CN107832965A - A kind of fast sound track rescue mode and system - Google Patents

A kind of fast sound track rescue mode and system Download PDF

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CN107832965A
CN107832965A CN201711168628.2A CN201711168628A CN107832965A CN 107832965 A CN107832965 A CN 107832965A CN 201711168628 A CN201711168628 A CN 201711168628A CN 107832965 A CN107832965 A CN 107832965A
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rescue
satellite
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task
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晁鲁静
谢泽兵
张耀磊
郭剑
张佳
李君�
倪越
黄虎
杨思亮
庄学彬
郑本昌
乙冉冉
吴海华
任金磊
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China Academy of Launch Vehicle Technology CALT
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Abstract

A kind of fast sound track rescue mode and system, this method breaks traditions the task development mode of carrier rocket and satellite, the rescue system progress war preparedness that proposition is formed with fast-response carrier rocket, seriation orbit maneuver level, modularization rescue flight device and end-of-arm tooling case is on duty, shortens the development time of rescue system；Satellite in orbit fault mode is analysed in depth by existing case and track rescues demand, instructs rescue method to design, improves covering power of the rescue system to fault type, shortens rescue ability analysis and scheme determines the time；Valuation, comprehensive analysis rescue task cost performance, the overall process for instructing rescue task to implement are carried out to breakdown loss and rescue cost by more key element appraisal procedures.The rescue task that this method is introduced into planned orbit and on-orbit fault for satellite proposes system scheme, is built from rescue task analysis, rescue system and rescue task implements too many levels and improves fast-response ability.

Description

A kind of fast sound track rescue mode and system
Technical field
The invention belongs to aerospace craft fault rescue field, more particularly to satellite launch is introduced into correct path and in-orbit The quick response rescue mode of failure.
Background technology
Space flight is excessive risk industry, simple to reduce space transoportation and in-orbit by component and unit reliability is improved Aircraft risk will greatly improve cost, and track rescue is to fail to enter the event such as correct path and in-orbit failure for satellite Barrier, carry out in-orbit rescue by engineering technology means, satellite is entered correct path or recover the technology of function.
The eighties in last century, the U.S. have carried out someone's participation to the satellite failure occurred in orbit using space shuttle Recovery and maintainable technology on-orbit, but due to the limitation of space shuttle flight track, it is limited to rescue the track-bound of satellite, and singly The efficiency-cost ratio that a frame space shuttle is launched in the pure rescue for a satellite is not high, with retired, someone's track of space shuttle Rescue technique has also exited stage.
The track towboat technology studied both at home and abroad in recent years, research emphasis are concentrated mainly on rescue flight device and defended by rescue The capture connection scheme of star, propose rescue flight device for satellite structure feature and quality scale and capture the design of bindiny mechanism Scheme and rescue mode；In-orbit service technology then lays particular emphasis on the in-orbit operation such as module replacing, fuel make up.Above two technical sides To research majority be to be studied for the single technology of a certain concrete application, be seldom related to the scheme of rescue system and meet fast ring Answer the rescue task flow of demand.But with the maturation of single technology, rescue system how appoint by a variety of track rescues of quick response The demand of business is more and more urgent.
The content of the invention
The technology of the present invention solves problem：A kind of overcome the deficiencies in the prior art, there is provided quick response track rescue party Method and system, solve the problems, such as that prior art studies systematicness, engineering deficiency to track rescue task.
The technical scheme is that：
A kind of fast sound track rescue mode, including step are as follows：
1) rescue system is on duty in launching site war preparedness；
2) when the satellite failure launched, inoperative component and unit are positioned, propose rescue demand；
3) the penalty values M of satellite failure is assessed according to loss factor；
4) the rescue demand proposed according to step 2), determines rescue method；
5) rescue method proposed according to step 4), consider that rescue cost factor assesses rescue cost value N；
6) compare M and N, if M is more than or equal to N, carry out the 7) step；If M is less than N, rescue is terminated；
7) ground simulation is carried out to the rescue method that step 4) proposes, determines launching site, launch window, tracking telemetry and command station, carried out Rescue system assembling, test, launching site, TT＆C Resources are coordinated, and are finally completed transmitting and in-orbit rescue.
The loss factor includes：Direct economic loss, again launching costs, indirect economic loss, externality weight.
The rescue cost factor includes：Direct cost, the satellite service output value and externality.
It is described assess satellite failure penalty values M specific method be：
M=(m1+m2+m3)×(1+K)
Wherein, m1For direct economic loss, m2For launching costs again, m3For indirect economic loss, K is externality weight.
