CN103192998B - System-level emergency response device of spacecraft - Google Patents
System-level emergency response device of spacecraft Download PDFInfo
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- CN103192998B CN103192998B CN201310035948.6A CN201310035948A CN103192998B CN 103192998 B CN103192998 B CN 103192998B CN 201310035948 A CN201310035948 A CN 201310035948A CN 103192998 B CN103192998 B CN 103192998B
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Abstract
The invention discloses a system-level emergency response device of a spacecraft. Through adoption of a micro technology and micro devices and components, platform design and emergency mechanism design of the spacecraft are coordinated from a top layer of a spacecraft system; main emergency response functions are implemented in an emergency response device; and the platform design only considers the conventional redundancy measures, thereby reducing the coupling degree and the complexity of each spacecraft subsystem due to consideration of emergency design. The emergency response device of the spacecraft achieves an independent power supply function, a spacecraft state monitoring function and a data recording function and is not coupled with an energy subsystem, a measurement and control subsystem, a satellite service subsystem, an attitude and orbit control subsystem and the like of the spacecraft platform; when the subsystems meet emergencies in orbit, the emergency response device of the spacecraft can independently achieve a satellite-ground communication function, a low-precision attitude measurement function and the like, can provide spacecraft state monitoring data and historical spacecraft state data for the ground to eliminate failures; and the emergency response device of the spacecraft is small in volume, low in mass loss (lower than 10kg) and independent and controlled in functions.
Description
Technical field
The present invention relates to a kind of spacecraft emergency response facility, particularly relate to a kind of Space Vehicle System level emergency response facility, belong to space technology field.
Background technology
Space mission is owing to substantially can not safeguard in-orbit both at home and abroad at present, and all devise the success that various redundant means ensures task, nonetheless spacecraft also various fault often occurs in-orbit, causes spacecraft mission failure.Spacecraft emergency mechanism design be the key issue that Space Vehicle System engineering must be considered, be included in the crucial subsystems such as the spacecraft energy, observing and controlling, Star Service, rail control break down in-orbit after counter-measure.Except adopting conventional redundancy backup means, spacecraft generally also can take more complicated isomery degradation backup mode reply emergency condition, current emergency response facility is distributed in each subsystem of spacecraft, it is larger that emergency design and normal platform design degree of coupling, add spacecraft complexity, when major failure appears in energy subsystem etc., spacecraft emergency response demand often can not be met.Such as rail control subsystem, Star Service subsystem all devise the emergency controller of respective degraded mode; Software recombination function is devised between the different spaceborne computers possessing bus interface.In recent years, after some spacecrafts generation problem in-orbit, expose the defect that spacecraft emergency response Mechanism Design exists, do not fully take into account some extreme cases, spacecraft emergency response demand can not be met, as the telemetry data lacked before and after fault complete accurately positioning problems, lack the spacecraft after major failure and to leave the right or normal track means etc.
Transmitted the Nano satellite of more than 70 both at home and abroad to the end of the year 2011, the micro-scale technology that Nano satellite carries and micro-module and parts show potentiality on life and reliability.Micro-scale technology and micro-module and the extensive application of parts on Nano satellite, bring new opportunity to the design of every other spacecraft.Adopt micro-scale technology and micro-module and parts, spacecraft Platform Designing and emergency mechanism design is coordinated from Space Vehicle System top layer, emergency mechanism is planned in a spacecraft emergency response facility and realizes, meet spacecraft emergency response demand from system level comprehensively.
Summary of the invention
The technical matters that the present invention solves is: overcome the deficiencies in the prior art, provide a kind of Space Vehicle System level emergency response facility, adopts Systematic Design, reduces the degree of coupling of emergency mechanism and Platform Designing.
