CN106428649A - Automatic support system for reusable carriers - Google Patents
Automatic support system for reusable carriers Download PDFInfo
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- CN106428649A CN106428649A CN201610949964.XA CN201610949964A CN106428649A CN 106428649 A CN106428649 A CN 106428649A CN 201610949964 A CN201610949964 A CN 201610949964A CN 106428649 A CN106428649 A CN 106428649A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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Abstract
The invention discloses an automatic support system for reusable carriers. The system establishes an automatic support system for reusable carriers through the use of distributed design of informational network, solves the problem of low efficiency caused by the traditional manual transmission of support message and demands, enhances the supportability of reusable carriers. The multi-signal flow model is used to construct the fault observation matrix which in turn is used to achieve the fast acquisition of the status information of the reusable carriers and identify the representational state data of the fault. The use of hierarchical coding format for designing the technical status code solves the problem of the complexity and low use rate of the status data information of the reusable carrier products, materializes the fast data tracking of thousands of standalone equipment products in the reusable carrier. The use of unique singular technical status code can correlate the technical status to the equipment, and clarify the procedure for updating the technical status code of the reusable carrier and make sure the technical status is consistent.
Description
Technical field
The present invention relates to a kind of Control System for Reusable Launch Vehicle self -support system, belongs to spacecraft prognostics and health management and sets
Meter field.
Background technology
Self -support system is that vehicle realizes reusable key support system, and its degree of protection is directly affected
The task object of vehicle, again duty cycle, execution mission preparation time and task expense etc..With regard to Reusable Launch Vehicles
Speech, need experience 1. ground prepare section->2. the ascent stage->3. in orbit section->4. reentry return section->1. ground prepare section-
>..., various aerial mission stage rugged environment conditions, cause vehicle in complicated power, heat and electromagnetism and spatial loop
Border.Different from traditional vehicle, Reusable Launch Vehicles need realization to reenter execution times again after the detection that returns and land is safeguarded
Business, need to carry out a series of test maintaining safeguard work, this guarantee skill just to Reusable Launch Vehicles after vehicle lands
Art proposes higher autonomous type and requires.
The each model of domestic space industry carries out fault interpretation or Support planning, transmission electricity by the way of artificial mostly
Son or paper information, traditional comprehensive coverage is less efficient, relatively costly.It is different from conventional aerospace model, reusable delivery
Device possess quick come and go, reusable feature, the cycle of being on active service is long, if still adopting this kind of mode, the manpower for putting into, physics,
Financial resources will be very huge.
Additionally, all kinds of space product equipment of domestic space industry all have the product designation of oneself, at present either rocket, defend
Star or airship are all without total system unit product Unified coding, and each unit research institute code name form species is various, and this gives type
Number information system management work brings a lot of inconvenience.Be different from conventional aerospace model, Control System for Reusable Launch Vehicle possess quick come and go,
Reusable feature, the cycle of being on active service is long, needs to carry out which life cycle management integrated maintenance guarantee.Control System for Reusable Launch Vehicle
System composition is sufficiently complex, and on vehicle, how quick accurate product is with containing much information, associating and processing rule complexity,
Really realize vehicle portion dress, the flow process such as safeguard, ensure, it is necessary to rely on advanced information carrier fly through device whole week in life-span
Phase, realize the real time information sampling to aircraft life cycle management, it is ensured that all product runnings and flow of information on aircraft
Real-time synchronization, so as to for staff make real-time, accurate, reliable plan and decision-making provide data supporting.
Content of the invention
The technology solve problem of the present invention is：Overcome existing Support technical deficiency, a kind of reusable fortune is provided
The self -support system of device is carried, solves the problems, such as that Traditional Man transmission ensures that message and demand cause guarantee inefficiency, to can
Reusable Launch Vehicles status information quick obtaining, at the same solve Control System for Reusable Launch Vehicle Product Status data message numerous and diverse and
The low problem of utilization rate, realizes over thousands of kind of unit portion product facility product data of Control System for Reusable Launch Vehicle and quickly reviews, clearly
The more new technological process of the state of the art code of Control System for Reusable Launch Vehicle, it is ensured that state of the art is consistent, improves Reusable Launch Vehicles
Self -support.
