably can complete all functions of integrated electronics computing machine, solve the miniaturization of survey of deep space applicator platform computing machine, lightness, low-power consumption, highly reliable problem.
Description
Technical field
The present invention relates to Aerospace Control equipment, particularly a kind of dual processors unibus computer system for deep space probe.
Background technology
In conventional flight applicator platform Computer Design and development, generally all adopt the architecture of the symmetrical redundancy of full two-shipper.Namely a host A adds an identical standby host B of design, and standby machine respectively comprises complete power module, CPU module and functional module, and two-shipper has independently internal bus, works alone separately, only in parallel in the isolation of external interface place.Under cold standby state, the duty of heat engine is monitored by self house dog hardware, and do not have independently monitoring modular, switching command is also sent by heat engine self.
Aircraft platforms computing machine due to prior art adopts the architecture of the symmetrical redundancy of full two-shipper, thus volume is too huge, for deep space probe, can not realize miniaturization and lightness on the one hand, on the other hand, dependent monitoring modular also may affect the reliability of complete machine.
Current Aerospace Control field does not find explanation or the report of the similar correlation technique with the present invention, not yet collects similar data both at home and abroad yet.
Summary of the invention
In order to solve deep space probe miniaturization, lightness, low-power consumption, autonomous operation and highly reliable problem, the object of the present invention is to provide a kind of dual processors unibus computer system for deep space probe.Utilize the present invention, the object of system compact can be reached, realize system autonomous operation, improve the reliability of system.
In order to reach foregoing invention object, the present invention is to provide a kind of dual processors unibus computer system for deep space probe for the technical scheme that its technical matters of solution adopts, and this device comprises:
Power module, it comprises power module and the two redundancy of B electromechanical source module composition of A machine; The CPU module being respectively A, B machine provides+5V to power; Power module on duty provides+5V ,+12V ,-12V to power for functional module; B electromechanical source module provides+12V to power for autonomous supervision module;
CPU module, form two redundancy by CPUA plate and CPUB plate, it comprises CPU and peripheral circuit thereof, is responsible for operational system software, export control and address, data-signal, implement the control to all functions module, receive the data from functional module; The CPU module of A machine also continues to send the normal burst signal characterizing own health;
Internal bus, it is merged into a set of bus after the control of cooling and heating machine CPU module, address, data bus signal being isolated by the chip with cold high resistant characteristic, connects all functions module;
Functional module, comprise feature board 1 and feature board 2, it has various interface type, the various external interface functions of computing machine are responsible for, then hang on the public internal bus of two-shipper in system, accept the control of CPU module on duty, its power supply is provided by power module on duty, can be switched by transfer relay between two-shipper power supply;
Autonomous supervision module is the circuit module independent of A machine, comprises the observation circuit of A machine health signal and cuts machine control circuit; Be responsible for receiving and differentiating the normal signal that A machine CPU module exports, send to commutation circuit module when A machine normal signal disappears and independently cut machine instruction;
Handover module, it comprises carries out the relay J 1 of switch control rule to two-shipper power module and functional module is carried out to the relay group J2 of power switching; Two group relaies all can accept the control of direct telecommand, in addition, relay J 1 can be subject to controlling from master instruction of monitoring module, carries out out the action that B closes A, relay group J2 can be subject to the control of B machine CPU module from master instruction, by feature board power switching to B electromechanical source.
