CN109583747A - Spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design method - Google Patents
Spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design method Download PDFInfo
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Abstract
The present invention relates to a kind of spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design methods, comprising: S1, analyzes spacecrafts rendezvous main task；S2, the aerial mission of overall process is divided according to time phase, the influence to each stage fly event implementing result to task object is analyzed, and identification principle is formulated, and will be necessary event to the completion of subsequent docking mission target and is defined as critical event；S3, the critical event that will identify that are analyzed as top event using Fault Tree Analysis, are analyzed all necessary conditions for leading to the top event failure；S4, it identifies according to the analysis result of the S3 and is related to the various faults mode of multiple target cooperative disposal；S5, for the various faults mode of the multiple target cooperative disposal identified, be disposed authorization according to the participant that fault mode disposition is related to.Method of the invention can be improved the comprehensive and correctness of fault countermeasure design.
Description
Technical field
The present invention relates to spacecrafts rendezvous task failure prediction scheme design field more particularly to a kind of spacecrafts rendezvous task are more
Target faults prediction scheme cooperative disposal design method.
Background technique
Fault countermeasure design is the important component of spacecraft flight control task, certain event occurs in practical flight control
After barrier, there is the case where needing the big system of two or more or subsystem to simultaneously participate in troubleshooting.China's spacecrafts rendezvous is appointed
Business is exactly the Typical Representative that multiple target spacecraft is performed in unison with task, includes manned spaceship/cargo ship, spacelab etc.
Spacecraft, and other big systems ginsengs such as have spacefarer, carrier rocket, telemetry communication, space technology test, launching site, reclaims factory
With, and each big internal system is divided into several to dozens of subsystem again, and entire engineering duty is complexity.
The design of spacecrafts rendezvous fault countermeasure, needs to consider between multiple subsystems, between multiple big systems, especially actively
Track the conspiracy relation between aircraft (manned spaceship or cargo ship) and target aircraft, including information, timing, space flight
Equipment, ground installation and personnel etc. on device, device, entire design process is as cumbersome, is flying the control preparation stage generally with regard to needing
3-4 wheel iterates, and expends a large amount of personnel, time resource.It is general in physical fault disposition that there is time, observing and controlling etc. simultaneously again
Condition of Strong Constraint further increases the difficulty of fault countermeasure design, is easy to appear leakage item, timing error, big system part interface
The problems such as mismatch, causes fault countermeasure that cannot use in crucial moment, is not handy, has to spacefarer's safety and main task success or failure
Significant impact.As China enters the space station epoch, space station becomes in terms of whole device configuration, offline mode, data
Must be increasingly complex, this will provide higher design requirement to space station spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal.
Summary of the invention
The purpose of the present invention is to provide a kind of spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design methods, really
Protect comprehensive, the correctness of fault countermeasure design.
To achieve the above object, the present invention provides a kind of spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design side
Method, comprising:
S1, spacecrafts rendezvous main task is analyzed；
S2, the aerial mission of overall process is divided according to time phase, to each stage fly event implementing result
Influence to task object is analyzed, and identification principle is formulated, and will be necessary event to the completion of subsequent docking mission target and be determined
Justice is critical event；
S3, the critical event that will identify that are analyzed as top event using Fault Tree Analysis, to causing
All necessary conditions for stating top event failure are analyzed；
S4, it identifies according to the analysis result of the S3 and is related to the various faults mode of multiple target cooperative disposal；
S5, for the various faults mode of the multiple target cooperative disposal identified, be related to according to fault mode disposition
To participant be disposed authorization.
According to an aspect of the present invention, in the step S1, the spacecrafts rendezvous main task includes that spacecrafts rendezvous is appointed
Spacefarer's safety is added and ensured to business, completion propellant.
According to an aspect of the present invention, in the step S2, the critical event includes influencing security incident, possibility
Lead to task termination event and flight plan is caused to change event.
According to an aspect of the present invention, the influence security incident include influence the security incident of spacecrafts rendezvous participant with
And influence spacefarer's security incident.
According to an aspect of the present invention, in the step S3, to the institute for causing the top event to fail, it is necessary to items
It includes information exchange analysis, equipment task analysis, spatial temporal analysis, people-ship-device-ground cooperating analysis that part, which carries out analysis,.
