CN106428649B - A kind of Control System for Reusable Launch Vehicle self -support system - Google Patents
A kind of Control System for Reusable Launch Vehicle self -support system Download PDFInfo
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- CN106428649B CN106428649B CN201610949964.XA CN201610949964A CN106428649B CN 106428649 B CN106428649 B CN 106428649B CN 201610949964 A CN201610949964 A CN 201610949964A CN 106428649 B CN106428649 B CN 106428649B
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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
Abstract
The invention discloses a kind of Control System for Reusable Launch Vehicle self -support systems, the system is by using distributed information network design, a kind of self -support system suitable for Control System for Reusable Launch Vehicle is built, it solves the problems, such as that traditional artificial transmitting ensures that message and demand cause to ensure inefficiency, improves the protection of Reusable Launch Vehicles；Fault observation matrix is established using multi signal flow model, is realized by fault observation matrix to Control System for Reusable Launch Vehicle status information quick obtaining, and identify fault signature status data；It using level coded format designing technique status code, solves the problems, such as that Control System for Reusable Launch Vehicle Product Status data information is many and diverse and utilization rate is low, realizes over thousands of kind of single machine portion product facility product data of Control System for Reusable Launch Vehicle and quickly trace；State of the art is associated with equipment using unique state of the art code, and specifies 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.
Description
Technical field
The present invention relates to a kind of Control System for Reusable Launch Vehicle self -support systems, belong to spacecraft prognostics and health management and set
Meter field.
Background technique
Self -support system is that vehicle realizes that reusable crucial support system, degree of protection directly affect
The task object of vehicle, executes mission preparation time and task expense etc. at duty cycle again.With regard to Reusable Launch Vehicles
Speech, need to undergo 1. ground prepare ascent stage of section -> 2. -> 3. and prepare section-in the ground of the reentry return section of section -> 4. -> 1. in orbit
> ..., various aerial mission stage rugged environment conditions cause vehicle to be in complicated power, heat and electromagnetism and spatial loop
Border.It is different from traditional vehicle, execution times again after Reusable Launch Vehicles needs realization reenters return and detection maintenance of landing
Business need to carry out a series of test maintaining safeguard work after vehicle landing, this is just to the guarantee skill of Reusable Launch Vehicles
Art proposes higher autonomous type requirement.
Domestic each model of space industry carries out failure interpretation or Support planning, transmitting electricity by the way of artificial mostly
Son or paper information, traditional comprehensive coverage efficiency is lower, higher cost.It is different from conventional aerospace model, reusable delivery
Device has quickly round-trip, the characteristics of reusing, and the period of being on active service is long, if still using such mode, the manpower put into, physics,
Financial resources will be very huge.
In addition, domestic all kinds of space product equipment of space industry have the product designation of oneself, at present either rocket, defend
All without total system single machine product Unified coding, each single machine research institute code name form is many kinds of for star or airship, this gives type
Number information system management work belt is come many inconvenient.Be different from conventional aerospace model, Control System for Reusable Launch Vehicle have quickly it is round-trip,
The characteristics of reuse, the period of being on active service is long, needs to carry out it life cycle management integrated maintenance guarantee.Control System for Reusable Launch Vehicle
System composition is sufficiently complex, and product has the characteristics that contain much information, be associated with and handle regular complexity on vehicle, how quickly quasi-
Really realize the processes such as vehicle portion dress, maintenance, guarantee, it is necessary to by advanced information carrier fly through device entire week in service life
Phase realizes the real time information sampling to aircraft life cycle management, guarantees all product operational process and information flow on aircraft
Real-time synchronization, thus for staff make it is real-time, accurate, reliable plan and decision data supporting is provided.