Above-mentioned CPU module is two redundancy cold standbies, the design of A, B machine is identical, + the 5V that they receive corresponding power module separately provides powers, the control to functional module is implemented by internal bus, and A machine CPU module sends to monitoring module and characterizes healthy normal signal, B machine CPU module then sends to handover module and independently cuts machine instruction under A machine failure condition; The control that described internal bus sends CPUA, B module, address, data bus signal are isolated, and are merged into a set of bus, connect all functions module; Described functional module completes the various interface functions of computing machine, hangs on the public internal bus of two-shipper, accepts the control of CPU module on duty, and its power supply switches acquisition by handover module to A, B electromechanical source module; The power supply of described autonomous supervision module often opens DC/DC by B electromechanical source module to be provided, and it receives and differentiates the normal signal that A machine CPU module exports, and sends independently cut machine instruction under judgement A machine failure condition to commutation circuit; Described handover module receives machine of independently the cutting instruction of direct telecommand or autonomous supervision module transmission, implements switch control rule, the i.e. mutual exclusion of A, B machine to A, B electromechanical source module; Receive the autonomous handoff functionality plate power supply instruction of direct telecommand or the transmission of B machine CPU module, implement to switch to the power supply of functional module.
A kind of dual processors unibus computer system for deep space probe of the present invention, owing to taking above-mentioned technical scheme, adopt the architecture of the incomplete redundancy of dual processors unibus, on the one hand redundancy backup is carried out to nucleus module, then effectively can reduce the volume and weight of system on the other hand, reduce power consumption, independently autonomous supervision module can carry out system reconfiguration, can successfully manage space fault.Therefore the invention solves deep space probe miniaturization, lightness, low-power consumption, autonomous operation and highly reliable problem, reach following beneficial effect:
1. provide reliable, general deep space exploration aircraft computer system redundant mode;
2. can effectively reduce system bulk, weight, power consumption;
3. can realize autonomous operation and failure reconfiguration, improve the reliability of system.
Accompanying drawing explanation
Fig. 1 is the theory diagram of the present invention for the dual processors unibus computer system of deep space probe;
Fig. 2 is the structural representation of the present invention for the dual processors unibus computer system of deep space probe.
Embodiment
Below in conjunction with accompanying drawing, the preferred embodiments of the present invention are described.
Fig. 1 is the theory diagram of the present invention for the dual processors unibus computer system of deep space probe.As shown in the illustrated embodiment of fig. 1, native system external interface connects other each subsystem QT in detector, comprising: send all telecommands by remote terminal machine YKZD and open A and close B instruction KAGB, open B and close A instruction KBGA, feature board power supply tangential A machine instruction QXAJ, feature board power supply tangential B machine instruction QXBJ four instructions, native system is powered and to be provided by power-supply system DYXT.
When YKZD sends KAGB instruction, native system power supply A opens B and closes, and CPUA works.
When YKZD sends KBGA instruction, native system power supply B opens A and closes, and CPUB works.
When YKZD sends QXAJ instruction, the tangential power supply A of native system all functions module for power supply.
When YKZD sends QXBJ instruction, the tangential power supply B of native system all functions module for power supply.
Fig. 2 is the structural representation of the present invention for the dual processors unibus computer system of deep space probe.As shown for example in fig. 2, this system comprises:
Power module 101, forms two redundancy by secondary power supply A and secondary power supply B; It comprises the DC/DC module of A machine and the DC/DC module of B machine, and the CPU module 102 being respectively A, B machine provides+5V to power; Power module on duty provides+5V ,+12V ,-12V to power for functional module 104; B electromechanical source module provides+12V to power for autonomous supervision module.
CPU module 102, form two redundancy by CPUA plate and CPUB plate, it comprises the circuit such as CPU and peripheral storage thereof, is responsible for operational system software, export control and address, data-signal, implement the control to all functions module, receive the data from functional module.The CPU module of A machine also should continue to send the normal burst signal characterizing own health.
Internal bus 103, it, after being isolated by the bus signals such as the control of cooling and heating machine CPU module, address, data by the chip with cold high resistant characteristic, is merged into a set of bus, connects all functions module.
Functional module 104, comprise feature board 1 and feature board 2, it has various interface type, the various external interface functions of computing machine are responsible for, then hang on the public internal bus of two-shipper in system, accept the control of CPU module on duty, its power supply is provided by power module on duty, can be switched by transfer relay between two-shipper power supply.