Technical scheme of the present invention is: a kind of Space Vehicle System level emergency response facility, by solar cell array, storage battery, power source management controller, emergency handling computer A, emergency handling computing machine B, digital sun sensor, MEMS gyro and TT&C antenna composition, power source management controller carries out management to the power supply that solar cell array or battery pack provide and controls, power source management controller is respectively emergency handling computer A, emergency handling computing machine B, digital sun sensor and MEMS gyro provide operating voltage, emergency handling computer A and emergency handling computing machine B form redundancy emergency response system, digital sun sensor and MEMS gyro form attitude measurement system and carry out attitude measurement to spacecraft in real time, emergency handling computer A and emergency handling computing machine B process the attitude data that attitude measurement system is measured in real time, store, emergency handling computer A and emergency handling computing machine B are monitored spacecraft state in real time by bus simultaneously, under emergency conditions, TT&C antenna receives ground control command, and ground control command is forwarded to redundancy emergency response system, the spacecraft attitude data of process and the spacecraft status information of supervision are sent to ground station by TT&C antenna according to ground control command by redundancy emergency response system on the one hand, by bus interface, ground control command is sent to each subsystem of spacecraft on the other hand, the response data of each subsystem of spacecraft to ground control command is sent to ground station by TT&C antenna.
The present invention compared with prior art beneficial effect is:
(1) the present invention adopts micro-scale technology and micro-module and parts, spacecraft Platform Designing and emergency mechanism design is coordinated from Space Vehicle System top layer, main emergency response function is realized in an emergency response facility, Platform Designing only considers conventional redundant means, thus reduces each subsystem of spacecraft because consider the degree of coupling that emergency design brings and complexity.
(2) spacecraft emergency response facility provided by the invention achieves independently-powered, spacecraft status surveillance and data recording function, with subsystems such as the spacecraft platform energy, observing and controlling, Star Service, rail controls without coupled relation, can communicate when emergency condition appears in above-mentioned subsystem in-orbit complete independently star, the function such as low precision attitude measurement, and spacecraft status surveillance data and spacecraft historical state data can be provided for ground trouble-shooting.
(3) the present invention adopts micro-scale technology and micro-module and component technology, and spacecraft emergency response facility volume, quality overhead little (being less than 10kg), functional independence is controlled.
Accompanying drawing explanation
Fig. 1 is theory of constitution block diagram of the present invention;
Fig. 2 is emergency response processing flow chart of the present invention.
Detailed description of the invention
Principle of design of the present invention is as follows: first according to the target of Spacecraft malfunction model partition spacecraft Redundancy Design and the target of spacecraft emergency design, secondly carries out platform according to the target of spacecraft Redundancy Design and the target of spacecraft emergency design, spacecraft emergency response facility function is distributed and Interface design.Spacecraft emergency response facility is the specific implementation of Space Vehicle System emergency plan, no longer considers that contingency mode designs at subsystem level.The interface of spacecraft emergency response facility and spacecraft generally only has mechanical interface, satellite-bone bus interface and interface altogether, and reduce degree of coupling therebetween as much as possible, simplify respective design, optimum completes spacecraft task and emergency handling task.
The present invention adopts micro-scale technology and micro-module and component technology, designed spacecraft emergency response facility as shown in Figure 1, by solar cell array, storage battery, power source management controller, emergency handling computer A, emergency handling computing machine B, digital sun sensor, MEMS gyro and TT&C antenna composition, power source management controller carries out management to the power supply that solar cell array or battery pack provide and controls, power source management controller is respectively emergency handling computer A, emergency handling computing machine B, digital sun sensor and MEMS gyro provide operating voltage, emergency handling computer A and emergency handling computing machine B form redundancy emergency response system, digital sun sensor and MEMS gyro form attitude measurement system and carry out attitude measurement to spacecraft in real time, emergency handling computer A and emergency handling computing machine B process the attitude data that attitude measurement system is measured in real time, store, emergency handling computer A and emergency handling computing machine B are monitored spacecraft state in real time by bus simultaneously, under emergency conditions, TT&C antenna receives ground control command, and ground control command is forwarded to redundancy emergency response system, the spacecraft attitude data of process and the spacecraft status information of supervision are sent to ground station by TT&C antenna according to ground control command by redundancy emergency response system on the one hand, by bus interface, ground control command is sent to each subsystem of spacecraft on the other hand, the response data of each subsystem of spacecraft to ground control command is sent to ground station by TT&C antenna.
