CN106292637B - A kind of airborne collision avoidance system centralized maintenance system and maintaining method - Google Patents
A kind of airborne collision avoidance system centralized maintenance system and maintaining method Download PDFInfo
- Publication number
- CN106292637B CN106292637B CN201610771374.2A CN201610771374A CN106292637B CN 106292637 B CN106292637 B CN 106292637B CN 201610771374 A CN201610771374 A CN 201610771374A CN 106292637 B CN106292637 B CN 106292637B
- Authority
- CN
- China
- Prior art keywords
- self
- task
- test
- collision avoidance
- airborne collision
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0208—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterized by the configuration of the monitoring system
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Debugging And Monitoring (AREA)
Abstract
The present invention provides a kind of airborne collision avoidance system centralized maintenance system and maintaining method, centralized maintenance system contains following subsystem, power self test subsystem, Mission Monitor subsystem, Integrated Self subsystem, starting self-test subsystem and extension self-test subsystem.Integrated Self subsystem collects the faulty raw information of institute of other subsystems of airborne collision avoidance system reported, and synthesis is handled, then stores processing result and be reported to integrated avionic system.Integrated avionic system can obtain the airborne collision avoidance systems relevant informations such as self-detection result by starting self-test subsystem；Mission Monitor subsystem monitors each task status of airborne collision avoidance system in real time, realizes that real time monitoring is restored online and generates monitoring log；Self-test subsystem is extended, airborne collision avoidance system can be made to realize human-computer interaction, LRU grades of self-detection results are shown by its indicator light.
Description
Technical field
The present invention relates to a kind of airborne collision avoidance system centralized maintenance system and maintaining methods, are suitable for more particularly to one kind
Airborne collision avoidance system centralized maintenance system and maintaining method based on TCASII synthesization airborne collision avoidance system.
Background technique
TCASII is a synthesization airborne collision avoidance system, is mainly used for providing air security separation assurance for aircraft, reach
To the purpose of anticollision.By inquiry, reception, the recall signal for handling other aircraft answering machines, to other aircrafts of surrounding into
Row monitoring, and calculate other aircrafts in monitoring range and provide traffic alert with respect to the flight trend of the machine and resolution alarm is suggested.
There are many function of TCASII airborne collision avoidance system itself, and system composition and its complexity are received comprising airborne collision avoidance equipment
Host, S mode answering machine, antenna change-over switch are sent out, directional aerial, omnidirectional antenna and mating high frequency low frequency cable etc. are a series of
Hardware device, wherein also including various software and hardware systems, problem occurs for any one position all will be airborne to TCASII
Anti-collision system causes to influence in various degree, and these influences possibly are present at the intermittent fault or hard event of various complex conditions
Barrier, after device fails, how quickly positioning and shortening maintenance time is to directly affect TCASII airborne collision avoidance system
User uses.
Current TCASII airborne collision avoidance system for itself monitoring project is few and not system, can not quickly, it is accurately fixed
Position failure lacks complete, system TCASII airborne collision avoidance system hardware detection technical solution and software detection technical solution,
Lack starting self-test and schemes for configuration and management, is unable to satisfy modern integrated avionic system requirement.
Summary of the invention
The technical problem to be solved in the present invention is to provide one kind systematically to carry out hardware detection to airborne collision avoidance system
And software detection, record fault log, realize quickly and accurately the airborne collision avoidance system centralized maintenance system of positioning failure and
Maintaining method.
The technical solution adopted by the invention is as follows: a kind of airborne collision avoidance system centralized maintenance system；Include:
Power self test subsystem, including,
Power state information detection module detects the power state information of airborne collision avoidance system；
Power state information summarizing module summarizes the power state information of airborne collision avoidance system；
Power failure information is recorded and is reported to Integrated Self subsystem by fault information reporting module；
Integrated Self subsystem, including,
Fault information collection module, is periodically detected airborne collision avoidance system, and that collects that other self-test subsystems provide is all
Failure raw information；
Fault message contrast module, to the front and back of the corresponding subsystem of collection, fault data is compared twice；
Fault message changes logging modle, according to comparing result, when fault message changes, records failure variation
Information is simultaneously reported to integrated avionic system.
The power self test subsystem includes power self test circuit and power-switching circuit, to the power supply of airborne collision avoidance system
Voltage status information and/or current state information are detected, and realize the power self test function of airborne collision avoidance system.