Autonomous supervision module 105 is the circuit modules independent of A machine, comprises the observation circuit of A machine health signal and cuts machine control circuit.Be responsible for receiving and differentiating the normal signal that A machine CPU module exports, send to commutation circuit when A machine normal signal disappears and independently cut machine instruction.
Handover module 106, it comprises carries out the relay J 1 of switch control rule to two-shipper power module and functional module is carried out to the relay group J2 of power switching.Two group relaies all can accept the control of direct telecommand, in addition, relay J 1 can be subject to controlling from master instruction of autonomous supervision module 105, carries out out the action that B closes A, relay group J2 can be subject to the control of B machine CPU module from master instruction, by feature board power switching to B electromechanical source.
Above-mentioned CPU module 102 is two redundancy cold standbies, the design of A, B machine is identical, + the 5V that they receive corresponding power module 101 separately provides powers, the control to functional module 104 is implemented by internal bus 103, and A machine CPU module sends to monitoring module 105 and characterizes healthy normal signal, and B machine CPU module then sends to handover module 106 and independently cuts machine instruction under A machine failure condition; Internal bus 103, the bus signals such as the control that it sends CPUA, B module, address, data are isolated, and are merged into a set of bus, connect all functions module 104; Functional module 104, completes the various interface functions of computing machine, hangs on the public internal bus 103 of two-shipper, accepts the control of CPU module 102 on duty, and its power supply switches acquisition by handover module 106 pairs of A, B electromechanical source modules 101; Autonomous supervision module 105, its power supply often opens DC/DC by one of them of B electromechanical source module 101 to be provided, and it receives and differentiates the normal signal that A machine CPU module 102 exports, and is judging to send to commutation circuit 105 under A machine failure condition independently to cut machine instruction; Handover module 106, receive machine of independently the cutting instruction of direct telecommand or autonomous supervision module 105 transmission, switch control rule (mutual exclusion of A, B machine) is implemented to A, B electromechanical source module 101, receive the autonomous handoff functionality plate power supply instruction of direct telecommand or the transmission of B machine CPU module 102, implement to switch to the power supply of functional module 104.
Above-mentioned power module 101 comprises the output DC/DC of+5V and the DC/DC of output ± 12V, the unified control being subject to change-over switch 106 of two DC/DC of its A machine module, open or close simultaneously, and B machine module only has the control of DC/DC by change-over switch 106 of+5V, its ± DC/DC of 12 is in normally open, for monitoring module 105 is powered.
Above-mentioned internal bus 103 is formed in parallel after isolation by the bus of A machine CPU and B machine CPU, dual processors is in heat engine and cold state respectively, after being isolated by the isolating chip with cold high-impedance state, the bus parallel connection of cold and heat engine, effectively can isolate the impact of cold on heat engine, internal bus is effectively worked.
Above-mentioned monitoring module 105 is responsible for monitoring the health status of A machine CPU module 102, the normal signal alternating impulse that its A machine sends is monitored, predetermined time (3 seconds) is exceeded when normal signal disappears, then send and independently cut machine instruction to machine of the cutting relay J 1 of handover module 106, control its action, close A electromechanical source module 101, open B electromechanical source module 101 simultaneously.
Above-mentioned handover module 106 comprises and carries out the relay J 1 of switch control rule to two-shipper power module 101 and functional module 104 is carried out to the relay group J2 of power switching.Two group relaies all can accept the control of direct telecommand, in addition, the action that B closes A is carried out out in the control that relay J 1 can be subject to monitoring module 105, relay group J2 can be subject to the control of B machine CPU module 102, when cutting machine, after B machine CPU working on power, independently sending feature board and to power tangential B-source instruction, then J2 action, supplies cable address to B electromechanical source feature board.
Below in conjunction with accompanying drawing 2, course of action of the present invention is described.