Summary of the invention
Technology of the invention solves the problems, such as: overcoming existing Support technical deficiency, provides a kind of reusable fortune
The self -support system for carrying device solves the problems, such as that traditional artificial transmitting ensures that message and demand lead to guarantee inefficiency, to can
Reusable Launch Vehicles status information quick obtaining, at the same solve Control System for Reusable Launch Vehicle Product Status data information it is many and diverse and
The low problem of utilization rate realizes that over thousands of kind of single machine portion product facility product data of Control System for Reusable Launch Vehicle quickly trace, clear
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 invention is as follows: a kind of Control System for Reusable Launch Vehicle self -support system, which includes sweeping
Code device, data server, coding follower, telemetry decoder and multiple man-machine interactive platforms, in which:
Code reader, the state of the art code on scanning recognition Reusable Launch Vehicles on each product facility, and sent out
It send to data server, the state of the art code includes model, system membership, installation state, state of the art baseline, flight
Sortie information；
Follower is encoded, the state of the art code for each product facility of Reusable Launch Vehicles that data server is sent is received,
And it prints out；
Data server records in real time and shows the resume letter of each product facility of Reusable Launch Vehicles life cycle management
Breath, the resume information include 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 that code reader is sent is received, corresponding equipment resume information is matched according to the state of the art code, and in real time more
New technology status code and equipment resume 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；The telemetry for receiving and saving the transmission of telemetry decoder, parses it, obtains
It is whether abnormal according to telemetering number parameter to telemetry parameter, it determines fault sensor test point, later, is surveyed according to fault sensor
Pilot and fault observation matrix are inferred to malfunction and failure mode, and further according to malfunction and failure mode, the failure for indexing storage inside is lost
Effect mode table corresponding with product facility generates Support demand item list, is sent to malfunction and failure mode related products and sets
Standby man-machine interactive platform；
Telemetry decoder receives Reusable Launch Vehicles downlink wireless telemetry signal, and demodulation obtains telemetry, sends out
It send 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 uses layered coding format, by type identifier code, Primary layer subcategory number, installation code, extension generation
Number is constituted, in which:
Type identifier code, for indicating vehicle model；
Primary layer subcategory number includes 1~N layer code, for indicating the affiliated subsystem of vehicle, subsystem or single machine；Together
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 a upper level coding
System；
Installation code, for indicating that vehicle is in " installation " state or " non-installation " state；
Code name code is extended, for indicating vehicle operating 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, when any product facility of selection is transported
When carrying device assembly, firstly, updating the installation code in data server in state of the art code is " installation " state；Then, pass through volume
Code follower export technique status code, which is attached on product；When ground test or execution task, by the skill
The test data that art status code is carried out with repeatable vehicle is bound, the keyword as retrieval and inquisition test data；Ground
After face test or execution task, when dismantling to product, the current state of the art code of the product is identified by code reader, then
Installation code in secondary update method status code is " non-installation " state, by encoding follower export technique status code, by the skill
Art status 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 indicates i-th of Sensor；
FMi, i are positive integer, and i >=1 indicates i-th of failure mode；
" 1 " indicates that some Sensor in its corresponding lengthwise position breaks down and the mistake on lateral position in table
Effect mode is related.
The fault observation matrix is established in the following manner:
(1), according to the functional performance of each subsystem of Control System for Reusable Launch Vehicle, the starting point and terminating point of signal are determined,
In conjunction with sensor test point position, the multi-signal flow graph model that each subsystem product signal is propagated is constructed；
(2), it is moved towards according to the signal in each subsystem multi-signal flow graph model, determines the failure cause and effect of system product equipment
The dependence of relationship and sensor test point and product facility failure；
(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 establishes fault observation matrix.
The data server, telemetry decoder pass through Ethernet exchanging data between multiple man-machine interactive platforms
Information.
Compared with the prior art, the invention has the advantages that:
(1), the present invention is a kind of suitable for the autonomous of Control System for Reusable Launch Vehicle using distributed information network struction
Safeguards system solves the problems, such as that traditional artificial transmitting ensures that message and demand cause to ensure inefficiency, transports to reusing
It carries device and carries out information-based self -support, improve the protection of Reusable Launch Vehicles；
(2), the present invention passes through fault observation matrix realization pair using fault observation matrix is established using multi signal flow model
Control System for Reusable Launch Vehicle quick obtaining, and identify fault signature status data, and then self -support has been better achieved；
(3), the present invention uses level coded format designing technique status code, solves Control System for Reusable Launch Vehicle product shape
The problem that state data information is many and diverse and utilization rate is low realizes over thousands of kind of single machine portion product facility product of Control System for Reusable Launch Vehicle
Data quickly trace, and are conducive to the control to product technology state, are that Control System for Reusable Launch Vehicle life cycle management is independently accurate
It ensures and technical support is provided；
(4), state of the art is associated with by the present invention using unique state of the art code with equipment, and is specified 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, realizes reusable Fast-Maintenance for vehicle
Support is provided with guarantee.
Detailed description of the invention
Fig. 1 is that Control System for Reusable Launch Vehicle self -support system of the invention designs.
Fig. 2 is Control System for Reusable Launch Vehicle intelligence hierarchy encoding method of the invention.