Digital sun sensor and MEMS gyro form attitude measurement system and mainly realize carrying out low precision measure to the attitude of spacecraft in real time, TT&C antenna can realize spacecraft and communicate with carrying out emergent star with ground, under emergency conditions, surface instruction can be received control, by the attitude data of ground real time monitoring spacecraft, the spacecraft history attitude data of storage.Spacecraft emergency response facility is embedded in spacecraft, pastes solar cell array on spacecraft surface, installs TT&C antenna and minitype digital sun sensor.Adopt micro-scale technology and micro-module and component technology, quality is less than 10kg.Spacecraft emergency response facility and spacecraft internal bus have interface, can complete spacecraft status surveillance and data logging in real time.
Spacecraft emergency response facility can suitably expand its function according to emergency response demand, as data on-line analysis ability, possesses automatic fault diagnosis function, real time recording abnormal information; Expand the disposable function of gesture stability in short-term, guarantee spacecraft energy security under emergency conditions; Expand separation function in-orbit, can be separated with spacecraft in-orbit, carry micro-camera and spacecraft body is taken pictures.
Such as, emergency response facility of the present invention is utilized to carry out a kind of flow process of emergency handling as shown in Figure 2:
(1) redundancy emergency response system judges whether " the remote measurement radio-frequency transmissions is opened " instruction receiving ground transmission, if receive instruction, proceeds to step (2); Otherwise proceed to step (3);
(2) start earthward to send telemetry data, proceed to step (9);
(3) redundancy emergency response system judges whether " record data telemetry the is online " instruction receiving ground transmission, if receive instruction, proceeds to step (4); Otherwise proceed to step (5);
(4) send the attitude data that starts of fixed time and status information earthward, proceed to step (9);
(5) redundancy emergency response system judges whether the Bus repeater instruction receiving ground transmission, if receive instruction, proceeds to step (6); Otherwise proceed to step (7);
(6) this instruction is forwarded on spacecraft bus after receiving by spacecraft emergency response facility, proceeds to step (9);
(7) redundancy emergency response system judges whether " the remote measurement radio-frequency transmissions pass " instruction receiving ground transmission, if receive instruction, proceeds to step (8); Otherwise proceed to step (9);
(8) stop sending data earthward, proceed to step (9);
(9) this instruction process process is exited.
Although disclose most preferred embodiment of the present invention and accompanying drawing for the purpose of illustration, it will be appreciated by those skilled in the art that: without departing from the spirit and scope of the invention and the appended claims, various replacement, change and amendment are all possible.Therefore, the present invention should not be limited to the content disclosed in most preferred embodiment and accompanying drawing.
Claims (1)
1. a Space Vehicle System level emergency response facility, it is characterized in that: by solar cell array, storage battery, power source management controller, emergency handling computer A, emergency handling computing machine B, digital sun sensor, MEMS gyro and TT&C antenna composition, power source management controller carries out management to the power supply that solar cell array or battery pack provide and controls, power source management controller is respectively emergency handling computer A, emergency handling computing machine B, digital sun sensor and MEMS gyro provide operating voltage, emergency handling computer A and emergency handling computing machine B form redundancy emergency response system, digital sun sensor and MEMS gyro form attitude measurement system and carry out attitude measurement to spacecraft in real time, emergency handling computer A and emergency handling computing machine B process the attitude data that attitude measurement system is measured in real time, store, emergency handling computer A and emergency handling computing machine B are monitored spacecraft state in real time by bus simultaneously, under emergency conditions, TT&C antenna receives ground control command, and ground control command is forwarded to redundancy emergency response system, the spacecraft attitude data of process and the spacecraft status information of supervision are sent to ground station by TT&C antenna according to ground control command by redundancy emergency response system on the one hand, by bus interface, ground control command is sent to each subsystem of spacecraft on the other hand, the response data of each subsystem of spacecraft to ground control command is sent to ground station by TT&C antenna.
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| CN103699069A (en) * | 2013-12-06 | 2014-04-02 | 上海卫星工程研究所 | Advanced electronic integrated system for microsatellite |
| CN107885140B (en) * | 2017-09-29 | 2019-08-09 | 航天东方红卫星有限公司 | It is a kind of to be classified the autonomous emergency management method of whole star and system |
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