CN103192998A - System-level emergency response device of spacecraft - Google Patents
System-level emergency response device of spacecraft Download PDFInfo
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- CN103192998A CN103192998A CN2013100359486A CN201310035948A CN103192998A CN 103192998 A CN103192998 A CN 103192998A CN 2013100359486 A CN2013100359486 A CN 2013100359486A CN 201310035948 A CN201310035948 A CN 201310035948A CN 103192998 A CN103192998 A CN 103192998A
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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, relate in particular to a kind of Space Vehicle System level emergency response facility, belong to the space technology field.
Background technology
Space mission has all designed the success that various redundant means guarantee task owing to originally can not safeguard at the base of the rail both at home and abroad at present, nonetheless at the rail spacecraft various faults often takes place also, causes the spacecraft mission failure.The design of spacecraft emergency mechanism is the key issue that the Space Vehicle System engineering must be considered, is included in the counter-measures of crucial subsystem after rail breaks down such as the spacecraft energy, observing and controlling, Star Service, rail control.Except adopting conventional redundancy backup means, spacecraft generally also can be taked more complicated isomery degradation backup mode reply emergency condition, present emergency response facility is distributed in each subsystem of spacecraft, emergent design and conventional platform design degree of coupling are bigger, increased the spacecraft complexity, when major failure appears in energy subsystem etc., often can not satisfy spacecraft emergency response demand.For example rail control subsystem, Star Service subsystem have all designed the emergency controller of degraded mode separately; Possess between the different spaceborne computers of bus interface and designed the software recombination function.In recent years, some spacecrafts are after rail generation problem, expose the defective that exists on the spacecraft emergency response Mechanism Design, do not fully take into account some extreme cases, can not satisfy spacecraft emergency response demand, as lack telemetry data before and after the fault and finish positioning problems accurately, lack spacecraft after the major failure means etc. that leave the right or normal track.
Launched the satellite of receiving more than 70 both at home and abroad to the end of the year 2011, the micro-scale technology that the satellite of receiving carries and micro-module and parts show potentiality in life-span and reliability.Micro-scale technology and micro-module and parts have brought new opportunity for the design of every other spacecraft in the extensive application of receiving on the satellite.Adopt micro-scale technology and micro-module and parts, coordinate the design of spacecraft platform and emergency mechanism design from the Space Vehicle System top layer, emergency mechanism is planned in the spacecraft emergency response facility realizes, satisfy 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, a kind of Space Vehicle System level emergency response facility is provided, adopt the systematization design, reduced the degree of coupling of emergency mechanism and platform design.
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, the emergency handling computer A, emergency handling computing machine B, digital sun sensor, MEMS gyro and observing and controlling antenna are formed, power source management controller manages control to the power supply that solar cell array or battery pack provide, power source management controller is respectively the 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 redundant emergency response system, digital sun sensor and MEMS gyro constitute attitude measurement system and in real time spacecraft are carried out attitude measurement, the attitude data that emergency handling computer A and the attitude measurement system of emergency handling computing machine B are measured is in real time handled, storage, emergency handling computer A and emergency handling computing machine B monitor the spacecraft state in real time by bus simultaneously, under emergency condition, the observing and controlling antenna receives the ground control command, and the ground control command is forwarded to redundant emergency response system, redundant emergency response system sends to ground station with the spacecraft attitude data of processing and the spacecraft status information of supervision by the observing and controlling antenna according to the ground control command on the one hand, by bus interface the ground control command is sent to each subsystem of spacecraft on the other hand, each subsystem of spacecraft is sent to ground station to the response data of ground control command by the observing and controlling antenna.
The present invention compared with prior art beneficial effect is:
(1) the present invention adopts micro-scale technology and micro-module and parts, coordinate the design of spacecraft platform and emergency mechanism design from the Space Vehicle System top layer, main emergency response function is realized in an emergency response facility, conventional redundant means is only considered in the platform design, thereby has reduced each subsystem of spacecraft because consider degree of coupling and the complexity that emergent design brings.
(2) spacecraft emergency response facility provided by the invention has been realized independently-powered, spacecraft status surveillance and data recording function, there is not coupled relation with subsystems such as the spacecraft platform energy, observing and controlling, Star Service, rail controls, when emergency condition appears in rail, can independently finish functions such as the communication of star ground, low precision attitude measurement in above-mentioned subsystem, and can provide spacecraft status surveillance data and spacecraft historical state data to use for the ground trouble-shooting.
(3) the present invention adopts micro-scale technology and micro-module and component technology, spacecraft emergency response facility volume, quality overhead little (less than 10kg), and function is independent controlled.
Description of drawings
Fig. 1 is theory of constitution block diagram of the present invention;
Fig. 2 is emergency response processing flow chart of the present invention.