Specific embodiment
The present invention will be described in detail with specific embodiment with reference to the accompanying drawing.
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
Device, telemetry decoder and multiple man-machine interactive platforms composition out, in which:
Code reader, the state of the art code on scanning recognition Reusable Launch Vehicles on each product facility, and pass through
RS232 bus sends it to data server, and the state of the art code includes model, system membership, installation state, skill
Art state baseline, Sortie information；
Follower is encoded, each product facility of Reusable Launch Vehicles that data server is sent is received by RS232 bus
State of the art code, and print out；
Data server records in real time and shows the resume letter of each product facility of Reusable Launch Vehicles life cycle management
Breath, the resume information include 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；Receive the skill that code reader is sent
Art status code matches corresponding equipment resume 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；The telemetry for receiving and saving the transmission of telemetry decoder, parses it, obtains telemetering ginseng
Number, it is whether abnormal according to telemetering number parameter, fault sensor test point is determined, later, according to fault sensor test point and event
Hinder observing matrix, be inferred to malfunction and failure mode, further according to malfunction and failure mode, index the malfunction and failure mode of storage inside with
Product facility corresponds to table, generates Support demand item list, is sent to malfunction and failure mode related products by Ethernet
Equipment man-machine interactive platform, the malfunction and failure mode table corresponding with product facility is product facility producer according to product facility
Self structure characteristic carries out what FMEA analysis was worked out, and every kind of malfunction and failure mode preferably refine to the bottom event of fault tree；
Telemetry decoder, receives Reusable Launch Vehicles downlink wireless telemetry signal, and demodulation obtains telemetry, presses
Data server is sent to 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, believes
Breathization, automation obtain status data on Reusable Launch Vehicles by wireless channel by telemetry decoder, then by telemetering
Decoding data is sent to self -support intranet data server by data decoder, then generating Support by data server need to
It asks or the specific information such as diagnostic test reason or Test Suggestion is transmitted to corresponding human-computer interaction terminal, information exchange uses 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 process of main guarantee, to realize that retrospect product is each in life cycle management
Category information.State of the art code uses layered coding format, and hierarchical coding is suitable to arrange by the subordinate of object of classification, hierarchical relationship
Code is divided into several levels when a kind of code of sequence, coding, 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 a upper level coding.
Layer code digital representation, every layer digital correspond respectively to a unit in layered structure, constitute 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 since 00, arrange by ascending order, and 99 can mostly be worked out by doing.
Three bit digitals represent the coding of a level since 000, arrange by ascending order, and 999 can mostly be worked out by doing.
As shown in Fig. 2, the technology of the present invention status code is by type identifier code, Primary layer subcategory number, installation code, extension code name code structure
At.Other than type identifier code is indicated with letter, other codes are made of number.
Wherein:
Type identifier code, for indicating vehicle model, such as: SD；
Primary layer subcategory number is divided into three layers, respectively indicates the affiliated subsystem of vehicle, subsystem or single machine, can be to repetition
It is encoded using product facilities all on vehicle, coding refinement to field changeable single machine (LRU).Wherein:
1st layer is indicated with double figures, is encoded to product primary structure, and each subsystem is corresponded to.
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 subsystem | 71 | Power subsystem |
2nd layer is indicated with double figures, is finely divided to a certain structural system according to the 1st layer of feature, is under the jurisdiction of the 1st layer,
Corresponding to each subsystem.System generally presses Function Decomposition, and structure is generally pressed assembly membership and decomposed.
3rd layer is indicated with two digits, is finely divided again to upper one layer of structure according to membership, is corresponded to single machine and is produced
Product.
The basic level of more levels can also be distributed by concrete condition according to above-mentioned rule.
Installation code indicates whether install at present, " 999 " indicate installation for indicating vehicle installation state；
Code name code is extended, is indicated with using two-part, accounts for 3, first is state of the art baseline, the technology shape from left to right
State baseline information refers to the functional characteristic and object reached specified in the state of the art file and in product (hardware, software)
The status information for managing characteristic, for example, the states such as first sample, sample or software and hardware release status.Number from 1 to 9；Two are frame afterwards
Secondary number, indicate first ride, second of flight ..., the information such as n-th flight, number from 01 to 99.
The Reusable Launch Vehicles state of the art code runs through the information carrier of the entire life cycle of Reusable Launch Vehicles, layer
It is secondary it is clear, scalability is strong.