According to an aspect of the present invention, in the step S5, according to the fault mode participant that is related to of disposition into
When row disposition authorization, specific personnel, password and treatment procedures are navigated to.
According to an aspect of the present invention, it in the step S5, according to safety, observing and controlling and time constraint condition, presses
Fault countermeasure detailed design is completed according to the disposition right handover definition of timing, fault branch and participant failure.
According to an aspect of the present invention, the fault countermeasure detailed design includes the judgement or initiation responsibility of clear failure
The cooperation subsystem or big system, design of subsystem, the responsibility subsystem of clear failure disposition or big system, clear failure disposition
The interface pass of participant in all fault branches being likely to occur and corresponding Disposal Measures, the faulty Disposal Measures of design institute
It is, designs the disposition ending-criterion or mark of all fault branches, is finally completed the cooperative disposal of certain fault countermeasure.
Spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design method of the invention, solved in time, observing and controlling
Under equal Condition of Strong Constraint, multi-aircraft, multisystem participate in the problem of the complex fault prediction scheme design of disposition, can system, comprehensively,
It is efficiently completed the design of spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal, meets the need of spacecrafts rendezvous flight control task with higher
It asks.
Detailed description of the invention
Fig. 1 schematically shows spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design method according to the present invention
Flow chart；
Fig. 2 is to schematically show critical event identification principle diagram according to the present invention.
Specific embodiment
It, below will be to embodiment in order to illustrate more clearly of embodiment of the present invention or technical solution in the prior art
Needed in attached drawing be briefly described.It should be evident that the accompanying drawings in the following description is only of the invention some
Embodiment for those of ordinary skills without creative efforts, can also be according to these
Attached drawing obtains other attached drawings.
When being described for embodiments of the present invention, term " longitudinal direction ", " transverse direction ", "upper", "lower", " preceding ",
" rear ", "left", "right", "vertical", "horizontal", "top", "bottom" "inner", orientation or positional relationship expressed by "outside" are based on phase
Orientation or positional relationship shown in the drawings is closed, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark
Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore above-mentioned term cannot
It is interpreted as limitation of the present invention.
The present invention is described in detail with reference to the accompanying drawings and detailed description, embodiment cannot go to live in the household of one's in-laws on getting married one by one herein
It states, but therefore embodiments of the present invention are not defined in following implementation.
Referring to figs. 1 and 2, spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design method packet of the invention
It includes S1, spacecrafts rendezvous main task is analyzed；S2, the aerial mission of overall process is divided according to time phase, to every
Influence of a stage fly event implementing result to task object is analyzed, and identification principle is formulated, will be to subsequent docking mission
Target completion is necessary event and is defined as critical event；S3, the critical event that will identify that use fault tree as top event
Analytic approach is analyzed, and is analyzed all necessary conditions for leading to top event failure；S4, the analysis result knowledge according to S3
The various faults mode of multiple target cooperative disposal Chu be related to；S5, a variety of events for the multiple target cooperative disposal identified
Barrier mode is disposed authorization according to the participant that fault mode disposition is related to.
Specifically, in step sl, spacecrafts rendezvous main task include spacecrafts rendezvous task, complete propellant addition and really
Protect spacefarer's safety.It is of course also possible to be a certain key technology verifying or the sundry item that user is concerned about, these determine key
The identification principle of event.
In step s 2, critical event includes influencing security incident, may cause task termination event and flight is caused to count
Change event is drawn, wherein influencing security incident includes influencing personnel safety event and influencing spacecraft security incident.Such as Fig. 2 institute
Show, according to influence security incident, may cause task termination event and flight plan change event is caused to divide the time,
One event may influence simultaneously peace safely, may cause task termination and flight plan caused to change, i.e., in figure influence safety
Event may cause task termination event and cause the lap of flight plan change event bigger, illustrate the shadow of the event
It is bigger to ring consequence, determines therefrom that critical event.
In step s3, analysis is carried out to all necessary conditions for causing top event to fail to include information exchange analysis, set
Standby task analysis, spatial temporal analysis and people-ship-device-ground cooperating analysis.After above content analysis, from different dimensions
It identifies and is related to the fault mode of multiple target cooperative disposal.Due to analyzing information exchange, equipment task analysis, spatial temporal
Analysis and people-ship-device-ground cooperating analysis, it can be ensured that the fault mode identified it is comprehensive, designed comprehensively for fault countermeasure
Property provide guarantee.