The technical solution of the present invention is：A kind of Control System for Reusable Launch Vehicle self -support system, the system includes to sweep
Code device, data server, coding follower, telemetry decoder and multiple man-machine interactive platforms, wherein：
Code reader, for the state of the art code on each product facility on scanning recognition Reusable Launch Vehicles, and by its
Data server is delivered to, the state of the art code is comprising model, system membership, installation state, state of the art baseline, flight
Sortie information；
Coding follower, the state of the art code of each product facility of the Reusable Launch Vehicles that receiving data server sends,
And printout；
Data server, real time record simultaneously shows that the resume of each product facility of Reusable Launch Vehicles life cycle management are believed
Breath, the record information includes essential information, state of the art code and the test number of all product facilities of Reusable Launch Vehicles
According to；The state of the art code of code reader transmission is received, according to the corresponding equipment record information of state of the art code coupling, and in real time more
New technique conditional code and equipment record information；According to instruction is manually entered, refer to coding follower output Reusable Launch Vehicles
Determine the state of the art code of product facility；Receive and preserve the telemetry of telemetry decoder transmission, which is parsed, is obtained
To telemetry parameter, whether abnormal according to remote measurement number parameter, determine fault sensor test point, afterwards, surveyed according to fault sensor
Pilot and fault observation matrix, are inferred to malfunction and failure pattern, and further according to malfunction and failure pattern, the fault for indexing storage inside is lost
Effect pattern table corresponding with product facility, generates Support demand item list, sends to malfunction and failure pattern related products and set
Standby man-machine interactive platform；
Telemetry decoder, receives the descending wireless telemetry signal of Reusable Launch Vehicles, and demodulation obtains telemetry, sends out
Deliver to data server；
Man-machine interactive platform, receives Support demand item list, by artificial according to Support demand item list, in time
Make Support planning.
The state of the art code adopts layered coding format, by type identifier code, Primary layer subcategory number, installation code, extension generation
Number is constituted, wherein：
Type identifier code, for representing vehicle model；
Primary layer subcategory number, comprising 1～N shell subcategory number, for representing the affiliated subsystem of vehicle, subsystem or unit；With
It is coordination between one level coding, does not intersect, do not repeat；It is to be subordinate to pass between next bit level and last layer time coding
System；
Installation code, for representing vehicle in " installation " state or " non-installation " state；
Extension code name code, for representing vehicle running status, including state of the art baseline and sortie number.
The state of the art code is attached on product facility or product facility encapsulation as product identification.
The installation code information default of the state of the art code is " non-installation " state, is transported when arbitrary product facility is selected
When carrying device assembling, first, it is " installation " state to update the data the installation code in server in state of the art code；Then, by compiling
Code follower export technique conditional code, the state of the art code is attached on product；When ground test or execution task, by the skill
The test data that art conditional code is carried out with repeatable vehicle is bound, used as the key word of retrieval and inquisition test data；Ground
After face test or execution task, the current state of the art code of the product when dismantling, is recognized to product by code reader, then
Installation code in secondary update method conditional code is " non-installation " state, by encoding follower export technique conditional code, by the skill
Art conditional code is attached on product.
The Reusable Launch Vehicles fault observation matrix is as shown in the table：
In table：
Ti, i are positive integer, and i >=1 represents i-th Sensor；
FMi, i are positive integer, and i >=1 represents i-th failure mode；
Certain Sensor that in table, " 1 " represents in its corresponding lengthwise position breaks down and mistake on lateral attitude
Effect pattern correlation.
The fault observation matrix is set up in the following manner：
(1) starting point and the terminating point of signal, according to the functional performance of each subsystem of Control System for Reusable Launch Vehicle, are determined,
In conjunction with sensor test point position, the multi-signal flow graph model that each subsystem product signal is propagated is built；
(2), moved towards according to the signal in each subsystem multi-signal flow graph model, determine the fault cause and effect of system product equipment
The dependence of relation and sensor test point and product facility fault；
(3), the equipment that flows through of signal of sensor test point test, as index by the failure mode of product facility and
Test point is associated, and sets up fault observation matrix.
Pass through Ethernet exchanging data between the data server, telemetry decoder, multiple man-machine interactive platforms
Information.