State of the art code is used as product identification to be attached in product facility or product facility encapsulation simultaneously.It is each on aircraft
The state of the art code of product facility is all made of the corresponded manner of " one yard of an object ", and every product (LRU) all has independent technology
Status code.By unique state of the art code, various information of the product in life cycle management can be totally traced, and in the full longevity
Life period interior coding is not altered, and does not recycle use, main part is not distinguished with spare part number.
State of the art code generallys use packing, is listed, puts up the modes such as label, spray painting, stickup, laser inscription and be attached to pair
On the product answered, for encode with interrelational form in kind, according to different product design feature and the characteristics of, can be divided into following several
Kind mode:
A) coding is pasted on work certificate；
B) product of less demanding to shape is beaten coding in product surface by laser marking machine in kind；
C) mode stored for the product of small volume, selection with packaging bag, coding is pasted onto packaging bag, or benefit
With marking pen etc., manual identification is carried out on product；
D) accurate product biggish for volume can neither cannot pack storage in product surface stamp, may be selected
Coding is beaten on nameplate with marking machine, is hung on product.
Reusable Launch Vehicles fault observation matrix is as shown in the table:
In table:
Ti, i are positive integer, and i >=1 indicates i-th of Sensor；
FMi, i are positive integer, and i >=1 indicates i-th of failure mode；
" 1 " indicates the failure in the failure and lateral position of some Sensor in its corresponding lengthwise position in table
Mode is related.Such as: event is reported by Sensor T1, when state is " 1 ", it can be seen that failure mode FM1/FM2 failure, by sensing
Device measuring point T2 report event, when state is " 1 ", it can be seen that failure mode FM2/FM3/FM4 failure etc..
According to the fault observation matrix, specific failure cause can be specified, and corresponding maintenance is provided according to fault level
The requirements of support can not such as position specific failure cause, form ambiguity group reason, and provide the information such as further Test Suggestion.
Fault observation matrix is established in the following manner:
(1), according to the functional performance of each subsystem of Control System for Reusable Launch Vehicle, the starting point and terminating point of signal are determined,
In conjunction with sensor test point position, the multi-signal flow graph model that each subsystem product signal is propagated is constructed；
(2), it is moved towards according to the signal in each subsystem multi-signal flow graph model, determines the failure cause and effect of system product equipment
The dependence of relationship and sensor test point and product facility failure；
(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 establishes fault observation matrix.
By taking power subsystem as an example, battery is responsible for power-supply controller of electric power supply, and sensor is arranged in power-supply controller of electric and surveys
Point T1 monitors secondary power supply voltage, which is the power supply of power controller controls plate, then multi-signal flow graph model is by electricity
Pond output primary voltage -> be input to power-supply controller of electric -> power-supply controller of electric voltage transformation -> is converted to the secondary electricity of power-supply controller of electric
Pressure -> sensor T1 monitoring.Sensor T1 test point may be power-supply controller of electric secondary power supply electric voltage exception (FM2) extremely, can also
It can be that battery output primary voltage is abnormal (FM1), therefore, T1 and the set of FM2 point of intersection in fault observation matrix, T1 and FM1 are handed over
Point also locates set, establishes fault observation matrix with this.
After product is delivered, 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 are defaulted as " non-installation " state；It is more when selecting to number with same code name, difference
One in platform (set) product for executing task assembly when, firstly, the installation code in update method status code is " installation " shape
State；Then, by encoding follower export technique status code, which is attached on product；Then, it executes and appoints
Business, and a series of test datas that repeatable vehicle carries out is bound with the state of the art code, that is, with the product into
Row binding；After Reusable Launch Vehicles execution task, when executing ground self -support and maintenance, product is dismantled, is led to
The current state of the art code that code reader identifies the product is crossed, the installation code in update method status code is " non-installation " state,
" task execution number " is updated simultaneously until passing through coding follower export technique state in the resume information of database server
Code, which is attached on product, then turns internal field by outfield and ensure maintenance and to record.
Self -support system, which is used to send, turns the Support demand in internal field by outfield and specific diagnostic test reason etc. is believed
Breath is to remote human-machine's interaction platform, detailed process are as follows: when product needs are further tested, repaired or are maintained, first by
Database server recognizes Product Status degradation or abnormal, and database server can not provide degradation or abnormal former after diagnosing
Cause, or the demand for needing repairing or maintaining can be provided, then demand item list is generated by database server side, through outer field technology
It is sent to relevant remote human-machine's interaction platform after personnel's confirmation is errorless, is analyzed by remote human-machine's interaction platform, and make
Determine Support planning, by feeding back field data library server end, assists outfield technical staff decision, the demand item list
Including the information such as Product Status degradation or abnormal tentative diagnosis result, further testing requirement, personnel, funds, period.
The present invention can realize vehicle life cycle management digital management using hierarchical coding, since aerocraft system forms
Complicated and have 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, to be that relationship aircraft can be reused 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 common sense 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 defeated including code reader, data server, coding
Device, telemetry decoder and multiple man-machine interactive platforms out, in which:
Code reader, the state of the art code on scanning recognition Control System for Reusable Launch Vehicle on each product facility, and be sent to
To data server, the state of the art code includes model, system membership, installation state, state of the art baseline, flight frame
Secondary information；
Follower is encoded, the state of the art code for each product facility of Control System for Reusable Launch Vehicle that data server is sent is received, and
Printout；
Data server records in real time and shows the resume information of each product facility of Control System for Reusable Launch Vehicle life cycle management,
The resume information includes essential information, state of the art code and the test number of all product facilities of Control System for Reusable Launch Vehicle
According to；The state of the art code that code reader is sent is received, corresponding equipment resume information is matched according to the state of the art code, and in real time more
New technology status code and equipment resume information；According to instruction is manually entered, Control System for Reusable Launch Vehicle is exported to coding follower
The state of the art code of appointed product equipment；The telemetry for receiving and saving the transmission of telemetry decoder, parses it,
Telemetry parameter is obtained, it is whether abnormal according to telemetering number parameter, fault sensor test point is determined, later, according to fault sensor
Test point and fault observation matrix are inferred to malfunction and failure mode, further according to malfunction and failure mode, index the failure of storage inside
Failure mode table corresponding with product facility generates Support demand item list, is sent to malfunction and failure mode related products
Equipment man-machine interactive platform；
Telemetry decoder receives Control System for Reusable Launch Vehicle downlink wireless telemetry signal, and demodulation obtains telemetry, sends
To data server；
Man-machine interactive platform receives Support demand item list, by artificial according to Support demand item list, makes in time
Support planning.
2. a kind of Control System for Reusable Launch Vehicle self -support system according to claim 1, it is characterised in that: the technology
Status code uses layered coding format, is made of type identifier code, Primary layer subcategory number, installation code, extension code name code, in which:
Type identifier code, for indicating vehicle model；
Primary layer subcategory number includes 1~N layer code, for indicating the affiliated subsystem of vehicle, subsystem or single machine；Same layer
It is coordination between secondary coding, does not intersect, do not repeat；It is membership between next bit level and a upper level coding；
Installation code, for indicating that vehicle is in " installation " state or " non-installation " state；
Code name code is extended, for indicating vehicle operating 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
Status 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 status code is " non-installation " state, when selecting any product facility to carry out vehicle assembly, firstly,
Updating the installation code in data server in state of the art code is " installation " state；Then, by encoding follower export technique
The state of the art code is attached on product by status code；When ground test or execution task, by the state of the art code and repeat
The test data that vehicle carries out is bound, the keyword as retrieval and inquisition test data；Ground test executes task
Afterwards, when dismantling to product, the current state of the art code of the product is identified by code reader, again update method status code
In installation code be " non-installation " state, by encode follower export technique status code, which is attached to production
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 failure
Observing matrix is as shown in the table:
In table:
Ti, i are positive integer, and i >=1 indicates i-th of Sensor；
FMi, i are positive integer, and i >=1 indicates i-th of failure mode；
" 1 " indicates that some Sensor in its corresponding lengthwise position breaks down and the failure mould on lateral position in table
Formula is related.
6. a kind of Control System for Reusable Launch Vehicle self -support system according to claim 5, it is characterised in that: the failure
Observing matrix is established in the following manner:
(1), according to the functional performance of each subsystem of Control System for Reusable Launch Vehicle, the starting point and terminating point of signal are determined, in conjunction with
Sensor test point position constructs the multi-signal flow graph model that each subsystem product signal is propagated；
(2), it is moved towards according to the signal in each subsystem multi-signal flow graph model, determines the Failure causality of system product equipment
With the dependence of sensor test point and product facility failure；
(3), the equipment that flows through of signal of sensor test point test, as index by the failure mode and test of product facility
Point is associated, and establishes 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
Server, telemetry decoder pass through Ethernet exchanging data information between multiple man-machine interactive platforms.
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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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