It is described assess rescue cost value N specific method be：
N=(n1+n2)×(1-J)
Wherein, n1For direct cost, n2For T2The satellite service output value in time, J are externality weight, T2For from this Abortive launch is to the time completed needed for in-orbit rescue.
The m1、m2、m3It is with K specific formula for calculation：
The m1=(satellite development cost+launching costs+insurance premium) × s- compensation pay-outs；Wherein, satellite is not When service can be provided, s=1；0 when satellite provides partial service or the lost of life<s<1；
The m2=newly grind satellite development cost/backup satellite cost+launching costs+insurance premium；
The m3The satellite service output value in the=insurance premium rate increased value+T1 times caused by satellite cost × abortive launch, Wherein T1 is from this abortive launch to the time re-emitted needed for a satellite；
The rail safety factor of influence k that the K=space junks are brought1+ space technology checking lagging influence factor k2+ production Industry factor of influence k3+ social influence factor k4, wherein 0≤ki≤ 1, i=1,2,3,4.
The n1、n2It is with J specific formula for calculation：
The n1=rescue system development cost+launching costs；
The J=rail safeties factor of influence j1+ space technology advancements affect factor j2+ Industrial Effects factor j3+ social shadow Ring factor j4, wherein 0≤ji≤ 1, i=1,2,3,4.
The determination rescue method specifically includes：The type selecting of carrier rocket, orbit maneuver level, determine rescue flight device function Module and end-of-arm tooling case composition.
A kind of fast sound track rescue system, including rescue subsystem, accident analysis subsystem, assessment of failure subsystem；
Accident analysis subsystem positions inoperative component and unit, determines rescue method；
Assessment of failure subsystem assesses the penalty values M and rescue cost value N of satellite failure, determines whether that carrying out rescue appoints Business；
After rescue subsystem is connected to rescue task, ground simulation rescue method is carried out, determines launching site, launch window, survey Control station, carry out rescue system assembling, test, coordinates transmission field, TT＆C Resources, complete transmitting and in-orbit rescue.
It is described assess satellite failure penalty values M circular be:
M=(m1+m2+m3)×(1+K)
m1=(satellite development cost+launching costs+insurance premium) × s- compensation pay-outs
m2=newly grind satellite development cost/backup satellite cost+launching costs+insurance premium
m3The satellite service output value in the=insurance premium rate increased value+T1 times caused by satellite cost × abortive launch
The rail safety factor of influence k that K=space junks are brought1+ space technology checking lagging influence factor k2+ industry shadow Ring factor k3+ social influence factor k4
Wherein, T1 is from this abortive launch to the time re-emitted needed for a satellite；When satellite can not provide clothes During business, s=1；When satellite provides partial service or the lost of life 0<s<1；0≤ki≤ 1, i=1,2,3,4.
It is described assess rescue cost value N circular be：
N=(n1+n2)×(1-J)
n1=rescue system development cost+launching costs
J=rail safety factors of influence j1+ space technology advancements affect factor j2+ Industrial Effects factor j3+ social influence because Sub- j4
Wherein 0≤ji≤ 1, i=1,2,3,4；n2For T2The satellite service output value in time.
The specific method that determines whether to be rescued is：
Compare M and N, if M is more than or equal to N, carry out rescue task；If M is less than N, rescue task is terminated.
Compared with the prior art, the invention has the advantages that：
1) propose that modular rescue flight device combines the rescue method of ripe carrier rocket, solve to transport in legacy transmission task The problem of load rocket and spacecraft need to customize respectively according to specific tasks, it can effectively shorten the development week of rescue system Phase；
2) track for proposing to assess based on more key elements rescues full flow of task, solves prior art to track rescue task system The problem of Journal of Sex Research deficiency of uniting, guidance is provided for satellite failure rescue, improves the normalization of task operating, when shortening rescue response Between.
Brief description of the drawings
Fig. 1 is the inventive method flow chart；
Fig. 2 is track rescue system composition figure；
Fig. 3 is satellite failure pattern and rescue demand analysis figure.
Embodiment
The embodiment of the present invention is further described in detail below in conjunction with the accompanying drawings.
The invention discloses a kind of quick response track rescue mode and system, and skill is rescued to track to solve prior art The problem of art research systematicness, engineering deficiency.Under the existing development mode of China's aerospace engineering, towards particular task, defend The lead time of star and carrier rocket is all longer, can not meet requirement of the track rescue task to rapidity.The present invention is from technology Angle and engineering viewpoint system research rescue method, are proposed using modularization rescue flight device as goods shelf productses, are delivered with maturation Rocket flexible combination forms track rescue system, and cost-efficiency analysis is carried out to rescue task using more key element appraisal procedures, there is provided Rescue task whole process specification instructs, and effectively lifts the capability of fast response of track rescue system.