Mishap Database of the Integrated Self subsystem according to design, cycle monitoring TCASII airborne collision avoidance system are collected
The faulty raw information of institute that other self-test submodules of TCASII airborne collision avoidance system provide, carries out faulted-phase judgment, when
When fault message changes, failure change information is sent to fault logging module, while reporting integrated avionic system.
The centralized maintenance system further includes Mission Monitor subsystem, including,
Task abnormity processing module carries out abnormality processing to the task of operation exception；
Task abnormity logging modle records the exception information of the task of operation exception.
The Mission Monitor subsystem, the task run situation of real-time monitoring airborne collision avoidance system are airborne to TCASII anti-
It hits that system is in abnormality or the task of miss status is restored online, while logger task abnormal time, it is different to generate task
Often record, be stored in TCASII airborne collision avoidance system, in order to carry out TCASII airborne collision avoidance system malfunction elimination and
Maintenance improves TCASII airborne collision avoidance system reliability, increases the means of TCASII airborne collision avoidance system malfunction elimination and maintenance.
Meanwhile using software watchdog mechanism that watchdog module is set for Mission Monitor subsystem itself, guarantee Mission Monitor subsystem
The normal operation of system monitor task.
The centralized maintenance system further includes extension self-test subsystem, including extends self-test trigger module, indicator light and refer to
Show lamp control module；
The extension self-test trigger module is extended certainly for sending extension self-test signal, triggering airborne collision avoidance system
Inspection；The indicator light is used to indicate airborne collision avoidance system relevant device current state；The instruction lamp control module is used for basis
Testing result control to the corresponding indicator light of airborne collision avoidance system and lights or extinguish.
Equipment is in the state of ground, i.e. wheel load and undercarriage signal is located at ground, and instruction TCASII airborne collision avoidance system can
To be extended self-test, the extension self-checking function of airborne collision avoidance system is triggered, it is intuitive to show that TCASII airborne collision avoidance system is current
The function of equipment state intuitively can quickly position general type fault, navigate to LRU rank.
The centralized maintenance system further includes starting self-test subsystem, including,
Starting self-test command module is received, the starting self-test order issued is received；
Test condition judgment module, judges whether current airborne collision avoidance system has starting self-test condition；
Self-detection result is sent integrated avionic system by self-detection result sending module.
Start self-test subsystem, starting self-test order is issued by external or integrated avionic system, is carried out when time TCASII machine
Anti-collision system self-test is carried, and obtains self-detection result, self-detection result is returned into integrated avionic system.
Based on the maintaining method of above-mentioned airborne collision avoidance system centralized maintenance system, method particularly includes: to airborne collision avoidance system
Each power supply power state information carry out periodically self-test one by one, be compared, determine each with given qualified threshold value
Whether the power state information of power supply correct, after having detected one by one, if there is there are failures for power supply, then record fault message and on
Report power module failure gives Integrated Self subsystem；Integrated Self subsystem collects other self-test subsystems of airborne collision avoidance system
The faulty raw information of institute reported, compares with failure raw information corresponding in Mishap Database, works as fault message
After changing, failure change information is stored and is reported to integrated avionic system.
The maintaining method further includes Mission Monitor maintaining method, and monitor task reads all TCASII airborne collision avoidance systems
Task status carries out task status monitoring, detects whether that there are task abnormity or tasks to lack, if there is task abnormity or
Person's task missing, monitor task suppressing exception task or re-creates missing task, and for abnormal task, initialization exception is appointed
The involved system variable of business re-creates the task, logger task abnormal time and task abnormity or task missing
Event is to Mission Monitor log.For the monitoring of monitor task itself, design software watchdog module monitors the monitor task,
Detect whether that perhaps task missing is lacked if there is task abnormity or task there are task abnormity, suppressing exception task or
Person re-creates missing task, for abnormal task, also to re-create the task, logger task abnormal time and task are different
Often or task deletion events are to Mission Monitor log.
The maintaining method further includes extension self checking method, method particularly includes: under conditions of having extension self-test, triggering
The extension self-checking function of airborne collision avoidance system；Indicate that lamp control module carries out control point to corresponding indicator light according to testing result
Bright or extinguishing indicates airborne collision avoidance system relevant device current state, intuitive display airborne collision avoidance system current device state
Function.
