CN112486140A - Flight control system fault reporting and inquiring method - Google Patents
Flight control system fault reporting and inquiring method Download PDFInfo
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- CN112486140A CN112486140A CN202011307739.9A CN202011307739A CN112486140A CN 112486140 A CN112486140 A CN 112486140A CN 202011307739 A CN202011307739 A CN 202011307739A CN 112486140 A CN112486140 A CN 112486140A
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- 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
- G05B23/0259—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterized by the response to fault detection
- G05B23/0267—Fault communication, e.g. human machine interface [HMI]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F16/00—Information retrieval; Database structures therefor; File system structures therefor
- G06F16/20—Information retrieval; Database structures therefor; File system structures therefor of structured data, e.g. relational data
- G06F16/22—Indexing; Data structures therefor; Storage structures
- G06F16/2228—Indexing structures
- G06F16/2246—Trees, e.g. B+trees
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F16/00—Information retrieval; Database structures therefor; File system structures therefor
- G06F16/20—Information retrieval; Database structures therefor; File system structures therefor of structured data, e.g. relational data
- G06F16/24—Querying
- G06F16/245—Query processing
- G06F16/2453—Query optimisation
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F16/00—Information retrieval; Database structures therefor; File system structures therefor
- G06F16/20—Information retrieval; Database structures therefor; File system structures therefor of structured data, e.g. relational data
- G06F16/24—Querying
- G06F16/245—Query processing
- G06F16/2455—Query execution
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- G—PHYSICS
- G11—INFORMATION STORAGE
- G11B—INFORMATION STORAGE BASED ON RELATIVE MOVEMENT BETWEEN RECORD CARRIER AND TRANSDUCER
- G11B20/00—Signal processing not specific to the method of recording or reproducing; Circuits therefor
- G11B20/10—Digital recording or reproducing
- G11B20/10009—Improvement or modification of read or write signals
- G11B20/10222—Improvement or modification of read or write signals clock-related aspects, e.g. phase or frequency adjustment or bit synchronisation
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Abstract
The invention belongs to the technical field of helicopter flight control systems, and relates to a flight control system fault declaration query method. The method comprises the following steps: the method comprises the following steps: a recorder is added in the flight control system for recording the faults of the flight control system; step two: the recorder is respectively connected with all subsystems in the flight control system through a bus; step three: a flight control computer in the flight control system sends system time to all other subsystems of the flight control system; step four: and all other subsystems of the flight control system send respective fault information to the recorder for recording according to the system time. The self computing capability of each component of the system is fully utilized, and the load of application software of a complex system is effectively reduced, so that the fault synthesis and fault declaration of the system components are not excessively undertaken; the fault tree graph is simply and conveniently drawn, the troubleshooting work efficiency is improved, and the troubleshooting work intensity is reduced.
Description
Technical Field
The invention belongs to the technical field of helicopter flight control systems, and relates to a flight control system fault declaration query method.
Background
Helicopter flight control systems exist in a number of components, typically including a flight control computer, a flight control console, an inertial measurement unit, and servo actuators … …. The intelligent circuits are arranged in the flight control computer, the flight control console and the inertia measurement unit, the fault of the intelligent circuits is detected on line through software running on a CPU of the intelligent circuits, fault information of the intelligent circuits is reported to flight control system application software in the flight control computer, and fault state of each component is subjected to fault synthesis through the application software, so that the function of the flight control system is influenced. In the whole process, the faults of the flight control system are processed by the application software of the flight control system running in the flight control computer and are recorded in the NVRAM with limited storage capacity or the flight parameter recorder.
In the subsequent fault inquiry process, the inquiry is made by reading a fault record in the NVRAM or a fault record in the flight parameter recorder.
With the use of new technology in the flight control system, the complexity of the system is improved, more and more fault monitoring points are provided for the system, the burden of system application software is greatly increased by the traditional fault reporting, recording and querying mode under the background, the inconvenience of the system application software is reflected in the fault querying process, and the fault querying is difficult to conveniently carry out.
Disclosure of Invention
The invention provides a flight control system fault declaration and query method which is used for guiding flight control system fault declaration, fault recording and fault query.