As shown in figure 1, specific implementation step of the present invention is as follows：
1) rescue system war preparedness is on duty
Carrier rocket, orbit maneuver level, rescue flight device and end-of-arm tooling case composition track rescue system, rescue system are put down When it is on duty in launching site war preparedness；
As shown in Fig. 2 rescue system is on duty in launching site war preparedness, the track rescue system includes fast-response delivery fire Arrow, orbit maneuver level, rescue flight device and end-of-arm tooling case.Taskization is gone to transform by active service carrier rocket, uniform configuration, shape Into generalization, modularization, seriation carrier rocket scheme, expand carrying capacity coverage, meet different task demand.Rail The power plant module of different scales may be selected according to different by rescue satellite quality scale and track in road maneuver stage, electrical system with Rescue flight device integrated design；Rescue flight device uses modularized design thinking, is divided into aircraft platforms, expansible power mould The disparate modules such as block, detecting module, capture link block, each functional module is matched according to specific rescue task and put down with aircraft Platform is combined；End-of-arm tooling case includes multiple types of tools needed for in-orbit operation, and a variety of maintenances, maintenance can be completed by coordinating with mechanical arm Task.The carrier rocket and orbit maneuver level of uniform configuration, and the rescue flight device and end-of-arm tooling case of modularized design, shape Into rescue method storehouse, it can support that track rescue system is periodically on duty at launching site, according to quick group different of rescue task demands Conjunction is built, and improves the fast-response ability of system.
2) satellite failure is analyzed
When the satellite failure launched, satellite failure mechanism is analyzed, inoperative component and unit are positioned, carried Go out rescue demand；
Determination of the satellite failure pattern to schemes such as rescue system acquisition mode, end-of-arm tooling case and orbit maneuver abilities rises Conclusive effect.It is illustrated in figure 3 satellite failure type to analyze with rescue mode, satellite failure pattern is divided into platform class Failure and load class failure, wherein platform class failure include dynamical system failure, the electricity such as rail control engine and orbit maneuver motor Gas failure and the class of mechanical breakdown three.Different faults pattern includes function auxiliary, Orbit Transformation, in-orbit mould to the demand of rescue system Block replacing and maintainable technology on-orbit etc., the difference according to fault mode to rescue demand, further determine that the work(that rescue flight device carries Can load and in-orbit operation task.By the analysis to satellite failure pattern, comprehensive existing case is to satellite in orbit fault type Analysed in depth, fault mode is classified, rescue system can be instructed to design in the rescue method design phase, expansion is rescued Help ability envelope；In the rescue task analysis phase, it is possible to achieve the quick analysis of rescue task and reply.
It is special to the constraint of different task rescue time, rescue cost constraint, rescue target on the basis of satellite failure is analyzed Property (characteristic containing current orbit, target shape and size, target faults reason and state), task object etc. are analyzed and really Recognize, rational rescue mode is determined according to a variety of constraintss.
3) breakdown loss value is assessed
Satellite failure loss is assessed from more key elements such as economic loss, Industrial Effects, social influence, determines the damage of satellite failure Mistake value M；
Satellite industry chain includes satellite manufacture, transmitting, ground installation, insurance, service etc., satellite can normally deliver and Rail is run except bringing direct economic loss, many-sided to vertical industry chain and society, politics and military affairs etc. can also be produced Considerable influence, comprehensive assessment is carried out to the more key elements of economic loss, Industrial Effects, social influence etc. caused by satellite failure, calculated Draw the penalty values M of satellite failure；Specific estimation method is as follows：
M=(m1+m2+m3)×(1+K)
Wherein, m1For direct economic loss, m2For launching costs again, m3For indirect economic loss, K is externality weight；
The m1、m2、m3It is with K specific formula for calculation：
The m1=(satellite development cost+launching costs+insurance premium) × s- compensation pay-outs；Wherein, satellite is not When service can be provided, s=1；0 when satellite provides partial service or the lost of life<s<1；
The m2=newly grind satellite development cost/backup satellite cost+launching costs+insurance premium；
The m3The satellite service output value in the=insurance premium rate increased value+T1 times caused by satellite cost × abortive launch；
The rail safety factor of influence k that the K=space junks are brought1+ space technology checking lagging influence factor k2+ production Industry factor of influence k3+ social influence factor k4, wherein 0≤ki≤ 1, i=1,2,3,4.