In step s 5, when being disposed authorization according to the participant that fault mode disposition is related to, need to navigate to tool
Body personnel, password and treatment procedures.Specifically, according to safety, observing and controlling and time constraint condition, according to timing, failure point
Fault countermeasure detailed design is completed in branch and the disposition right handover definition of participant failure.The detailed design of fault countermeasure includes event
Initiation, responsibility subsystem or the big system of barrier, the branch of failure and corresponding Disposal Measures, failure disposition handover relationship and
Failure disposes structural criteria.
Spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design method of the invention, solved in time, observing and controlling
Under equal Condition of Strong Constraint, multi-aircraft, multisystem participate in the problem of the complex fault prediction scheme design of disposition, can system, comprehensively,
It is efficiently completed the design of spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal, meets the need of spacecrafts rendezvous flight control task with higher
It asks.
Below by taking the design of spacelab spacecrafts rendezvous task failure prediction scheme as an example, method of the invention is illustrated:
Firstly, carrying out the analysis of spacelab task spacecrafts rendezvous main task, critical event criterion of identification is determined, with flight
Time is clue, in conjunction with the time domain airspace dynamic analysis of aerial mission, identifies a series of critical events of influence task success or failure.
Then critical event is unsuccessfully used as to fault tree top event, from information exchange, equipment task, spatial temporal and people-ship-device-ground
The dimensions such as cooperation are analyzed, and identify all events for leading to top event failure, combination failure mode and impact analysis
(FMEA) all subsystems relevant to critical event disposition and big system are further identified.
In spacecrafts rendezvous task Butt Section, representative key event includes: capture and butt-joint locking etc..If capture failure occurs
Or butt-joint locking failure fault mode, then exist and needs airship docking mechanism, airship GNC, target docking structure, target GNC
With the possibility of spacefarer's disposition.Simultaneously because Butt Section airship and target aircraft, which are in, stops control state, it is overproof that there are postures
Hou Chu observing and controlling area relaying can not track possibility, and ground can not control aircraft, eventually lead to the possibility of mission failure, because
This fault mode must complete disposition before ground out connects observing and controlling area.Typically it is related to multiple target collaboration at this point, there is
The fault mode of disposition.
Then, for the fault mode of identification, under the constraint conditions such as safety, observing and controlling and time, according to information interchange,
Timing etc. carries out detailed design to failure disposition step, disposes branch to failure and interface handover relationship is defined.Including bright
Responsibility subsystem (or specific to people), the responsibility subsystem of clear failure disposition or big system, bright are initiated in the judgement of true failure
The cooperation subsystem or big system of true failure disposition design all fault branches being likely to occur and corresponding Disposal Measures, set
Meter in faulty Disposal Measures the interface relationship of participant (clearly enter into and exit from condition, can be certain instruction, certain signal
Or time point etc.), the disposition ending-criterion or mark of all fault branches of design, be finally completed at the collaboration of certain fault countermeasure
It sets.If the docking structure in spacecrafts rendezvous task locks relevant fault mode, to improve disposal efficiency, posture rail is authorized in advance
Control, docking mechanism monitoring post carry out failure disposition, complete the failure disposition division of labor and disposition according to the password defined each other
The handover of right, it is ensured that the connectivity and harmony of failure disposition.Before task, method of the invention can be drilled repeatedly
Practice, confirms the enforceability of prediction scheme.
The foregoing is merely a schemes of the invention, are not intended to restrict the invention, for the technology of this field
For personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (8)
1. a kind of spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design method, comprising:
S1, spacecrafts rendezvous main task is analyzed；
S2, the aerial mission of overall process is divided according to time phase, to each stage fly event implementing result to appoint
The influence of business target is analyzed, and identification principle is formulated, and will be necessary event to the completion of subsequent docking mission target and is defined as
Critical event；
S3, the critical event that will identify that are analyzed as top event using Fault Tree Analysis, to leading to the top
All necessary conditions of event failure are analyzed；
S4, it identifies according to the analysis result of the S3 and is related to the various faults mode of multiple target cooperative disposal；
S5, for the various faults mode of the multiple target cooperative disposal identified, be related to according to fault mode disposition
Participant is disposed authorization.
2. spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design method according to claim 1, feature exist
In, in the step S1, the spacecrafts rendezvous main task include spacecrafts rendezvous task, complete propellant add and ensure space flight
Member's safety.
3. spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design method according to claim 1, feature exist
In in the step S2, the critical event includes influencing security incident, may cause task termination event and cause to fly
Plan change event.
4. spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design method according to claim 3, feature exist
In the influence security incident includes influencing the security incident of spacecrafts rendezvous participant and influence spacefarer's security incident.
5. spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design method according to claim 1, feature exist
In, in the step S3, to cause all necessary conditions of top event failure carry out analysis include information exchange analysis,
Equipment task analysis, spatial temporal analysis and people-ship-device-ground cooperating analysis.
6. spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design method according to claim 1, feature exist
In when being disposed authorization according to the participant that is related to of fault mode disposition, navigating to specific people in the step S5
Member, password and treatment procedures.
7. spacecrafts rendezvous task multiple target fault countermeasure cooperative disposal design method according to claim 6, feature exist
In in the step S5, according to safety, observing and controlling and time constraint condition, according to timing, fault branch and participant event
Fault countermeasure detailed design is completed in barrier disposition right handover definition.
8. the more Spacecraft malfunction prediction scheme cooperative disposal design methods of spacecrafts rendezvous task according to claim 7, feature
It is, the fault countermeasure detailed design includes: the judgement of clear failure or the duty for initiating responsibility subsystem, clear failure disposition
All fault branches for appointing subsystem or big system, the cooperation subsystem of clear failure disposition or big system, design to be likely to occur
And the interface relationship of participant in corresponding Disposal Measures, the faulty Disposal Measures of design institute, the place for designing all fault branches
Ending-criterion or mark are set, the cooperative disposal of certain fault countermeasure is finally completed.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110705051A (en) * | 2019-09-17 | 2020-01-17 | 北京航空航天大学 | Dynamic fault tree model and simulation method of time constraint touch-change logic |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090113248A1 (en) * | 2007-10-26 | 2009-04-30 | Megan Elena Bock | Collaborative troubleshooting computer systems using fault tree analysis |
| CN103810383A (en) * | 2014-01-27 | 2014-05-21 | 中国航天标准化研究所 | Method for identifying and analyzing single-point failure mode of launch vehicle |
| CN104298825A (en) * | 2014-10-10 | 2015-01-21 | 中国科学院合肥物质科学研究院 | Fault tree collaborative analysis system based on authority management and model decomposition |
| CN108170566A (en) * | 2017-12-18 | 2018-06-15 | 新疆金风科技股份有限公司 | Product failure information processing method, system, equipment and collaboration platform |
| CN108418728A (en) * | 2018-02-12 | 2018-08-17 | 北京空间技术研制试验中心 | A kind of system detection method for spacecraft launching site aerial mission |
-
2018
- 2018-11-27 CN CN201811427128.0A patent/CN109583747A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090113248A1 (en) * | 2007-10-26 | 2009-04-30 | Megan Elena Bock | Collaborative troubleshooting computer systems using fault tree analysis |
| CN103810383A (en) * | 2014-01-27 | 2014-05-21 | 中国航天标准化研究所 | Method for identifying and analyzing single-point failure mode of launch vehicle |
| CN104298825A (en) * | 2014-10-10 | 2015-01-21 | 中国科学院合肥物质科学研究院 | Fault tree collaborative analysis system based on authority management and model decomposition |
| CN108170566A (en) * | 2017-12-18 | 2018-06-15 | 新疆金风科技股份有限公司 | Product failure information processing method, system, equipment and collaboration platform |
| CN108418728A (en) * | 2018-02-12 | 2018-08-17 | 北京空间技术研制试验中心 | A kind of system detection method for spacecraft launching site aerial mission |
Non-Patent Citations (2)
| Title |
|---|
| 杨健 等: "交会对接任务故障与应急仿真系统设计与实现", 《载人航天》 * |
| 杨海峰 等: "基于关键事件的系统级单点故障识别方法及应用", 《航天器环境工程》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110705051A (en) * | 2019-09-17 | 2020-01-17 | 北京航空航天大学 | Dynamic fault tree model and simulation method of time constraint touch-change logic |
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Application publication date: 20190405 |