A flight control system fault declaration query method comprises the following steps:
the method comprises the following steps: a recorder is added in the flight control system for recording the faults of the flight control system;
step two: the recorder is respectively connected with all subsystems in the flight control system through a bus;
step three: a flight control computer in the flight control system sends system time to all other subsystems of the flight control system;
step four: and all other subsystems of the flight control system send respective fault information to the recorder for recording according to the system time.
Further, in the fourth step, all other subsystems of the flight control system send respective fault information and send the system time when the fault occurs to the recorder.
Further, the fourth step further includes: and all other subsystems of the flight control system also send respective signal availability to the flight control computer.
Further, the flight control computer comprehensively analyzes the signal availability of each subsystem to obtain system-level fault information.
Further, the flight control computer sends the system-level fault information to the recorder for recording, and simultaneously sends the system time when the system-level fault occurs to the recorder.
Further, the method further comprises the step of drawing the fault tree based on the system time by using the fault information recorded by the recorder.
Further, all subsystems of the flight control system include: the system comprises a flight control computer, a flight control console, an inertia measurement unit and a servo actuator.
Furthermore, the generation of the system time is carried out by depending on the running time of the flight control computer of the core component of the flight control system.
Has the advantages that: the invention fully utilizes the self computing power of each component of the system, and effectively reduces the burden of complex system application software, so that the fault synthesis and fault declaration of the system components are not excessively undertaken; the fault tree graph is simply and conveniently drawn, the troubleshooting work efficiency is improved, and the troubleshooting work intensity is reduced.
Drawings
FIG. 1 is a schematic view of a flight control system connection;
FIG. 2 is a schematic view of a flight control system connection mode II;
FIG. 3 is a schematic diagram of a fault query fault tree.
Detailed Description
The design method according to the present invention will be described in further detail with reference to the accompanying drawings.
A flight control system fault declaration and query method is used for guiding flight control system fault declaration, fault recording and fault query and is realized through the following methods and strategies:
a) interconnecting flight control system components in bus form
A component (recorder) special for recording fault declaration information of each component in flight is added in the flight control system, and the component is interconnected with other components of the flight control system by buses. The method has the function of reporting the faults of each component of the flight control system, and does not depend on application software of the flight control system to carry out fault synthesis and fault reporting on fault points of all the components. The distributed fault synthesis and fault declaration can reduce the burden of the application software of the flight control system, and the application software of the flight control system can be concentrated on the fault declaration at the system level. The connection is shown in fig. 1 and 2.
b) The application software of the flight control system issues uniform time to other components
The flight control system application software runs in the flight control computer and is the core software of the flight control system. The unified system time is distributed to each component, and each component declares own fault information according to the unified system time. The recorder faithfully records the fault information of each component, including the system time. When the follow-up fault inquiry is convenient, the occurrence time of system faults and component faults can be unified.
c) Each component of the system sends the availability of the sensor signal to the application software of the flight control system
Each component of the flight control system informs system application software of the availability of a signal sent to the application software of the flight control system, and the system application software comprehensively obtains system functional fault information based on the signal availability.
d) The recorder receives and records the information of failure declaration
The recorder receives fault declaration information and system fault information from each component (including flight control computer) in the system through the bus and records the information in the memory card of the recorder.
e) Reading information in memory card of recorder to inquire about failure
The memory card in the recorder can be taken out in a quick-release mode and connected to the maintenance equipment; or the information in the memory card is downloaded to the maintenance equipment through a download line. The maintenance device parses the failure information in the memory card and draws a failure tree based on the system uniform time, as shown in fig. 3. And fault inquiry and fault analysis are convenient.
The technology is characterized in that:
1) distributed fault reporting
The distributed fault declaration fully utilizes the CPU operation capacity of each component in the system, and reduces the burden of application software of the flight control system. For a complex system, the coupling degree between system application software and component software is reduced by the distributed fault reporting method, so that the fault relation between the system and the component is more clear and definite.