4) rescue method is proposed
The rescue demand proposed according to step 2), determines rescue method, analyzes different rescue modes to Orbit Transformation, in-orbit The ability needs such as operation, carrier rocket, the type selecting of orbit maneuver level are completed, determines rescue flight device functional module and end-of-arm tooling Case forms；
According to by the quality scale of rescue satellite, orbital position and transfer demand, specify rescue task carrying capacity need Ask, determine the type selecting of carrier rocket and orbit maneuver level；According to by the target property, architectural feature, maintenance requirements of rescue satellite Deng confirmation rescue flight device target detection and identification ability, docking capacity is arrested, and end-of-arm tooling case carries the type of instrument, It is final to propose track rescue method.
5) rescue cost value is assessed
The rescue method proposed for step 4), wanted from financial cost, time cost, Industrial Effects, social influence etc. Element carries out comprehensive assessment, it is determined that rescue cost value N；
Cost is rescued in addition to the direct economy cost of rescue method, further relates to task response-time cost, to technological progress Impetus, subsidiary social influence, specific tasks, which are also contemplated that the political and military that satellite attribute brings, to be influenceed etc., to each Influent factor is assessed, and rescue cost value N is calculated；
Specific estimation method is as follows：
N=(n1+n2)×(1-J)
Wherein, n1For direct cost, n2For T2The satellite service output value in time, J are externality weight, T2For from this Abortive launch is to the time completed needed for in-orbit rescue；
The n1、n2It is with J specific formula for calculation：
The n1=rescue system development cost+launching costs；
The J=rail safeties factor of influence j1+ space technology advancements affect factor j2+ Industrial Effects factor j3+ social shadow Ring factor j4, wherein 0≤ji≤ 1, i=1,2,3,4.
6) cost performance is assessed
Compare M and N, if M is more than or equal to N, carry out the 7) step；If M is less than N, rescue is terminated.
7) rescue method is implemented
Ground simulation is carried out to the rescue method that step 4) proposes, determines launching site, launch window, tracking telemetry and command station；
The rescue method proposed according to step 4), rescue task is entered from whole processes such as transmitting, Orbit Transformation, in-orbit operations Row Six-degree-of-freedom Simulation, comprehensive analysis carrying capacity, TT＆C Resources, launching site task situation etc., determine location of launching site, transmitting The tracking telemetry and command station of window and required by task.
8) rescue task is implemented
Carry out rescue system assembling, test, launching site, TT＆C Resources are coordinated, and are finally completed transmitting and in-orbit rescue；
After rescue task is clear and definite, carry out carrier rocket, orbit maneuver level, the test of rescue flight device and part frock respectively Processing and production, synchronously carry out launching site and TT＆C Resources are coordinated, and carry out rescue system general assembly, total survey, ground after the completion of test Observing and controlling carries out, by the tracking of rescue satellite orbit, forecast, after being ready to complete before penetrating, performing launch mission.Carrier rocket is by track machine Dynamic level is sent into parking orbit with rescue flight device, and rescue flight device is sent into target Orbit of Rendezvous, rescue flight by orbit maneuver level After device long-range detection capture target, realize that the capture to target satellite connects by autonomous vehicle out-driving, according to specific tasks Demand carries out the tasks such as Orbit Transformation, rail control adapter or malfunctioning module replacing, completes rescue work.
9) rescue effect is assessed
Satellite functional rehabilitation situation, rescue cost are confirmed again, comprehensive assessment rescue task；
The direct economy cost of track rescue system is confirmed according to specific rescue task implementation status, according to ground observing and controlling number According to and satellite telemetering data confirm rescue task implementation result.It is node tracking satellite working condition, rescues with season, year respectively Economic benefit, social benefit and political and military influence that the task of helping is brought etc., comprehensive assessment rescue task implements effect stage by stage Fruit.
The known technology for the content category professional and technical personnel in the field not being described in detail in description of the invention.

Claims (10)

1. a kind of fast sound track rescue mode, it is characterised in that as follows including step：
1) rescue system is on duty in launching site war preparedness；
2) when the satellite failure launched, inoperative component and unit are positioned, propose rescue demand；
3) the penalty values M of satellite failure is assessed according to loss factor；
4) the rescue demand proposed according to step 2), determines rescue method；
5) rescue method proposed according to step 4), consider that rescue cost factor assesses rescue cost value N；
6) compare M and N, if M is more than or equal to N, carry out the 7) step；If M is less than N, rescue is terminated；
7) ground simulation is carried out to the rescue method that step 4) proposes, determines launching site, launch window, tracking telemetry and command station, carry out rescue System assembles, test, launching site, TT＆C Resources are coordinated, and are finally completed transmitting and in-orbit rescue.
