CN102062822A

CN102062822A - Fault diagnosis method of integrated traffic collision avoidance system (TCAS)

Info

Publication number: CN102062822A
Application number: CN2009102189680A
Authority: CN
Inventors: 史忠科; 黄溢
Original assignee: Xian Feisida Automation Engineering Co Ltd
Current assignee: Xian Feisida Automation Engineering Co Ltd
Priority date: 2009-11-16
Filing date: 2009-11-16
Publication date: 2011-05-18
Anticipated expiration: 2029-11-16
Also published as: CN102062822B

Abstract

The invention discloses a fault diagnosis method of an integrated traffic collision avoidance system (TCAS), which finishes software and hardware designs with diagnosis functions such as detection, positioning, reporting and the like of a fault of the integrated TCAS. Aiming at the problem that the conventional TCAS fault diagnosis system is unsuitable for the integrated TCAS, the invention provides a fault diagnosis system of the integrated TCAS in two aspects such as an interface of the TCAS with an airborne maintenance system and a self-detection circuit of the integrated TCAS. In the design, an aeronautical radio Inc. (ARINC) 429 interface is connected with the airborne maintenance system so as to provide data for determining a fault; moreover, a corresponding integrated self-test circuit is designed and simulation TCAS data is operated so as to detect the fault of the system and determine the position of the fault.

Description

Integrated TCAS diagnosis method for system fault

(1) technical field under:

The present invention relates to the diagnosis method for system fault design of airborne TCAS of new generation.

(2) background technology:

Collision avoidance system on the aircraft, the US Airways system is called air traffic early warning and collision avoidance system (hereinafter to be referred as TCAS), aviation system in Europe is called airborne collision avoidance system, both implications, function are consistent, and composition is also similar substantially, so the present patent application instructions is that technical background is described with TCAS.

Through years of development, the TCAS system has developed and multiple model, as: TCAS I, TCAS II, TCAS III, TCAS IV.Wherein TCAS II is most widely used at present, and it can provide with different colours and shape to the aviator and show the traffic prompting (TA) of the relative height of closing on aircraft, distance, orientation, rising/information such as decline state and show pitch channel change, attitude maintenance, the settling mode (RA) of information such as maintenance highly.Other more highest version model architecture based on TCAS II, difference slightly on function just.

The fault diagnosis design of system is the important component part of system design, and necessity is carried out self-test to the TCAS system before taking off, the not permission to take off of aircraft that test is not passed through.The design of good fault diagnosis can be accelerated fault detect speed, and maintenance load is reduced in accurate fault location position, accelerates maintenance speed, therefore considers troubleshooting issue with regard to necessity when system design.

In existing TCAS system, its system fault diagnosis comprises two aspects: on the one hand, fault diagnosis system generally all is housed on the current aircraft, as Aircraft Condition Monitor System on the Boeing-747-400 (ACMS) or airborne integrated data system (AIDS), these systems can cooperate with whole electronic equipments (comprising the TCAS system) on the aircraft, with the duty of each system on the surveillance aircraft, and this interface generally meets ARINC 604 standards; On the other hand, the TCAS system has also comprised self-testing software and circuit and has finished fault diagnosis to self in controller.With TCAS-4000 is example, and circuit such as its self-test, diagnosis report, fault alarm just are integrated on the CTR-92A.

(3) summary of the invention:

In order to realize the fault diagnosis of integrated TCAS system, the present invention has designed the failure diagnosis apparatus interface and has been connected with airborne maintenance system and realizes whole fail soft identification; Also design the integral system self-test function, realized the diagnosis and the localization of fault of system;

The technical solution adopted for the present invention to solve the technical problems: a kind of TCAS method for diagnosing faults, it comprises:

(1) in order to link to each other with Aircraft Condition Monitor System (ACMS) or airborne integrated data system (AIDS), finish the overall fault detect of each system on the aircraft (comprise integrated TCAS system), ARINC 429 buses that the present invention has designed a high speed link to each other with comprehensive detection system.Primary processor only need be when to receive LABEL be 271 ARINC 429 bus datas, the status data of each equipment of collecting is formed ARINC 429 bus datas, send on ARINC 429 buses, data type is a service data, LABEL is that the identification of 356. faults removes to analyze identification, the following Fig. 1 of its communication process by failure diagnosis apparatus software;

(2) the present invention has also designed self-testing system, and it adopts and interrupts detecting the Precise Position System fault certainly, and the removal system fault.

The testing process of self-test function still at first must be tested primary processor according to the flow process of system's normal process signal.After primary processor test is passed through, to each independently functional module test; The self testing circuit simulation produces the intruder data, and these intruders are in different positions, and primary processor produces different warning information according to these positions.The self testing circuit simulation generates A, C, S pattern answer signal, and is loaded in the receiver; Being the test of message processor after the receiver test, is the test of modulator and emitter assemblies afterwards; The following Fig. 2 of the system component that self-test function need be tested; When there is fault in the system of detecting, or carry out fault isolation, or carry out unit replacement.