System electrification initial state: power supply A and CPUA works, each functional module power supply hangs on A electromechanical source; + the 5VDC/DC of power supply B is in off-mode, power supply B ± 12VDC/DC is in normally open, and CPUB is in cold state; CPUA occupies internal bus.
System operation: under normal circumstances, each block combiner state is as powered on as described in initial state; CPUA continues the pulse signal sending alternation to monitoring module, characterizes self health status.
A machine fault handling: when A machine normal signal disappears, then monitoring module sends and cuts machine instruction ,+5VDC/DC the start of power supply B, CPUB powers on; Power supply A closes, and CPUA quits work and enters cold state; The instruction of CPUB sending function plate electrical source exchange, feature board supplies cable address to B electromechanical source by the actuating of relay; CPUB occupies internal bus, and system reconfiguration completes.
Telecommand cuts machine: send direct telecommand and cut machine, should be divided into two steps, B machine as tangential in A machine, and first send and open the A instruction of B pass, then sending function plate power supply tangential B machine instruction, vice versa.
As mentioned above, the present invention adopts the dual processors unibus computer architecture with automatic fault diagnosis and handoff functionality, solves the miniaturization of deep space exploration aircraft computing machine, lightness, low-power consumption, highly reliable problem.Obviously, those skilled in the art can carry out various change and distortion to architecture of the present invention and not depart from the spirit and scope of the present invention.Like this, if these amendments of the present invention 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 (6)
1., for a dual processors unibus computer system for deep space probe, it is characterized in that, this system comprises:
Power module, it comprises A electromechanical source module and the two redundancy of B electromechanical source module composition; The CPU module being respectively A, B machine provides+5V to power; Power module on duty provides+5V ,+12V ,-12V to power for functional module; B electromechanical source module provides+12V to power for autonomous supervision module;
CPU module, form two redundancy by CPUA plate and CPUB plate, it comprises CPU and peripheral circuit thereof, is responsible for operational system software, export control and address, data-signal, implement the control to all functions module, receive the data from functional module; The CPU module of A machine also continues to send the normal burst signal characterizing own health;
Internal bus, it is merged into a set of bus after the control of cooling and heating machine CPU module, address, data bus signal being isolated by the chip with cold high resistant characteristic, connects all functions module;
Functional module, comprise feature board 1 and feature board 2, it has various interface type, the various external interface functions of computing machine are responsible for, then hang on the public internal bus of two-shipper in system, accept the control of CPU module on duty, its power supply is provided by power module on duty, can be switched by transfer relay between two-shipper power supply;
Autonomous supervision module is the circuit module independent of A machine, comprises the observation circuit of A machine health signal and cuts machine control circuit; Be responsible for receiving and differentiating the normal signal that A machine CPU module exports, send to commutation circuit module when A machine normal signal disappears and independently cut machine instruction;
Handover module, it comprises carries out the relay J 1 of switch control rule to two-shipper power module and functional module is carried out to the relay J 2 of power switching; Two group relaies all can accept the control of direct telecommand, in addition, relay J 1 can be subject to controlling from master instruction of autonomous supervision module, carries out out the action that B closes A, relay J 2 can be subject to the control of B machine CPU module from master instruction, by feature board power switching to B electromechanical source.
2. dual processors unibus computer system as claimed in claim 1, it is characterized in that: described CPU module is two redundancy cold standby, the design of A, B machine is identical, + the 5V that they receive corresponding power module separately provides powers, the control to functional module is implemented by internal bus, and A machine CPU module sends to monitoring module and characterizes healthy normal signal, B machine CPU module then sends to handover module and independently cuts machine instruction under A machine failure condition; The control that described internal bus sends CPUA, CPUB module, address, data bus signal are isolated, and are merged into a set of bus, connect all functions module; Described functional module completes the various interface functions of computing machine, hangs on the public internal bus of two-shipper, accepts the control of CPU module on duty, and its power supply switches acquisition by handover module to A, B electromechanical source module; The power supply of described autonomous supervision module often opens DC/DC by B electromechanical source module to be provided, and it receives and differentiates the normal signal that A machine CPU module exports, and sends independently cut machine instruction under judgement A machine failure condition to commutation circuit; Described handover module receives machine of independently the cutting instruction of direct telecommand or autonomous supervision module transmission, A, B electromechanical source module is implemented to the switch control rule of A, B machine mutual exclusion; Receive the autonomous handoff functionality plate power supply instruction of direct telecommand or the transmission of B machine CPU module, implement to switch to the power supply of functional module.