2) Graphical fault query
Based on the unified time of the system, the fault tree recurrence form is carried out on the fault point, and the system fault and the component fault are displayed, so that the fault inquiry is facilitated, and the fault relation is clear at a glance.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and decorations can be made without departing from the original scope of the invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (8)
1. A flight control system fault declaration query method is characterized by comprising the following steps: the method comprises the following steps:
the method comprises the following steps: a recorder is added in the flight control system for recording the faults of the flight control system;
step two: the recorder is respectively connected with all subsystems in the flight control system through a bus;
step three: a flight control computer in the flight control system sends system time to all other subsystems of the flight control system;
step four: and all other subsystems of the flight control system send respective fault information to the recorder for recording according to the system time.
2. The flight control system fault declaration query method of claim 1, wherein: in the fourth step, all other subsystems of the flight control system send respective fault information and send the system time when the fault occurs to the recorder.
3. The flight control system fault declaration query method of claim 2, wherein: the fourth step further comprises: and all other subsystems of the flight control system also send respective signal availability to the flight control computer.
4. The flight control system fault declaration query method of claim 3, wherein: and the flight control computer comprehensively analyzes the signal availability of each subsystem to obtain system-level fault information.
5. The flight control system fault declaration query method of claim 4, wherein: and the flight control computer sends the system-level fault information to the recorder for recording, and simultaneously sends the system time when the system-level fault occurs to the recorder.
6. The flight control system fault declaration query method of claim 5, wherein: after the fourth step, the method further comprises the step of drawing a fault tree based on the fault information recorded by the recorder.
7. The flight control system fault declaration query method of claim 1, wherein: all subsystems of the flight control system comprise: the system comprises a flight control computer, a flight control console, an inertia measurement unit and a servo actuator.
8. The flight control system fault declaration query method of claim 1, wherein: the generation of the system time is carried out by depending on the running time of a flight control computer of a core component of the flight control system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202011307739.9A CN112486140A (en) | 2020-11-20 | 2020-11-20 | Flight control system fault reporting and inquiring method |
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| CN202011307739.9A CN112486140A (en) | 2020-11-20 | 2020-11-20 | Flight control system fault reporting and inquiring method |
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| CN102393630A (en) * | 2011-09-26 | 2012-03-28 | 南京航空航天大学 | Carrier aircraft landing guide and control system for inhibiting airflow disturbance of stern and control method for system |
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| CN102955456A (en) * | 2011-08-26 | 2013-03-06 | 北京安翔动力科技有限公司 | Bus communication based small unmanned aerial vehicle control system |
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| CN105259788A (en) * | 2015-11-04 | 2016-01-20 | 中国直升机设计研究所 | Fault simulation method and system for flight control system |
| KR20160079394A (en) * | 2014-12-26 | 2016-07-06 | 한국항공우주산업 주식회사 | Desktop based realtime simulation apparatus and method |
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| CN111007873A (en) * | 2019-12-06 | 2020-04-14 | 江西洪都航空工业集团有限责任公司 | Flight control system BIT detection control method and logic |
| CN111862686A (en) * | 2020-06-04 | 2020-10-30 | 中国人民解放军国防科技大学 | Aircraft motion state measurement and data processing system |
-
2020
- 2020-11-20 CN CN202011307739.9A patent/CN112486140A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102467114A (en) * | 2010-11-01 | 2012-05-23 | 成都飞机工业（集团）有限责任公司 | Method for digitally managing unmanned aerial vehicle electricity parameters |
| CN102955456A (en) * | 2011-08-26 | 2013-03-06 | 北京安翔动力科技有限公司 | Bus communication based small unmanned aerial vehicle control system |
| CN102393630A (en) * | 2011-09-26 | 2012-03-28 | 南京航空航天大学 | Carrier aircraft landing guide and control system for inhibiting airflow disturbance of stern and control method for system |
| CN104699067A (en) * | 2013-12-10 | 2015-06-10 | 中国航空工业第六一八研究所 | System fault comprehensive declare processing method |
| KR20160079394A (en) * | 2014-12-26 | 2016-07-06 | 한국항공우주산업 주식회사 | Desktop based realtime simulation apparatus and method |
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