Compared with the prior art, the invention has the advantages that：
(1), the present invention adopts distributed information network struction a kind of suitable for the autonomous of Control System for Reusable Launch Vehicle
Safeguards system, solves the problems, such as that Traditional Man transmission ensures that message causes to ensure inefficiency with demand, to reusing fortune
Carrying device carries out information-based self -support, improves the protection of Reusable Launch Vehicles；
(2), the present invention sets up fault observation matrix using using multi signal flow model, and it is right to be realized by fault observation matrix
Control System for Reusable Launch Vehicle quick obtaining, and fault signature status data is recognized, and then self -support has been better achieved；
(3), the present invention adopts level coded format designing technique conditional code, solves Control System for Reusable Launch Vehicle product shape
The low problem of the numerous and diverse and utilization rate of state data message, it is achieved that over thousands of kind of unit portion product facility product of Control System for Reusable Launch Vehicle
Data are quickly reviewed, and are conducive to the control to product technology state, are that Control System for Reusable Launch Vehicle life cycle management is independently accurate
Ensure and technical support is provided；
(4), state of the art is associated with equipment by the present invention using unique state of the art code, and be specify that reusable
The more new technological process of the state of the art code of vehicle, it is ensured that state of the art is consistent, is that vehicle realizes reusable Fast-Maintenance
With guarantee there is provided support.
Description of the drawings
Fig. 1 is the Control System for Reusable Launch Vehicle self -support system design of the present invention.
Fig. 2 is the Control System for Reusable Launch Vehicle intelligence hierarchy encoding method of the present invention.
Specific embodiment
Describe the present invention with specific embodiment below in conjunction with the accompanying drawings.
As shown in figure 1, a kind of Control System for Reusable Launch Vehicle self -support system is defeated by code reader, data server, coding
Go out device, telemetry decoder and multiple man-machine interactive platforms composition, wherein：
Code reader, for the state of the art code on each product facility on scanning recognition Reusable Launch Vehicles, and passes through
RS232 bus sends it to data server, and the state of the art code is comprising model, system membership, installation state, skill
Art state baseline, Sortie information；
Coding follower, each product facility of the Reusable Launch Vehicles for being sent by RS232 bus receiving data server
State of the art code, and printout；
Data server, real time record simultaneously shows that the resume of each product facility of Reusable Launch Vehicles life cycle management are believed
Breath, the record information includes essential information, state of the art code and the test number of all product facilities of Reusable Launch Vehicles
According to essential information is usually the intrinsic information of product facility, such as date of manufacture, company-information etc.；Receive the skill of code reader transmission
Art conditional code, mates corresponding equipment record information according to the state of the art code, and real-time update state of the art code and equipment are carried out
Go through information；According to instruction is manually entered, Reusable Launch Vehicles appointed product is exported to coding follower by RS232 bus and is set
Standby state of the art code；Receive and preserve the telemetry of telemetry decoder transmission, which is parsed, obtain remote measurement ginseng
Number, whether abnormal according to remote measurement number parameter, determine fault sensor test point, afterwards, according to fault sensor test point and event
Barrier observing matrix, is inferred to malfunction and failure pattern, further according to malfunction and failure pattern, index the malfunction and failure pattern of storage inside with
Product facility corresponds to table, generates Support demand item list, is sent to malfunction and failure pattern related products by Ethernet
Equipment man-machine interactive platform, malfunction and failure pattern Biao Shi product facility producer corresponding with product facility is according to product facility
Self structure characteristic, carries out what FMEA analysis was worked out, and every kind of malfunction and failure pattern preferably refine to the bottom event of fault tree；
Telemetry decoder, receives the descending wireless telemetry signal of Reusable Launch Vehicles, and demodulation obtains telemetry, presses
Send to data server according to Ethernet protocol again framing；
Man-machine interactive platform, receives Support demand item list, by artificial according to Support demand item list, in time
Make Support planning.
Being mainly characterized by for the self -support system distributed information network of above-mentioned Reusable Launch Vehicles is distributed, letter
Breathization, automatization, obtain status data on Reusable Launch Vehicles by telemetry decoder by wireless channel, then by remote measurement
Data decoder sends decoding data to self -support intranet data server, then is needed by data server generation Support
Ask or the concrete information transfer such as diagnostic test reason or Test Suggestion is to corresponding human-computer interaction terminal, information exchange adopts ether
Net, RS232 serial bus network, realize status information quick obtaining and identification.
The state of the art code is the only identification code of each product facility state of the art of Reusable Launch Vehicles, for certainly
The different technologies state of each product facility is characterized in the flow process of main guarantee, each in life cycle management so as to realize reviewing product
Category information.State of the art code adopts layered coding format, and hierarchical coding is suitable for arrangement by the subordinate of object of classification, hierarchical relationship
When a kind of code of sequence, coding, code is divided into some levels, and corresponding with the classification level of object of classification.Same level is compiled
It is coordination between code, does not intersect, do not repeat；It is membership between next bit level and last layer time coding.