The maintaining method further includes starting self checking method, method particularly includes: airborne collision avoidance system receives vacant lot mode
Order, and vacant lot mode is " ground ", avionics system issues starting self-test and starts test command, if airborne collision avoidance system does not have
Standby test condition, returns to " test is forbidden " response message, sends " test stops " order；If the vacant lot mode received is
" aerial ", while the starting self-test order that avionics system issues is received, " test is forbidden " response message is returned, " test is sent
Stop " order；Otherwise, " testing in carrying out " response message is sent to integrated avionics, and starts starting test；It is airborne anti-
The system of hitting starts to start self-checking, and operation Integrated Self is tested, and obtains test result, and test result returned to comprehensive
Combination avionics system, returned content are " test passes through " or " test failure " to indicate TCASII airborne collision avoidance system work shape
State is normal or order " is tested and stopped " in failure, transmission.
Compared with prior art, the beneficial effects of the present invention are: hardware inspection systematically can be carried out to airborne collision avoidance system
It surveys and software detection, record fault log realizes quickly and accurately positioning failure.
Detailed description of the invention
Fig. 1 is the method flow diagram of the wherein power self test method of a specific embodiment of the invention.
Fig. 2 is the technical solution figure of the wherein power self test method of a specific embodiment of the invention.
Fig. 3 is the technical solution figure of the extension self checking method of a wherein specific embodiment of the invention.
Fig. 4 is the method flow diagram of the extension self checking method of a wherein specific embodiment of the invention.
Fig. 5 is the conceptual scheme of the wherein Mission Monitor method of a specific embodiment of the invention.
Fig. 6 is the method flow diagram of the wherein Mission Monitor method of a specific embodiment of the invention.
Fig. 7 is the scheme journey figure of the starting self checking method of a wherein specific embodiment of the invention.
Fig. 8 is the method flow diagram of the starting self checking method of a wherein specific embodiment of the invention.
Fig. 9 is the conceptual scheme of the wherein Integrated Self method of a specific embodiment of the invention.
Figure 10 is the method flow diagram of the wherein Integrated Self method of a specific embodiment of the invention.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to embodiments, to the present invention
It is further elaborated.It should be appreciated that described herein, specific examples are only used to explain the present invention, is not used to limit
The fixed present invention.
Any feature disclosed in this specification (including abstract) unless specifically stated can or tool equivalent by other
There are the alternative features of similar purpose to be replaced.That is, unless specifically stated, each feature is a series of equivalent or similar characteristics
In an example.
Specific embodiment 1
In this embodiment, for power self test subsystem, power self test circuit and power-switching circuit are devised,
The power self test acquisition module of TCASII airborne collision avoidance system is made of FPGA and A/D sample circuit etc., self-test acquisition module is adopted
Collection self-inspection data is reported to TCASII airborne collision avoidance system, TCASII airborne collision avoidance system according to determining power self test threshold value into
Row power module self-test.Its specific implementation flow are as follows:
Power self test subsystem carries out power module self-test using period self test mode, detects power module one by one every time
Supply voltage obtains the voltage value being transformed into fixed range through overvoltage value from power self test acquisition module, detects voltage value
Whether correct, the multiple reading for single supply voltage using the threshold value according to design at least twice is filtered simultaneously, obtains
To accurate data value；The accurate voltage value that will acquire is compared with given qualified threshold value, determines that the road supplies
Whether piezoelectric voltage is correct, and corresponding flag bit is arranged, until all power detectings finish；Fail result is reported into synthesis certainly
Fault message is recorded in fault logging module if there are failures for power module for inspection subsystem, for subsequent to failure
Quickly positioning uses.
In addition, when read power self test data difference it is huge when and for it is of short duration occur when, carried out using latest result
Power self test determines, is more than given threshold if there is frequency, then reports power module failure.
Design error failure database, Integrated Self subsystem, according to the Mishap Database of design, cycle monitoring TCASII is airborne
It is former to collect all self test failures that other self-test subsystems of TCASII airborne collision avoidance system provide for all self-test information of anti-collision system
Beginning information carries out self-test information processing, when failure changes, will be stored in failure logging mould after failure change information coding
Block, while integrated avionic system is reported after failure is recompiled.In this embodiment, airborne for the TCASII of collection
All self-test information of anti-collision system, carry out classification judgement respectively, obtain this Mishap Database as a result, and by the note of previous cycle
The Mishap Database result of record is compared with this monitoring Mishap Database；By being compared with previous Mishap Database, when event
Barrier changes, and TCASII airborne collision avoidance system fault logging module is recorded in TCASII airborne collision avoidance system fault message,
Simultaneously integrated avionic system will be reported after TCASII airborne collision avoidance system fault message and sorted major class fault message coding.