The invention has the beneficial effects as follows: owing to designed failure diagnosis apparatus interface and integrated self-testing device, the system that makes can be quick, determines himself software fault and hardware fault accurately, and realize localization of fault.

(4) description of drawings:

Accompanying drawing 1 is integral system and failure diagnosis apparatus communication process

Accompanying drawing 2 is system components that self-test function need be tested

(5) embodiment:

In the present embodiment, difference design error failure diagnostic device interface and integrated self-testing device.

(1) failure diagnosis apparatus Interface design:

Airborne maintenance system (OMS) is housed on the type aircraft, and airborne maintenance system equipment meets ARINC 604 standards.Regulation and stipulation communication interface and communication protocol, the diagnostics interface of this integrated system provides design considerations.Communication process between integral system and the failure diagnosis apparatus such as a mistake! Do not find Reference source.Shown in.The interface of failure diagnosis apparatus is high speed ARINC 429 bus interface.Therefore integral system need comprise high speed ARINC 429 bus communication interface.Need the service data of each module of system to be concentrated in together and deliver on these ARINC 429 buses, by ARINC 429 bus transfer to airborne service equipment.Failure diagnosis apparatus generally comprises fault data collection, functions such as fault analysis.

Relation in the taking into account system between each equipment and connected mode, primary processor is in the center, peripherals is connected on the processor, and primary processor periodically reads the data of peripherals, these equipment mainly comprise control enclosure, radio altimeter, pressure altimeter, synchronizer input etc.Primary processor only need be when to receive LABEL be 271 ARINC 429 bus datas, and the status data of each equipment of collecting is formed ARINC 429 bus datas, sends on ARINC 429 buses, and data type is a service data, and LABEL is 356.The identification of fault goes to analyze identification by failure diagnosis apparatus software.

(2) integral system self-test design

Self-test function can be divided into according to the intensity difference: Power-On Self-Test is surveyed (PBIT:Power-up build-in test), is detected (CBIT:Continuous BIT), interruption from detecting (IBIT:Interrupt BIT), quick self-checking survey (QBIT:Quick BIT) periodically certainly.Wherein, interrupt using from detecting by the maintenance personal, the operate as normal of its meeting halt system is done comprehensive test to equipment, accurately judges system failure position.

Integral system is the key equipment of assurance flight safety, if there is fault not allow to take off, therefore needs to use and interrupts detecting the Precise Position System fault certainly, and the removal system fault.The system failure is got rid of by changing LRU (Line-replaceable unit) realization.

Self-test function is done complete detection to equipment.Self-test function is realized by self-built build-in test (BIT:build-in test) circuit.Self testing circuit is distributed in each module, and test circuit comprises that test signal produces circuit, the supervisory circuit of system state, fault display circuit.A mistake! Do not find Reference source.Listed the object of self-test function test, it is the various piece of covering system basically.

One, self-test function is controlled by control enclosure, and after self-test function was triggered, system stopped the response external input signal, and test procedure brings into operation.Self testing procedure is stored in one section independently in the address space, it and the normal function program separate storage of system.

Two, the supervisory circuit of system state is selected suitable system state, as the supervisory electric circuit inspection power source voltage of power supply value, and with the data transmission of monitoring to primary processor, primary processor is judged data, whether determination module fault, and monitored results is stored in the nonvolatile memory.

Three, fault display circuit is on the one hand for each module is equipped with pilot lamp, and according to test result, the control led status is convenient to the state that the tester judges each module; By the mode of multiplexing display, the RA/TA/TVI display can show detecting information on the one hand, and according to ARINC 429 bus protocols regulation, primary processor mails to display with data, and display shows test results.

The testing process of self-test function still at first must be tested primary processor according to the flow process of system's normal process signal.After primary processor test is passed through, to each independently functional module test.The self testing circuit simulation produces the intruder data, and these intruders are in different positions, and primary processor produces different warning information according to these positions.The self testing circuit simulation generates A, C, S pattern answer signal, and is loaded in the receiver.Being the test of message processor after the receiver test, is the test of modulator and emitter assemblies afterwards.

Need to prove that the signal difference of detection mainly comprises between frequency, voltage, impedance, noise, power, the signal input and output concerning.

On the other hand, when there is fault in the system of detecting, or carry out fault isolation, or carry out unit replacement.Therefore observe the modularization principle during system design.Modular design helps system and carries out localization of fault and fault isolation.And help module to change and maintenance

Claims

1. integrated TCAS method for diagnosing faults is characterized in that:

A. designing ARINC 429 interfaces is connected with airborne maintenance system;

B. designed integrated TCAS self-testing system;

2. an integrated TCAS method for diagnosing faults is characterized in that: by ARINC 429 buses the TCAS data are offered airborne maintenance system to determine that whether fault exists;

3. integrated TCAS method for diagnosing faults is characterized in that: in integrated TCAS self-testing system, the designing power supply detection module monitors the work of power supply;

4. an integrated TCAS method for diagnosing faults is characterized in that: the TCAS data of simulation are offered integrated TCAS self-testing system operation, and then detect and fault location.