Layer code is represented with numeral, corresponds respectively to a unit in hierarchy per layer digital, constitutes corresponding item
Mesh decomposition texture code.From left to right, the level of expression is from high to low for code.
Two digits represent the coding of a level from the beginning of 00, arrange by ascending order, do and how can work out 99.
Three bit digital represent the coding of a level from the beginning of 000, arrange by ascending order, do and how can work out 999.
As shown in Fig. 2 the technology of the present invention conditional code is by type identifier code, Primary layer subcategory number, installation code, extension code name code structure
Become.In addition to type identifier code letter representation, other codes are by numeral composition.
Wherein：
Type identifier code, for representing vehicle model, such as：SD；
Primary layer subcategory number, is divided into three layers, represents the affiliated subsystem of vehicle, subsystem or unit respectively, can be to repeating
Encoded using all product facilities on vehicle, coding refinement to field changeable unit (LRU).Wherein：
1st layer is represented with double figures, product primary structure is encoded, corresponding to each subsystem.
It is as shown in the table that code constitutes example：
| Code | Title | Code | Title |
| 05 | Overall circuit subsystem | 09 | Landing subsystem |
| 24 | Power subsystem | 19 | Thermal protection subsystem |
| 53 | Structure subsystem | 23 | Telemetry subsystem |
| 58 | Test subsystem | 34 | Control subsystem |
| 57 | Mechanism's subsystem | 71 | Power subsystem |
2nd layer is represented with double figures, feature of a certain structural system according to the 1st layer is finely divided, is under the jurisdiction of the 1st layer,
Corresponding to each subsystem.System typically presses Function Decomposition, and structure is typically by assembling membership decomposition.
3rd layer is represented with two digits, and the structure of last layer is finely divided again according to membership, is produced corresponding to unit
Product.
The basic level of more levels can also be distributed by concrete condition according to above-mentioned rule.
Installation code, for representing vehicle installation state, represents whether install at present, and " 999 " represent installation；
Extension code name code, with representing using two-part, accounts for 3, and first is state of the art baseline, the technology shape from left to right
State baseline information is referred in the functional characteristic for reaching specified in state of the art file and in product (hardware, software) and thing
The status information of reason characteristic, for example, the state such as first sample, sample or software and hardware release status.Number from 1 to 9；Two is frame afterwards
Secondary number, represent first ride, fly for second ... that the information such as n-th flight is numbered from 01 to 99.
The Reusable Launch Vehicles state of the art code is through the information carrier of the whole life cycle of Reusable Launch Vehicles, layer
Secondary clear, autgmentability is strong.
State of the art code is attached on product facility or product facility encapsulation simultaneously as product identification.Each on aircraft
The state of the art code of product facility is respectively provided with independent technology all using the corresponded manner of " one yard of a thing " per part product (LRU)
Conditional code.By unique state of the art code, various information of the product in life cycle management can be totally reviewed, and in the full longevity
Life cycle interior coding is not altered, and does not reclaim use, and main part is not distinguished with spare part number.
It is right that state of the art code is generally attached to using the modes such as label, spray painting, stickup, laser inscription of packing, be listed, put up
On the product that answers, for coding and interrelational form in kind, according to different product construction featuress and feature, can be divided into following several
The mode of kind：
A) coding is pasted on work certificate；
B) to the less demanding product of profile, will be encoded by laser marking machine in kind and beat in product surface；
C) mode that is deposited with packaging bag for the product of small volume, selection, coding is pasted onto in packaging bag, or profit
With marking pen etc., manual identification is carried out on product；
D) for the accurate product that volume is larger, storage can neither can not be packed again in product surface stamp, may be selected
To be encoded with marking machine and beat on nameplate, hang on product.
Reusable Launch Vehicles fault observation matrix is as shown in the table：
In table：
Ti, i are positive integer, and i >=1 represents i-th Sensor；
FMi, i are positive integer, and i >=1 represents i-th failure mode；
In table, " 1 " represents the failure on the fault of certain Sensor in its corresponding lengthwise position and lateral attitude
Pattern correlation.For example：By Sensor T1 report therefore, when state is " 1 ", failure mode FM1/FM2 fault can be learnt, by sensing
Device measuring point T2 report event, when state is " 1 ", can learn failure mode FM2/FM3/FM4 fault etc..
According to the fault observation matrix, can clear and definite concrete failure cause, and corresponding maintenance is provided according to fault level
The requirements of support, cannot such as position concrete failure cause, form ambiguity group reason, and provide the information such as further Test Suggestion.