By the way that with after previous Mishap Database comparison processing, this Mishap Database is covered historical failure data library.
In addition, Integrated Self subsystem will collect TCASII airborne collision avoidance system this period fault information data in this period
Library is compared with upper period Mishap Database, records comparison result, and Mishap Database progress failure modes are obtained major class
Failure (LRU rank) is as a result, and save result；The Mishap Database that Integrated Self module obtains this period, and therefore
Hinder information major class fail result, according to situation of change, carries out fail result and report, by fail result according to the failure format of regulation
Report boat integrated avionic system；Fault logging module is recorded in fail result simultaneously.
Specific embodiment 2
On the basis of specific embodiment 1, monitor task reads all TCASII airborne collision avoidance system task statuses, carries out
Task status monitoring detects whether that perhaps task missing is supervised if there is task abnormity or task missing there are task abnormity
Control task suppressing exception task re-creates missing task, for abnormal task, involved by initialization exception task
System variable re-creates the task, logger task abnormal time and task abnormity or task deletion events and supervises to task
Control log.For the monitoring of monitor task itself, design software house dog monitors the monitor task, detects whether that there are tasks
Perhaps if there is task abnormity, perhaps task lacks suppressing exception task or re-creates missing times task missing exception
Business will also re-create the task, logger task abnormal time and task abnormity or task missing thing for abnormal task
Part is to Mission Monitor log.
If task abnormity or task lack continuous 3 times be initialised after there are still task abnormities or task to lack,
Delete the monitored task, re-create monitored task, and by the logout to Mission Monitor log.
After if monitored task continuous 3 times are deleted and re-create, if cannot still eliminate task abnormity or task
Missing, then be recorded Mission Monitor log for whole process.
Specific embodiment 3
On the basis of specific embodiment 1 or 2, which is mainly used for ground check use, cannot use in the air.Equipment
In the state of ground, i.e. wheel load and undercarriage signal is located at ground, and instruction TCASII airborne collision avoidance system can be extended certainly
Inspection presses self-test button before TCASII airborne collision avoidance system in this embodiment, kept for down state 2 seconds or more, touching
It sends out TCASII airborne collision avoidance system and extends self-checking function.
In this embodiment, self-checking module detection wheel information carrying number, undercarriage signal and front panel are extended certainly
Button signal is examined, if condition has, i.e., wheel load, undercarriage signal are on ground, and front panel self-test button is in down state
When TCASII airborne collision avoidance system S mode answering machine or transmitting-receiving host, have respectively entered respective extension self-test state machine,
In extension self-test state machine operational process, provides all light front panel instruction modulating signal first, detection is provided after for 3 seconds
As a result, only lighting self-detection result indicator light, after self-test button restores normal, self-detection result indicator light extinguishes after 3 seconds.It is no
Self-detection result indicator light is then indicated always, and after self-test button restores normal, self-detection result indicator light extinguishes after 3 seconds.It is logical
Pressing TCASII airborne collision avoidance system S mode answering machine and ACAS transmitting-receiving host front panel self-test button are crossed, it is intuitive to show
The function of TCASII airborne collision avoidance system current device state, intuitively can quickly position general type fault, navigate to LRU grades
Not.
In this embodiment, as follows in TCASII airborne collision avoidance system S mode answering machine front panel design: front panel
It is made of indicator light and self-test button, indicator light respectively " normal " indicator light, " failure " indicator light, " control " indicator light,
" upper antenna " indicator light, " lower antenna " indicator light, " height " indicator light；TCASII airborne collision avoidance system transmitting-receiving host front panel is set
Count as follows: front panel is made of indicator light and self-test button, indicator light respectively " normal " indicator light, " failure " indicator light,
" upper antenna " indicator light, " lower antenna " indicator light, " answering machine bus " indicator light.
In this embodiment, design TCASII airborne collision avoidance system indicates lamp control module, is realized with FPGA device,
The switch of control instructions lamp reads self-test button input signal, according to the self-detection result that TCASII airborne collision avoidance system provides, divides
Class control instructions lamp.