3. dual processors unibus computer system as claimed in claim 1, it is characterized in that: described power module comprises the output DC/DC of+5V and the DC/DC of output ± 12V, the unified control being subject to change-over switch of two DC/DC of its A machine module, open or close simultaneously, and B machine module only has the control of DC/DC by change-over switch of+5V, its ± DC/DC of 12V is in normally open, for monitoring module is powered.
4. dual processors unibus computer system as claimed in claim 1, it is characterized in that: described internal bus is formed in parallel after isolation by the bus of A machine CPU and B machine CPU, dual processors is in heat engine and cold state respectively, after being isolated by the isolating chip with cold high-impedance state, the bus parallel connection of cold and heat engine.
5. dual processors unibus computer system as claimed in claim 1, it is characterized in that: described autonomous supervision module is monitored the normal signal alternating impulse that A machine sends, predetermined time is exceeded when normal signal disappears, then send and independently cut machine instruction to machine of the cutting relay J 1 of handover module, control its action, close A electromechanical source module, open B electromechanical source module simultaneously.
6. dual processors unibus computer system as claimed in claim 1, it is characterized in that: when cutting machine, after B machine CPU works on power, described handover module independently sends feature board and to power the instruction of tangential B-source, then relay J 2 action, supplies cable address to B electromechanical source feature board.
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| CN201110366041.9A CN103116285B (en) | 2011-11-17 | 2011-11-17 | For the dual processors unibus computer system of deep space probe |
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| CN201110366041.9A CN103116285B (en) | 2011-11-17 | 2011-11-17 | For the dual processors unibus computer system of deep space probe |
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| CN103116285B true CN103116285B (en) | 2016-04-20 |
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Families Citing this family (11)
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| CN105550074B (en) * | 2015-12-08 | 2018-06-19 | 中国计量大学 | Aerospace computer |
| CN106125544A (en) * | 2016-07-12 | 2016-11-16 | 浙江众合科技股份有限公司 | A kind of temperature of track switch controller that is applicable to is for redundant system |
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| CN107517001B (en) * | 2017-09-20 | 2024-06-14 | 重庆聚陆新能源有限公司 | Reconfigurable DC/DC converter |
| CN109782578A (en) * | 2018-12-24 | 2019-05-21 | 中国船舶重工集团公司第七一0研究所 | A kind of high reliability deep-sea autonomous underwater vehicle control method |
| CN111400109B (en) * | 2020-04-07 | 2023-08-01 | 上海航天计算机技术研究所 | Dual-machine redundancy backup system based on PCIe high-speed bus interface |
| CN113783295A (en) * | 2021-08-10 | 2021-12-10 | 北京航天发射技术研究所 | Remote control device and method for power distribution system |
| CN114116279A (en) * | 2021-11-08 | 2022-03-01 | 陕西千山航空电子有限责任公司 | Electromechanical management system |
| CN114488888B (en) * | 2022-01-14 | 2024-01-30 | 上海卫星工程研究所 | spaceVPX architecture-based satellite-borne stand-alone dual-redundancy high-reliability power supply |
| CN117519007A (en) * | 2023-10-27 | 2024-02-06 | 北京航天晨信科技有限责任公司 | Three-level intelligent shift system, method, equipment management software and product |
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