The specific embodiment
Principle of design of the present invention is as follows: at first divide the target of spacecraft Redundancy Design and the target that spacecraft is met an urgent need and designed according to the spacecraft fault model, secondly carry out platform, the distribution of spacecraft emergency response facility function and Interface design according to the target of spacecraft Redundancy Design and the target of the emergent design of spacecraft.The spacecraft emergency response facility is the specific implementation of Space Vehicle System emergency plan, no longer considers the contingency mode design at the subsystem level.The interface of spacecraft emergency response facility and spacecraft generally only has mechanical interface, spaceborne bus interface and interface altogether, reduces degree of coupling between the two as much as possible, simplifies design separately, and optimum is finished 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, the emergency handling computer A, emergency handling computing machine B, digital sun sensor, MEMS gyro and observing and controlling antenna are formed, power source management controller manages control to the power supply that solar cell array or battery pack provide, power source management controller is respectively the 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 redundant emergency response system, digital sun sensor and MEMS gyro constitute attitude measurement system and in real time spacecraft are carried out attitude measurement, the attitude data that emergency handling computer A and the attitude measurement system of emergency handling computing machine B are measured is in real time handled, storage, emergency handling computer A and emergency handling computing machine B monitor the spacecraft state in real time by bus simultaneously, under emergency condition, the observing and controlling antenna receives the ground control command, and the ground control command is forwarded to redundant emergency response system, redundant emergency response system sends to ground station with the spacecraft attitude data of processing and the spacecraft status information of supervision by the observing and controlling antenna according to the ground control command on the one hand, by bus interface the ground control command is sent to each subsystem of spacecraft on the other hand, each subsystem of spacecraft is sent to ground station to the response data of ground control command by the observing and controlling antenna.
Digital sun sensor and MEMS gyro constitute attitude measurement system mainly to be realized in real time the attitude of spacecraft being hanged down precision measure, the observing and controlling antenna can realize that spacecraft and ground communicates by letter with meeting an urgent need star, under emergency condition, can receive surface instruction control, by the attitude data of ground real time monitoring spacecraft, the historical attitude data of spacecraft of storage.The spacecraft emergency response facility is embedded in the spacecraft, pastes solar cell array on the spacecraft surface, observing and controlling antenna and minitype digital sun sensor are installed.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 finish spacecraft status surveillance and data logging in real time.
The spacecraft emergency response facility can suitably be expanded its function according to the emergency response demand, as data on-line analysis ability, possesses the automatic fault diagnosis function, the real time recording abnormal information; Expand the disposable control of attitude in short-term function, under emergency condition, guarantee the spacecraft energy security; Expansion can separate with spacecraft at rail at the rail separation function, carries micro-camera the spacecraft body is taken pictures.
For example, utilize flow process that emergency response facility of the present invention carries out a kind of emergency handling as shown in Figure 2:
(1) redundant emergency response system judges whether to receive " the remote measurement radio-frequency transmissions is opened " instruction of ground transmission, if receive instruction, changes step (2) over to; Otherwise change step (3) over to;
(2) begin to send telemetry data earthward, change step (9) over to;
(3) redundant emergency response system judges whether to receive " the record data remote measurement is online " instruction of ground transmission, if receive instruction, changes step (4) over to; Otherwise change step (5) over to;
(4) send attitude data and the status information that the fixed time begins earthward, change step (9) over to;
(5) redundant emergency response system judges whether to receive the bus forwarding instruction of ground transmission, if receive instruction, changes step (6) over to; Otherwise change step (7) over to;
(6) the spacecraft emergency response facility is forwarded to this instruction on the spacecraft bus after receiving, and changes step (9) over to;
(7) redundant emergency response system judges whether to receive " remote measurement radio-frequency transmissions pass " instruction of ground transmission, if receive instruction, changes step (8) over to; Otherwise change step (9) over to;
(8) stop to send earthward data, change step (9) over to;
(9) withdraw from this instruction process process.
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 replacements, variation and modification all are possible.Therefore, the present invention should not be limited to most preferred embodiment and the disclosed content of accompanying drawing.
Claims (1)
1. Space Vehicle System level emergency response facility, it is characterized in that: by solar cell array, storage battery, power source management controller, the emergency handling computer A, emergency handling computing machine B, digital sun sensor, MEMS gyro and observing and controlling antenna are formed, power source management controller manages control to the power supply that solar cell array or battery pack provide, power source management controller is respectively the 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 redundant emergency response system, digital sun sensor and MEMS gyro constitute attitude measurement system and in real time spacecraft are carried out attitude measurement, the attitude data that emergency handling computer A and the attitude measurement system of emergency handling computing machine B are measured is in real time handled, storage, emergency handling computer A and emergency handling computing machine B monitor the spacecraft state in real time by bus simultaneously, under emergency condition, the observing and controlling antenna receives the ground control command, and the ground control command is forwarded to redundant emergency response system, redundant emergency response system sends to ground station with the spacecraft attitude data of processing and the spacecraft status information of supervision by the observing and controlling antenna according to the ground control command on the one hand, by bus interface the ground control command is sent to each subsystem of spacecraft on the other hand, each subsystem of spacecraft is sent to ground station to the response data of ground control command by the observing and controlling antenna.
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| CN201310035948.6A CN103192998B (en) | 2013-01-30 | 2013-01-30 | System-level emergency response device of spacecraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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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 |
| CN107885140A (en) * | 2017-09-29 | 2018-04-06 | 航天东方红卫星有限公司 | One kind is classified the autonomous emergency management method of whole star and system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN107885140A (en) * | 2017-09-29 | 2018-04-06 | 航天东方红卫星有限公司 | One kind is classified the autonomous emergency management method of whole star and system |
| 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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| CN103192998B (en) | 2015-07-08 |
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