Extension selftest module and the indicator light control of TCASII airborne collision avoidance system in TCASII airborne collision avoidance system CPU module
Molding block is communicated, and after TCASII airborne collision avoidance system self-detection result is carried out precise classification, is believed with the indicator light of smallest number
Number more situation of instruction, quickly positions the fault direction and interface data deletion condition of LRU rank.
In this embodiment, indicator light logical relation is as follows:
TCASII airborne collision avoidance system S mode answering machine and ACAS transmitting-receiving host bus failure or the event of S mode answering machine
Barrier then light by indicator light " answering machine bus ", represents answering machine bus failure；
TCASII airborne collision avoidance system ACAS receives and dispatches host itself normally, then " normal " lamp that ACAS receives and dispatches host is lighted,
Otherwise it does not light；
TCASII airborne collision avoidance system ACAS receives and dispatches host internal fault, then " failure " lamp that ACAS receives and dispatches host is lighted,
Otherwise it does not light；
Directional aerial failure in TCASII airborne collision avoidance system, then " upper antenna " lamp that ACAS receives and dispatches host are lighted, otherwise
It does not light；
Directional aerial failure under TCASII airborne collision avoidance system, then " lower antenna " lamp that ACAS receives and dispatches host are lighted, otherwise
It does not light；
TCASII airborne collision avoidance system S mode answering machine faults itself, then " failure " lamp of S mode answering machine is lighted, no
It does not light then；
TCASII airborne collision avoidance system S mode answering machine itself is normal, then " normal " lamp of S mode answering machine is lighted, no
It does not light then；
TCASII airborne collision avoidance system does not receive control data, then " control " lamp of S mode answering machine is lighted, otherwise not point
It is bright；
TCASII airborne collision avoidance system does not receive height evidence, then " height " lamp of S mode answering machine is lighted, otherwise not point
It is bright；
Omnidirectional antenna failure in TCASII airborne collision avoidance system, then " upper antenna " lamp of S mode answering machine is lighted, otherwise not
It lights；
Omnidirectional antenna failure under TCASII airborne collision avoidance system, then " lower antenna " lamp of S mode answering machine is lighted, otherwise not
It lights；
According to the above design, it can analyze TCASII airborne collision avoidance system ACAS transmitting-receiving host and S mode answering machine be grouped
The LRU rank for navigating to failure part is isolated to analyze in situation, combination control.
Specific embodiment 4
TCASII airborne collision avoidance system receives vacant lot mode order, and vacant lot mode is " ground ", and avionics system issues
Starting self-test starts test command, if TCASII airborne collision avoidance system does not have test condition, returns to " test is forbidden " response
Information sends " test stops " order；If the vacant lot mode received is " aerial ", while receiving what avionics system issued
Start self-test order, return to " test is forbidden " response message, sends " test stops " order；Otherwise, it sends " in test progress "
Response message starts starting test to integrated avionics；TCASII airborne collision avoidance system starts to start self-checking, fortune
Row Integrated Self is tested, and obtains test result, and test result is returned to integrated avionics, returned content is
" test passes through " or " test failure " indicates that TCASII airborne collision avoidance system working condition is normal or failure, sends and " survey
Examination stops " order.
In addition, if receiving integrated avionics before returning to test result to integrated avionics and issuing
" starting self-checking stop " order；If instructed in the vacant lot mode for not receiving integrated avionics transmission, return
" test is forbidden " response message.
Claims (6)
1. a kind of airborne collision avoidance system centralized maintenance system, comprising:
Power self test subsystem, including,
Power state information detection module detects the power state information of airborne collision avoidance system；
Power state information summarizing module summarizes the power state information of airborne collision avoidance system；
Power failure information is recorded and is reported to Integrated Self subsystem by fault information reporting module；
Integrated Self subsystem, including,
Fault information collection module, is periodically detected airborne collision avoidance system, and it is faulty to collect the institute that other self-test subsystems provide
Raw information；
Fault message contrast module, to the front and back of the corresponding subsystem of collection, fault data is compared twice；
Fault message changes logging modle and, when fault message changes, records the failure change information according to comparing result
And it is reported to integrated avionic system；
It further include Mission Monitor subsystem, including,
Task abnormity processing module carries out abnormality processing to the task of operation exception；
Task abnormity logging modle records the exception information of the task of operation exception；
Monitor task reads all airborne collision avoidance system task statuses, carries out task status monitoring, it is different to detect whether that there are tasks
Often perhaps if there is task abnormity, perhaps task lacks monitor task suppressing exception task or re-creates task missing
Missing task, for abnormal task, system variable involved by initialization exception task re-creates the task, and record is appointed
Abnormal time and task abnormity or task deletion events be engaged in Mission Monitor log.