Fault observation matrix is set up in the following manner：
(1) starting point and the terminating point of signal, according to the functional performance of each subsystem of Control System for Reusable Launch Vehicle, are determined,
In conjunction with sensor test point position, the multi-signal flow graph model that each subsystem product signal is propagated is built；
(2), moved towards according to the signal in each subsystem multi-signal flow graph model, determine the fault cause and effect of system product equipment
The dependence of relation and sensor test point and product facility fault；
(3), the equipment that flows through of signal of sensor test point test, as index by the failure mode of product facility and
Test point is associated, and sets up fault observation matrix.
By taking power subsystem as an example, battery is responsible for power-supply controller of electric and powers, and arranges sensor survey in power-supply controller of electric
Point T1, monitors secondary power supply voltage, and the secondary power supply powered for power controller controls plate, then multi-signal flow graph model be by electricity
Pond output primary voltage->Be input into power-supply controller of electric->Power-supply controller of electric voltage transformation->Be converted to the secondary electricity of power-supply controller of electric
Pressure->Sensor T1 is monitored.Sensor T1 test point is probably power-supply controller of electric secondary power supply electric voltage exception (FM2) extremely, also may be used
Can be that battery output primary voltage is abnormal (FM1), therefore, T1 and FM2 point of intersection set in fault observation matrix, T1 and FM1 is handed over
Point also locates set, sets up fault observation matrix with this.
After product is paid, before general assembly, state of the art code is formed according to product essential information, is input to database service
Device, the installation code in the state of the art code is defaulted as " non-installation " state；When select to have same code name, different numbering many
When one in platform (covering) product is used for executing task assembling, first, the installation code in update method conditional code is " installation " shape
State；Then, by encoding follower export technique conditional code, the state of the art code is attached on product；Subsequently, execute and appoint
It is engaged in, and a series of test datas that repeatable vehicle is carried out is bound with the state of the art code, that is, enters with the product
Row binding；After Reusable Launch Vehicles execution task, when ground self -support is executed with safeguarding, product being dismantled, leads to
The current state of the art code that code reader recognizes the product is crossed, the installation code in update method conditional code is " non-installation " state,
While " tasks carrying number of times " is updated in the record information of database server, by encoding follower export technique state
Code, the state of the art code is attached on product, is subsequently turned internal field by outfield and is carried out guarantee and safeguards and record.
Self -support system is used for transmission and turns the letter such as the Support demand in internal field and concrete diagnostic test reason by outfield
Cease to remote human-machine's interaction platform, idiographic flow is：When product needed is tested further, keeps in repair or maintained, first by
Database server recognizes Product Status and degrades or abnormal, and database server cannot provide degradation or abnormal former after diagnosing
Cause, or the demand for needing repairing or maintaining can be given, then demand item list is generated by database server side, through outer field technology
Send after personnel's confirmation is errorless to related remote human-machine's interaction platform, be analyzed by remote human-machine's interaction platform, and make
Determine Support planning, by field data storehouse server end is fed back, aid in outfield technical staff's decision-making, the demand item list
Degrade including Product Status or the information such as abnormal tentative diagnosis result, further testing requirement, personnel, funds, cycle.
The present invention can achieve vehicle life cycle management digital management using hierarchical coding, as aerocraft system constitutes
Complicated and possess reusable feature, flying product informationization digital management is for aircraft life cycle management comprehensive coverage
Significant, therefore, carrying out with different levels Unified coding to each product of aircraft is that relation aircraft can be reusable important
Factor.
Reusable Launch Vehicles self -support system, implementing procedure and various methods according to the present invention etc., belong to
Protection scope of the present invention.
Unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (7)
1. a kind of Control System for Reusable Launch Vehicle self -support system, it is characterised in that including code reader, data server, encode defeated
Go out device, telemetry decoder and multiple man-machine interactive platforms, wherein：
Code reader, for the state of the art code on each product facility on scanning recognition Reusable Launch Vehicles, and sends it to
Data server, the state of the art code is comprising model, system membership, installation state, state of the art baseline, Sortie
Information；
Coding follower, the state of the art code of each product facility of the Reusable Launch Vehicles that receiving data server sends, and beat
Print output；
Data server, real time record simultaneously shows the record information of each product facility of Reusable Launch Vehicles life cycle management, institute
Stating record information includes the essential information of all product facilities, state of the art code and the test data of Reusable Launch Vehicles；Connect
The state of the art code of code reader transmission is received, corresponding equipment record information, and real-time update skill are mated according to the state of the art code
Art conditional code and equipment record information；According to instruction is manually entered, specifies to coding follower output Reusable Launch Vehicles and produce
The state of the art code of product equipment；Receive and preserve the telemetry of telemetry decoder transmission, which is parsed, is obtained distant
Parameter is surveyed, whether abnormal according to remote measurement number parameter, determine fault sensor test point, afterwards, according to fault sensor test point
And fault observation matrix, it is inferred to malfunction and failure pattern, further according to malfunction and failure pattern, indexes the malfunction and failure mould of storage inside
Formula table corresponding with product facility, generates Support demand item list, sends to malfunction and failure pattern related products equipment people
Machine interaction platform；
Telemetry decoder, receives the descending wireless telemetry signal of Reusable Launch Vehicles, and demodulation obtains telemetry, send to
Data server；
Man-machine interactive platform, receives Support demand item list, by artificial according to Support demand item list, makes in time
Support is planned.
2. a kind of Control System for Reusable Launch Vehicle self -support system according to claim 1, it is characterised in that：The technology
Conditional code adopts layered coding format, is made up of type identifier code, Primary layer subcategory number, installation code, extension code name code, wherein：
Type identifier code, for representing vehicle model；
Primary layer subcategory number, comprising 1～N shell subcategory number, for representing the affiliated subsystem of vehicle, subsystem or unit；Same layer
It is coordination between secondary coding, does not intersect, do not repeat；It is membership between next bit level and last layer time coding；
Installation code, for representing vehicle in " installation " state or " non-installation " state；
Extension code name code, for representing vehicle running status, including state of the art baseline and sortie number.
3. a kind of Control System for Reusable Launch Vehicle self -support system according to claim 1, it is characterised in that：The technology
Conditional code is attached on product facility or product facility encapsulation as product identification.
4. a kind of Control System for Reusable Launch Vehicle self -support system according to claim 3, it is characterised in that：The technology
The installation code information default of conditional code is " non-installation " state, when selecting arbitrary product facility to carry out vehicle assembling, first,
It is " installation " state to update the data the installation code in server in state of the art code；Then, by encoding follower export technique
Conditional code, the state of the art code is attached on product；Ground test or when executing task, by the state of the art code with repeatable
The test data that vehicle is carried out is bound, used as the key word of retrieval and inquisition test data；Ground test or execution task
Afterwards, the current state of the art code of the product, when dismantling to product, is recognized by code reader, again update method conditional code
In installation code be " non-installation " state, by encode follower export technique conditional code, the state of the art code is attached to product
On product.
5. a kind of Control System for Reusable Launch Vehicle self -support system according to claim 1, it is characterised in that：The repetition
As shown in the table using vehicle fault observation matrix：
In table：
Ti, i are positive integer, and i >=1 represents i-th Sensor；
FMi, i are positive integer, and i >=1 represents i-th failure mode；
Certain Sensor that in table, " 1 " represents in its corresponding lengthwise position breaks down and failure mould on lateral attitude
Formula correlation.
6. a kind of Control System for Reusable Launch Vehicle self -support system according to claim 5, it is characterised in that：The fault
Observing matrix is set up in the following manner：
(1) starting point and the terminating point of signal, according to the functional performance of each subsystem of Control System for Reusable Launch Vehicle, are determined, in conjunction with
Sensor test point position, builds the multi-signal flow graph model that each subsystem product signal is propagated；
(2), moved towards according to the signal in each subsystem multi-signal flow graph model, determine the Failure causality of system product equipment
Dependence with sensor test point and product facility fault；
(3), the equipment that flows through of signal of sensor test point test, as index by the failure mode of product facility and test
Point is associated, and sets up fault observation matrix.
7. a kind of Control System for Reusable Launch Vehicle self -support system according to claim 1, it is characterised in that：The data
Pass through Ethernet exchanging data message between server, telemetry decoder, multiple man-machine interactive platforms.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107963240A (en) * | 2017-11-20 | 2018-04-27 | 中国运载火箭技术研究院 | A kind of Reusable Launch Vehicles automatic fault diagnosis and intelligent maintenance system and method |
| CN111071487A (en) * | 2019-12-10 | 2020-04-28 | 上海空间推进研究所 | On-orbit autonomous management method and system for planetary probe propulsion system |
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| CN111071487B (en) * | 2019-12-10 | 2021-06-04 | 上海空间推进研究所 | On-orbit autonomous management method and system for planetary probe propulsion system |
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