2. a kind of fast sound track rescue mode according to claim 1, it is characterised in that the loss factor includes：Directly Connect economic loss, again launching costs, indirect economic loss, externality weight.
A kind of 3. fast sound track rescue mode according to claim 1, it is characterised in that the rescue cost factor bag Include：Direct cost, the satellite service output value and externality.
A kind of 4. fast sound track rescue mode according to claim 2, it is characterised in that the damage for assessing satellite failure Mistake value M specific method is：
M=(m1+m2+m3)×(1+K)
Wherein, m1For direct economic loss, m2For launching costs again, m3For indirect economic loss, K is externality weight.
5. a kind of fast sound track rescue mode according to claim 3, it is characterised in that described to assess rescue cost value N Specific method be：
N=(n1+n2)×(1-J)
Wherein, n1For direct cost, n2For T2The satellite service output value in time, J are externality weight, T2To be lost from this transmitting Lose to the time completed needed for in-orbit rescue.
A kind of 6. fast sound track rescue mode according to claim 4, it is characterised in that the m1、m2、m3Specifically counted with K Calculating formula is：
The m1=(satellite development cost+launching costs+insurance premium) × s- compensation pay-outs；Wherein, satellite can not provide During service, s=1；0 when satellite provides partial service or the lost of life<s<1；
The m2=newly grind satellite development cost/backup satellite cost+launching costs+insurance premium；
The m3The satellite service output value, wherein T1 in the=insurance premium rate increased value+T1 times caused by satellite cost × abortive launch For from this abortive launch to the time re-emitted needed for a satellite；
The rail safety factor of influence k that the K=space junks are brought1+ space technology checking lagging influence factor k2+ industry shadow Ring factor k3+ social influence factor k4, wherein 0≤ki≤ 1, i=1,2,3,4.
A kind of 7. fast sound track rescue mode according to claim 5, it is characterised in that the n1、n2Specifically calculated with J Formula is：
The n1=rescue system development cost+launching costs；
The J=rail safeties factor of influence j1+ space technology advancements affect factor j2+ Industrial Effects factor j3+ social influence because Sub- j4, wherein 0≤ji≤ 1, i=1,2,3,4.
8. according to a kind of any described fast sound track rescue modes of claim 1-7, it is characterised in that the determination rescue party Case specifically includes：The type selecting of carrier rocket, orbit maneuver level, determine rescue flight device functional module and end-of-arm tooling case composition.
A kind of 9. fast sound track rescue system, it is characterised in that：Including rescue subsystem, accident analysis subsystem, assessment of failure Subsystem；
Accident analysis subsystem positions inoperative component and unit, determines rescue method；
Assessment of failure subsystem assesses the penalty values M and rescue cost value N of satellite failure, determines whether to carry out rescue task；
After rescue subsystem is connected to rescue task, ground simulation rescue method is carried out, determines launching site, launch window, tracking telemetry and command station, Carry out rescue system assembling, test, coordinates transmission field, TT＆C Resources, complete transmitting and in-orbit rescue.
A kind of 10. fast sound track rescue system according to claim 9, it is characterised in that：
It is described assess satellite failure penalty values M circular be:
M=(m1+m2+m3)×(1+K)
m1=(satellite development cost+launching costs+insurance premium) × s- compensation pay-outs
m2=newly grind satellite development cost/backup satellite cost+launching costs+insurance premium
m3The satellite service output value in the=insurance premium rate increased value+T1 times caused by satellite cost × abortive launch
The rail safety factor of influence k that K=space junks are brought1+ space technology checking lagging influence factor k2+ Industrial Effects because Sub- k3+ social influence factor k4
Wherein, T1 is from this abortive launch to the time re-emitted needed for a satellite；When satellite can not provide service, S=1；When satellite provides partial service or the lost of life 0<s<1；0≤ki≤ 1, i=1,2,3,4；
It is described assess rescue cost value N circular be：
N=(n1+n2)×(1-J)
n1=rescue system development cost+launching costs
J=rail safety factors of influence j1+ space technology advancements affect factor j2+ Industrial Effects factor j3+ social influence factor j4
Wherein 0≤ji≤ 1, i=1,2,3,4；n2For T2The satellite service output value in time；
The specific method that determines whether to be rescued is：
Compare M and N, if M is more than or equal to N, carry out rescue task；If M is less than N, rescue task is terminated.
CN201711168628.2A 2017-11-21 2017-11-21 A kind of fast sound track rescue mode and system Pending CN107832965A (en)

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