2. centralized maintenance system according to claim 1, the centralized maintenance system further includes extension self-test subsystem, packet
Include extension self-test trigger module, indicator light and instruction lamp control module；
The extension self-test trigger module is extended self-test for sending extension self-test signal, triggering airborne collision avoidance system；Institute
It states indicator light and is used to indicate airborne collision avoidance system relevant device current state；The instruction lamp control module is used to be tied according to detection
Fruit control to corresponding indicator light and lights or extinguish.
3. centralized maintenance system according to claim 1, the centralized maintenance system further includes starting self-test subsystem, packet
It includes,
Starting self-test command module is received, the starting self-test order issued is received；
Test condition judgment module, judges whether current airborne collision avoidance system has starting self-test condition；
Self-detection result is sent integrated avionic system by self-detection result sending module.
4. based on the maintaining method of airborne collision avoidance system centralized maintenance system described in one of claims 1 to 3, specific method
Are as follows: periodically self-test one by one is carried out to the power state information of each power supply of airborne collision avoidance system, with given qualified threshold value
It is compared, determines whether the power state information of each power supply is correct, after having detected one by one, if there is power supply is there are failure,
It then records fault message and power module failure is reported to give Integrated Self subsystem；Integrated Self subsystem collects airborne collision avoidance system
Unite the faulty raw information of institute reported of other self-test subsystems, with failure raw information corresponding in Mishap Database into
Row comparison, after fault message changes, failure change information is stored and is reported to integrated avionic system；
The maintaining method further includes Mission Monitor maintaining method, and monitor task reads all airborne collision avoidance system task statuses,
Task status monitoring is carried out, detects whether that perhaps task missing is scarce if there is task abnormity or task there are task abnormity
It loses, monitor task suppressing exception task or re-creates missing task, for abnormal task, involved by initialization exception task
The system variable arrived, re-creates the task, logger task abnormal time and task abnormity or task deletion events are taken office
Business monitoring log.
5. maintaining method according to claim 4, the maintaining method further includes extension self checking method, method particularly includes:
Under conditions of having extension self-test, the extension self-checking function of airborne collision avoidance system is triggered；The control of airborne collision avoidance system indicator light
Module control to corresponding indicator light and lights or extinguish according to testing result, and instruction airborne collision avoidance system relevant device is current
State, the intuitive function of showing airborne collision avoidance system current device state.
6. maintaining method according to claim 4, the maintaining method further includes starting self checking method, method particularly includes:
Airborne collision avoidance system receives vacant lot mode order, and vacant lot mode is " ground ", and avionics system issues starting self-test and starts to survey
Examination order returns to " test is forbidden " response message if airborne collision avoidance system does not have test condition, sends " test stops " life
It enables；If the vacant lot mode received is " aerial ", while receiving the starting self-test order that avionics system issues, returns and " survey
Examination is forbidden " response message, send " test stops " order；Otherwise, " testing in carrying out " response message is sent to integrated avionics
System, and start starting test；Airborne collision avoidance system starts to start self-checking, and operation Integrated Self is tested, surveyed
Test result, and test result is returned into integrated avionics, returned content comes for " test passes through " or " test failure "
Indicate that TCASII airborne collision avoidance system working condition is normal or order " is tested and stopped " in failure, transmission.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610771374.2A CN106292637B (en) | 2016-08-31 | 2016-08-31 | A kind of airborne collision avoidance system centralized maintenance system and maintaining method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610771374.2A CN106292637B (en) | 2016-08-31 | 2016-08-31 | A kind of airborne collision avoidance system centralized maintenance system and maintaining method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106292637A CN106292637A (en) | 2017-01-04 |
| CN106292637B true CN106292637B (en) | 2019-02-12 |
Family
ID=57674421
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610771374.2A Active CN106292637B (en) | 2016-08-31 | 2016-08-31 | A kind of airborne collision avoidance system centralized maintenance system and maintaining method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106292637B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113242437A (en) * | 2021-04-01 | 2021-08-10 | 联通(广东)产业互联网有限公司 | RTSP (real time streaming protocol) video plug-in-free playing method, system, device and storage medium |
| CN114180096B (en) * | 2021-11-15 | 2024-05-07 | 中国航空工业集团公司沈阳飞机设计研究所 | Maintenance and detection method for airborne products |
| CN115131994B (en) * | 2022-06-29 | 2023-08-18 | 四川九洲空管科技有限责任公司 | H-ACAS target monitoring capacity and overload capacity test method and system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102062822A (en) * | 2009-11-16 | 2011-05-18 | 西安费斯达自动化工程有限公司 | Fault diagnosis method of integrated traffic collision avoidance system (TCAS) |
| CN103019908A (en) * | 2012-12-07 | 2013-04-03 | 陕西千山航空电子有限责任公司 | Vxworks multi-task monitoring technological method based on multiple buses |
| CN105070107A (en) * | 2015-07-16 | 2015-11-18 | 四川九洲空管科技有限责任公司 | Airborne collision avoidance system, ACAS transmit-receive host digital signal loop self-detection system and method |
| CN105527506A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Intelligent fault message detection system and transmission method thereof |
-
2016
- 2016-08-31 CN CN201610771374.2A patent/CN106292637B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102062822A (en) * | 2009-11-16 | 2011-05-18 | 西安费斯达自动化工程有限公司 | Fault diagnosis method of integrated traffic collision avoidance system (TCAS) |
| CN103019908A (en) * | 2012-12-07 | 2013-04-03 | 陕西千山航空电子有限责任公司 | Vxworks multi-task monitoring technological method based on multiple buses |
| CN105527506A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Intelligent fault message detection system and transmission method thereof |
| CN105070107A (en) * | 2015-07-16 | 2015-11-18 | 四川九洲空管科技有限责任公司 | Airborne collision avoidance system, ACAS transmit-receive host digital signal loop self-detection system and method |
Non-Patent Citations (1)
| Title |
|---|
| "TCAS故障诊断专家系统的设计与研究";李国胜;《中国硕士论文全文数据库工程科技II辑》;20111215;论文7-16页 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106292637A (en) | 2017-01-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102460516B (en) | Method and device for processing faults | |
| KR101856543B1 (en) | Failure prediction system based on artificial intelligence | |
| US10643187B2 (en) | Reporting and prioritizing faults for aircraft downtime reduction | |
| US8442702B2 (en) | Fault diagnosis device and method for optimizing maintenance measures in technical systems | |
| CN106292637B (en) | A kind of airborne collision avoidance system centralized maintenance system and maintaining method | |
| US8126597B2 (en) | Formulation of a preventive maintenance message relating to the functional degradations of an aircraft | |
| CN104346430B (en) | The method and storage medium of maintenance auxiliary for aircraft devices | |
| US20130274991A1 (en) | Method, devices and program for computer-aided analysis of the failure tolerance of an aircraft system, using critical event charts | |
| CN108454879B (en) | Airplane fault processing system and method and computer equipment | |
| CN106646030A (en) | Power grid fault diagnosis method and device based on multiple data sources and expert rule base | |
| US20080304418A1 (en) | Maintenance system for a set of equipment | |
| CN111611114A (en) | Integrated avionics PHM system | |
| CN108909773A (en) | A kind of signalling arrangement comprehensive analysis of fault system | |
| Wheeler et al. | A survey of health management user objectives related to diagnostic and prognostic metrics | |
| CN112151195B (en) | Method and device for checking potential safety hazards of power distribution equipment | |
| EP3462266B1 (en) | Aircraft maintenance message prediction | |
| KR20140045367A (en) | System for recommending helicopter engine maintenance | |
| US20100037099A1 (en) | Diagnostic method for locating a failure in a complex system, and a device for implementing said method | |
| US9891978B1 (en) | Fault detection in a multi-core safety-critical avionics system | |
| CN110737256B (en) | Method and device for controlling variable-frequency transmission system | |
| CN110018377A (en) | A kind of fault detection analysis system of ARINC664P7 terminal device | |
| JP6622040B2 (en) | Analysis system and analysis method | |
| KR20070057649A (en) | System for managing falut using the technology of satellite telemetering and its method | |
| CN102843246B (en) | Exchanging system tests appraisal procedure and device | |
| CN102062822B (en) | Fault diagnosis method of integrated traffic collision avoidance system (TCAS) |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |