CN119719973A - Aircraft fault diagnosis method, system and device - Google Patents

Abstract

The present invention relates to the field of fault diagnosis technology, and discloses an aircraft fault diagnosis method, system and device, the method comprising: obtaining a fault tree model and a fault code knowledge base of a target aircraft; the fault tree model characterizes the logical relationship of each fault in the aircraft's airborne equipment; the fault code knowledge base characterizes each fault code information in the aircraft's airborne equipment; based on the fault tree model and the fault code knowledge base of the target aircraft, the target aircraft's airborne equipment is subjected to fault simulation by layer to obtain a fault simulation result; the layer includes at least one of an application layer, a physical layer, a protocol layer and an electrical layer; based on the fault simulation result, the fault is located and diagnosed in real time to obtain a fault diagnosis result. The present invention provides a comprehensive and efficient aircraft fault simulation diagnosis and knowledge base management function, which improves the safety and reliability of the aircraft.

Description

Method, system and equipment for diagnosing faults of aircraft

Technical Field

The invention relates to the technical field of fault diagnosis, in particular to an aircraft fault diagnosis method, system and equipment.

Background

With the continued development of the global aviation industry, the safety and reliability of aircraft has become a focus of industry attention. The fault diagnosis technology of the aircraft is used as an important means for guaranteeing the safe operation of the aircraft, and has important significance in research and development. The technology can discover and locate faults in time by monitoring, detecting and analyzing the running state of the aircraft in real time, thereby effectively preventing accidents and prolonging the service life of the aircraft.

The traditional airborne system fault diagnosis research system has the problems of few fault types, serious dependence on hardware mechanical equipment caused by fault generation, complex operation, difficult development, time and labor waste, difficult management of fault diagnosis results, low universality of diagnosis equipment and the like, and in the running process of an aircraft, any tiny fault can be rapidly expanded and cause serious consequences, and the traditional fault signals are difficult to simulate and rapidly inject into the airborne system.

Disclosure of Invention

In view of the above, the invention provides a method, a system and equipment for diagnosing faults of an aircraft, which are used for providing comprehensive and efficient fault simulation diagnosis and knowledge base management functions of the aircraft, and improving the safety and reliability of the aircraft.

The invention provides an aircraft fault diagnosis method, which comprises the steps of obtaining a fault tree model and a fault code knowledge base of a target aircraft, wherein the fault tree model represents each fault logic relation in aircraft airborne equipment, the fault code knowledge base represents each fault code information in the aircraft airborne equipment, conducting fault simulation on the target aircraft airborne equipment according to layers based on the fault tree model and the fault code knowledge base of the target aircraft to obtain a fault simulation result, and conducting fault real-time positioning and diagnosis based on the fault simulation result to obtain a fault diagnosis result.

In an alternative implementation mode, fault simulation is conducted on the airborne equipment of the target aircraft according to layers based on a fault tree model and a fault code knowledge base of the target aircraft, and after a fault simulation result is obtained, the fault simulation result is injected into a fault diagnosis prototype through hardware interface resources and hardware fault injection adaptation equipment, and the fault diagnosis prototype is used for simulating the airborne equipment of the aircraft.

In an alternative embodiment, the method further comprises updating the fault tree model and the fault code knowledge base based on the fault diagnosis results.

In an alternative implementation mode, the step of carrying out fault simulation according to layers comprises the steps of establishing an application layer fault model and carrying out fault simulation in an application layer, wherein the application layer fault model comprises combined navigation sensor faults, flight control system faults and steering engine faults, establishing a physical layer fault model and carrying out fault simulation in a physical layer, the physical layer fault model comprises signal-to-power short circuits, signal-to-ground short circuits and open circuits, establishing a protocol layer fault model and carrying out fault simulation in a protocol layer, the protocol layer fault model comprises serial communication bus electric faults, establishing an electric layer fault model and carrying out fault simulation in an electric layer, and the electric layer fault model comprises power supply abnormity and signal fluctuation.

In an alternative embodiment, the fault diagnosis result includes at least one of a fault code, a fault location, a fault occurrence time, a fault type, and a fault handling measure.

In an alternative embodiment, building the fault tree model of the aircraft comprises determining a top event, an intermediate event and a basic fault, wherein the top event is a main fault event of on-board equipment of the aircraft, the intermediate event is a specific fault event causing the top event, the basic fault is a basic fault causing the intermediate event, and the fault tree model is generated according to a logic relation among the top event, the intermediate event and the basic fault.

The invention provides an aircraft fault diagnosis system which comprises a fault expert knowledge base module, a fault diagnosis prototype module and a fault diagnosis prototype module, wherein the fault expert knowledge base module is used for acquiring a fault tree model and a fault code knowledge base of a target aircraft, the fault tree model represents each fault logic relation in aircraft airborne equipment, the fault code knowledge base represents each fault code information in the aircraft airborne equipment, the fault simulation and injection module is used for conducting fault simulation on the target aircraft airborne equipment according to layers based on the fault tree model and the fault code knowledge base of the target aircraft to obtain a fault simulation result, the layers comprise at least one of an application layer, a physical layer, a protocol layer and an electric layer, and the fault diagnosis prototype module is used for conducting fault real-time positioning and diagnosis based on the fault simulation result to obtain the fault diagnosis result.

In an alternative embodiment, the fault simulation and injection module is further configured to inject the fault simulation result into a fault diagnosis prototype through the hardware interface resource and the hardware fault injection adaptation device, where the fault diagnosis prototype is configured to simulate an on-board device of the aircraft.

In an alternative embodiment, the fault expert knowledge base module is further configured to update the fault tree model and the fault code knowledge base based on the fault diagnosis results.

In a third aspect, the invention provides a computer device comprising a memory and a processor, the memory and the processor being in communication with each other, the memory having stored therein computer instructions, the processor executing the computer instructions to thereby perform a method of diagnosing an aircraft failure according to the first aspect or any of its corresponding embodiments.

In a fourth aspect, the present invention provides a computer readable storage medium having stored thereon computer instructions for causing a computer to perform a method of diagnosing an aircraft failure according to the first aspect or any of its corresponding embodiments.

In a fifth aspect, the present invention provides a computer program product comprising computer instructions for causing a computer to perform a method of diagnosing an aircraft failure according to the first aspect or any of its corresponding embodiments.

The technical scheme provided by the invention can comprise the following beneficial effects:

The fault tree model and the fault code knowledge base respectively provide logic relation and code information of faults in the aircraft airborne equipment, are the basis of subsequent fault simulation, can comprehensively simulate various fault conditions possibly encountered by the aircraft airborne equipment in the actual operation process through the fault simulation of an application layer, a physical layer, a protocol layer and an electric layer, and can quickly and accurately position and diagnose the faults based on the fault simulation result by combining a fault diagnosis model and a positioning algorithm. According to the scheme, through the steps of obtaining the fault tree model and the fault code knowledge base, performing multi-level fault simulation, real-time fault positioning, diagnosis and the like, comprehensive and efficient fault simulation diagnosis and knowledge base management functions of the aircraft are provided, and the safety and reliability of the aircraft are improved.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.

FIG. 1 is a flow diagram of an aircraft fault diagnosis method according to an embodiment of the invention;

FIG. 2 is a schematic diagram of an aircraft fault diagnosis according to an embodiment of the invention;

FIG. 3 is a block diagram of an aircraft fault diagnosis device according to an embodiment of the invention;

fig. 4 is a schematic diagram of a hardware structure of a computer device according to an embodiment of the present invention.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

According to an embodiment of the present invention, an aircraft fault diagnosis method embodiment is provided, it being noted that the steps shown in the flowchart of the figures may be performed in a computer system, such as a set of computer executable instructions, and, although a logical order is shown in the flowchart, in some cases, the steps shown or described may be performed in an order other than that shown or described herein.

In this embodiment, an aircraft fault diagnosis method is provided, and fig. 1 is a flowchart of an aircraft fault diagnosis method according to an embodiment of the present invention, as shown in fig. 1, where the flowchart includes the following steps:

Step S101, a fault tree model and a fault code knowledge base of a target aircraft are obtained, the fault tree model represents each fault logic relation in the aircraft airborne equipment, and the fault code knowledge base represents each fault code information in the aircraft airborne equipment.

The fault tree is a method for identifying and analyzing faults of the airborne equipment of the aircraft, can realize fault prediction and fault cause analysis, and can display fault logic relations through graphics. The fault tree structure is divided into a primitive fault tree and a logic calculation fault tree, wherein the primitive fault tree is used for editing a fault tree model and managing a fault tree engineering file. The logic calculation fault tree is generated by a primitive fault tree, is mainly used for analyzing and detecting the fault tree, and has the functions of analyzing, modeling, configuring basic event parameters, deriving model tree pictures and data, managing engineering files, designing workflow and the like. In the invention, the fault tree model connects various basic fault events through logic gates (such as AND gates, OR gates and the like) to form a tree structure, and the causal relationship among the fault events is shown. The fault tree model provides a fault logic relationship for subsequent fault simulation.

The fault code knowledge base is a database storing various fault codes and corresponding fault information of the aircraft on-board equipment. According to the fault code knowledge base, the fault scene, fault positioning judgment and possible fault states can be inquired. The fault code knowledge base provides fault code information for subsequent fault simulation.

Step S102, performing fault simulation on the airborne equipment of the target aircraft according to a hierarchy based on a fault tree model and a fault code knowledge base of the target aircraft to obtain a fault simulation result, wherein the hierarchy comprises at least one of an application layer, a physical layer, a protocol layer and an electric layer.

Fault simulation is a simulation of various possible fault scenarios of the equipment onboard an aircraft to predict and evaluate the impact of these faults on the performance of the equipment. The typical fault simulation based on the aircraft mainly comprises two types of faults, namely a part component functional fault model integrated in a flight model library, a fault simulation based on model fault data, and an application layer fault simulation, wherein the fault simulation based on program-controlled hardware comprises a protocol layer fault, an electrical layer fault and a physical layer fault based on control implementation of hardware equipment. Each layer represents different components and functional characteristics of the device, wherein an application layer is a layer of a software architecture, which is directly interacted with a user and is responsible for processing various application functions and data processing directly related to a flight task, a physical layer is a hardware device part of an aircraft and is responsible for physical connection and transmission of a hardware interface, an electric signal and the like, a protocol layer is responsible for communication and data exchange between devices, and an electric layer is responsible for transmission and distribution of the electric signal. The fault simulation result obtained by performing fault simulation according to the layers can cover typical faults of the aircraft in a test task or a flight process, and support is provided for subsequent fault real-time positioning and diagnosis.

And step S103, based on the fault simulation result, performing fault real-time positioning and diagnosis to obtain a fault diagnosis result.

And carrying out calculation and analysis on the fault simulation result through a fault diagnosis model, identifying the fault type and positioning a fault source. The fault diagnosis model is a mathematical model constructed on the basis of a certain algorithm or rule and is used for monitoring and diagnosing the fault condition of the airborne equipment in real time during the running process of the aircraft. And obtaining a fault diagnosis result through real-time positioning and diagnosis. From the fault diagnosis results, detailed fault reports can be generated for fault analysis and system optimization of the aircraft on-board equipment. Meanwhile, the fault diagnosis model operates in a real-time environment, and can rapidly respond and process faults in real time, so that measures can be rapidly taken when the faults occur without affecting flight results.

In conclusion, through the steps of obtaining the fault tree model and the fault code knowledge base, performing multi-level fault simulation, real-time fault positioning, diagnosis and the like, comprehensive and efficient fault simulation diagnosis and knowledge base management functions of the aircraft are provided, and safety and reliability of the aircraft are improved.

In an alternative embodiment, the fault simulation result is injected into a fault diagnosis prototype through hardware interface resources and hardware fault injection adapting equipment, and the fault diagnosis prototype is used for simulating on-board equipment of the aircraft.

Hardware interface resources are various physical interfaces for connection and communication, for data transfer and signal exchange between different hardware devices. In the present invention, the hardware interface resources include serial communication interfaces, ethernet interfaces, analog signal interfaces, and digital signal interfaces. The hardware interface enables the fault simulation apparatus to connect with the fault diagnosis prototype and other hardware components. The hardware fault injection adapting device is used for converting a fault simulation result into a form suitable for being received by a fault diagnosis prototype, and comprises a signal conditioning circuit, an interface conversion circuit and control logic. The fault signal is simulated through the real hardware interface and the fault injection equipment, so that the authenticity of fault simulation is improved, and the test result is more reliable.

The fault diagnosis prototype is equipment for simulating functions and interfaces of airborne equipment of an aircraft, has a hardware and software architecture similar to that of real airborne equipment, can simulate actual running conditions of the aircraft in a ground environment, and receives a fault injection signal comprising a fault simulation result. By running the fault diagnosis model, the fault diagnosis prototype machine can locate and diagnose the fault simulation result in real time. The fault diagnosis prototype machine supports the rapid verification of fault diagnosis algorithm design in the early design stage, realizes fault diagnosis and fault processing function verification, and optionally also supports the replacement of real airborne fault diagnosis equipment to a test environment in the later stage, and supports the rapid diagnosis and fault processing capability verification of the airborne fault diagnosis equipment.

The fault diagnosis prototype provides an operation environment of a fault test, provides rich application scenes of the fault test, realizes full verification of a fault diagnosis function of an airborne system through test design on the ground, improves the rapid diagnosis response capability of the system to the fault, and improves the safety of flight design.

In an alternative embodiment, an aircraft fault diagnosis method further comprises:

Based on the fault diagnosis result, the fault tree model and the fault code knowledge base are updated.

And when the fault diagnosis result shows that a new fault type or fault path exists, feeding back the fault type or fault path into the fault tree model, and updating the fault logic relationship. Based on the fault diagnosis result, a new fault code and corresponding fault information thereof are obtained and added into a fault code knowledge base. By continuously updating the fault tree model and the fault code knowledge base, the fault diagnosis performance can be improved, and various faults can be more accurately positioned and diagnosed.

In an alternative embodiment, the performing fault simulation in layers in step S102 includes:

And a step a11, establishing an application layer fault model and performing fault simulation on an application layer, wherein the application layer fault model comprises an integrated navigation sensor fault, a flight control system fault and a steering engine fault.

The application layer fault model simulates typical fault conditions in upper layer applications of the aircraft, including integrated navigation sensor faults, flight control system faults, and steering engine faults. Application layer failures can reflect software or configuration problems that may occur during actual flight.

Specifically, the application layer fault is mainly realized through a fault simulation model, and a typical application layer fault model library of the aircraft is provided, which mainly comprises a type fault model library of combined navigation sensor faults, flight control system faults, steering engine faults and the like, and is integrated in a Matlab/Simulink development environment.

The fault model library comprises a fault model library of types such as integrated navigation sensor faults, flight control system faults, steering engine faults and the like, and the fault model library comprises the following specific steps:

1) The integrated navigation fault model library comprises a GPS navigation fault model and an inertial navigation fault model.

2) The flight control system fault model library comprises a control unit fault model, a power supply fault model and a communication fault model.

3) The steering engine fault model library comprises a communication fault model, a motor fault, a position sensor fault model and a control surface mechanical fault model.

The user-defined application fault model expansion is supported, and the user-defined application fault model expansion is loaded into an application layer fault model library, and is conveniently dragged into a test model as a library module, so that the user-defined model data injection is realized.

And a step a12, establishing a physical layer fault model and performing fault simulation on the physical layer, wherein the physical layer fault model comprises signal-to-power short circuit, signal-to-ground short circuit and open circuit.

The physical layer fault model simulates fault conditions in the physical connection and transmission of the hardware interface and the electrical signals, including signal-to-power shorts, signal-to-ground shorts, open circuit faults. Physical layer failures directly affect the physical transmission of electrical signals. These physical layer failures are simulated by hardware means (such as physical connection errors, shorting plates, etc.) or by control software using physical layer failure injection equipment.

And a step a13, establishing a protocol layer fault model and performing fault simulation on a protocol layer, wherein the protocol layer fault model comprises a serial communication bus electrical fault.

The protocol layer fault model simulates faults occurring in the communication and data exchange processes, including electrical faults (such as voltage bias, misregulation of common mode voltage, signal delay and data bit inversion) of the serial communication bus. These faults affect the accuracy and integrity of the data transmission. Protocol layer failures affect the accuracy and integrity of data transmission. The protocol layer fault is simulated by modifying the communication signals or protocol parameters using the electrical layer/protocol layer fault injection device.

And a step a14, establishing an electrical layer fault model and performing fault simulation on an electrical layer, wherein the electrical layer fault model comprises abnormal power supply and signal fluctuation.

The electrical layer fault model simulates power supply and signal transmission problems in an electrical system, including power supply anomalies (e.g., voltage instabilities, power supply faults) and signal fluctuations (e.g., noise disturbances, signal attenuation). Electrical layer faults affect the stability and reliability of the electrical system. Power anomalies are simulated by electrical test equipment (e.g., power supplies, signal generators), and signal fluctuations are simulated using a signal analyzer or oscilloscope.

In addition, the real-time hardware I/O interface driver mainly provides real-time simulation of hardware fault signals, provides a hardware interface board card driver, realizes a fault injection control function for airborne equipment, and realizes drive management and real-time calling functions of real-time fault injection hardware interface resources.

Optionally, the fault diagnosis result includes at least one of a fault code, a fault location, a fault occurrence time, a fault type, and a fault handling measure.

The fault code is a code or number that uniquely identifies a particular fault, one code being assigned to each fault. The fault location refers to the aircraft specific device or system in which the fault occurred. For example, faults occur in integrated navigation systems, flight control systems, steering engines, or other on-board devices. The time of occurrence of the fault records the specific point in time when the fault is first detected and is used for determining the operation phase of the fault occurrence. The fault type characterizes the nature of the fault, such as hardware fault, software fault, configuration error. Fault handling measures are countermeasures against faults, including replacement of faulty components, reconfiguration of system parameters, updating of software or firmware. The fault diagnosis result provides comprehensive information about the fault, and is helpful for quickly locating the fault and taking corresponding treatment measures.

In an alternative embodiment, the acquiring the fault tree model of the aircraft in the step S101 includes:

step b11, determining a top event, an intermediate event and a basic fault, wherein the top event is a main fault event of airborne equipment of the aircraft, the intermediate event is a specific fault event causing the top event, and the basic fault is a basic fault causing the intermediate event.

Roof events are major fault events of the aircraft on-board equipment, such as aircraft on-board system failures, aircraft unresponsive maneuvers, etc., which are the targets of the overall fault tree analysis. An intermediate event is a specific failure event that causes a top event to occur. In the fault tree, they are located between the roof event and the foundation fault, as a bridge connecting the two. An intermediate event may be a failure of one or more subsystems, such as a "flight control computer failure" or "sensor data anomaly. The intermediate events of the invention comprise integrated navigation sensor faults, flight control computer faults and steering engine failure faults. The fault tree model of the aircraft airborne system is defined by using a rectangular module, and the fault tree model of the steering engine consists of four basic intermediate faults, namely a communication fault, a motor fault, a position sensor fault and a control surface mechanical fault. The basic faults are the lowest, most fundamental cause of occurrence of intermediate events, typically non-redispersible hardware or software faults such as "power module damage", "software logic errors", etc. The basic faults are positioned at the bottommost end of the fault tree, can consist of single or multiple basic faults, are defined by using a circular module in an aircraft airborne system failure fault tree model, and cause an intermediate event to occur through logic gate operation. A basic fault composition diagram of motor faults, the basic faults of motor faults consisting of a control unit, power supply and mechanical faults. The user can customize the probability of occurrence of faults in the circular basic fault module, and all basic faults accord with the exponential distribution probability.

And b12, generating a fault tree model according to the logic relation among the top event, the intermediate event and the basic fault.

After the top event, intermediate event, and base fault are determined, a fault tree model is generated from the logical relationships between them. In the fault tree, different events are connected through logic gates (such as AND gate AND OR gate) to express the logic relationship between the events. For example, if two intermediate events must occur simultaneously to cause a top event to occur, then the two intermediate events should be connected to the top event through an AND gate.

Specifically, the design flow of the fault tree model is as follows:

(1) Determining a top event;

(2) Determining an intermediate event;

(3) Determining a basic fault;

(4) And (3) drawing a tree diagram, namely designing logic relations in the fault tree by using FTA software. For example, using an AND gate to indicate that multiple base events must occur simultaneously to cause a top event, and using an OR gate to indicate that any occurrence of an event causes a top event. Each elementary event is connected to an appropriate logic gate to reflect the fault propagation path in the system.

(5) Results and analysis the FTA is run to perform calculations and analyze the results to determine the probability of a top event and the primary failure path that caused the top event to occur. The probability of the top event is calculated by combining the probability with the truth table of the logic gates. The user may be aided in determining the overall reliability of the aircraft on-board system. And according to the analysis result, evaluating the reliability of the onboard system of the aircraft, and then proposing improvement advice to take measures to reduce the probability of faults and enhance the fault tolerance of the system.

In the implementation of the present invention, as shown in fig. 2, the present invention is composed of a fault simulation and injection part, a fault diagnosis prototype part, and a fault expert knowledge base part. The fault expert knowledge base comprises a fault tree and a fault code knowledge base which are typical of an aircraft, provides common fault types and fault occurrence probabilities based on a method for identifying and analyzing faults of an onboard system of the aircraft, and provides references for fault injection. The fault expert knowledge base has the functions of fault early warning display and expert knowledge base driving and management, analyzes and predicts a fault system in a test, has the function of fault tree analysis, can realize fault prediction and cause analysis, and comprehensively utilizes test data and system model knowledge to complete the health management of the aircraft.

The fault diagnosis subsystem provides a fault diagnosis prototype machine which simulates the fault positioning and diagnosis processing functions of the airborne equipment, the fault diagnosis target machine loads a fault diagnosis model, receives a fault injection signal through a hardware interface, performs positioning and diagnosis, outputs positioning and diagnosis results, performs fault processing through fault tolerance control and fault isolation model, and enables the fault result not to affect the flight test state after the fault is reported. The fault diagnosis result can be corrected, enriched and perfected through the fault test and diagnosis process.

Specifically, the fault diagnosis model includes a fault location and diagnosis model (phm_integrated_nav_sys) of a fault Integrated navigation system, a fault location and diagnosis phm_fcm of a flight control system, and a fault location and diagnosis model (phm_actual) of an execution cabinet. The input of the model is respectively a sensor bus signal, a flight control system FCM bus signal and a steering engine bus signal, and the fault diagnosis model can output diagnosis results of inertial navigation IMU fault codes, GPS navigation fault codes, flight control FCM fault codes, execution mechanism Actuation fault codes and the like through positioning diagnosis logic diagnosis according to fault injection of an application layer, protocol layer fault injection and physical layer fault injection. The fault diagnosis model provides fault diagnosis and positioning functions, fault tolerance control and fault processing functions, fault results are reported and fault processing is achieved in a flight test, normal flight test data are output by the model, and the flight state is not influenced as much as possible by faults.

According to the invention, an aircraft application layer fault model is designed based on an MATLAB/Simulink environment, a simulation target code is automatically generated, fault injection is provided through a fault real-time simulator, meanwhile, fault simulation and injection of a hardware layer are provided through a physical layer fault injection device and an electrical/protocol layer fault injection device, faults are provided to a fault diagnosis prototype machine through a hardware fault injection adapting device, in the fault simulation process, the fault diagnosis prototype machine simulates an aircraft flight process and a typical fault diagnosis mode, real-time fault reasoning diagnosis, positioning and fault-tolerant control are performed, and finally, a diagnosis result is fed back to a fault expert diagnosis subsystem to form a real-time closed-loop fault diagnosis test environment.

The fault real-time simulation machine is a real-time simulation machine, runs a real-time operating system, supports real-time operation of an application fault model and fault data excitation, provides a fault hardware interface, provides real-time excitation of hardware interfaces such as analog quantity, discrete quantity, serial port and CAN channel, supports excitation test faults from a hardware layer, and provides injection of fault signals.

The fault diagnosis prototype subsystem mainly realizes the simulation function of a fault diagnosis prototype of the airborne equipment of the aircraft, runs a real-time simulation engine, configures a physical hardware interface the same as that of the airborne equipment, has the functions of the airborne equipment and the functions of fault diagnosis, prediction and positioning, predicts and diagnoses according to input faults, outputs a fault diagnosis result, and supports the storage and management of the fault diagnosis result. The hardware implementation is a real-time simulation computer, a fault diagnosis verification prototype target machine platform is realized, a real-time operating system is operated, and the following functions are mainly completed:

a) The real-time simulation engine provides a real-time operation platform for the inference engine and the fault-tolerant flight control software, can calculate the algorithm model of the fault diagnosis inference engine in real time, and has the functions of controlling the prototype start-stop control of the computer, the data communication service, the data storage service, the algorithm scheduling service management and the like;

b) The configuration provides the same hardware interface as the airborne equipment, has the capability of fault diagnosis and verification of prototype machine bus network communication and non-bus signal acquisition control, combines various sensor variable information acquired by the system, carries out inference engine real-time calculation according to input quantity, and outputs early warning information and fault diagnosis results.

The invention supports the access of real aircraft onboard equipment to replace a fault diagnosis prototype, and enriches and perfects a fault tree model and a fault diagnosis code table through an onboard real fault test and positioning diagnosis result. In the test process, the access of the airborne equipment is supported through the hardware fault injection adaptation unit, the fault simulation and injection of multiple scenes are provided for the real airborne equipment, and the fault expert knowledge base part in the invention is further enriched and perfected through the fault positioning and diagnosis test of the real equipment.

The invention provides various fault diagnosis test application scenes. And the system fault detection and fault diagnosis function test is realized through the application layer, the protocol layer and the physical layer fault injection test. For example, the fault test is mainly divided into the following test scenarios:

1) And (3) application layer fault injection, namely simulating control surface clamping stagnation fault injection by exciting an application layer fault model, injecting faults based on fault diagnosis test software, and setting fault injection of ailerons, elevators or rudder clamping stagnation and the like. The fault diagnosis prototype is loaded and operated with a fault diagnosis model, and after the fault diagnosis model detects a fault, a fault code 0xA1510000 is output, and the corresponding fault is elevator clamping stagnation. Meanwhile, the fault diagnosis model carries out fault processing, and the output value of the model is kept unchanged after the deflection of the rudder is dithered, so that the flight test is not affected.

2) And the protocol layer fault injection is to simulate the inertial navigation communication disconnection fault of the aircraft through the protocol/electrical layer fault injection equipment, and to perform fault detection and diagnosis through a fault diagnosis prototype operation diagnosis model. And after the fault diagnosis model detects the fault, outputting fault codes 0xA2112000 and 0xA2111000, wherein the corresponding faults are accelerometer 1 failure and gyroscope 1 failure. The fault diagnosis prototype model carries out fault processing, and parameter output values such as a rolling angle, a yaw angle, a pitch angle, a North east sky speed and the like of the flight are kept unchanged, so that a flight test is not influenced.

3) Physical layer fault injection, simulating physical layer fault injection through three scenarios:

a) And in the GPS fault test, a DA signal is output through an analog quantity to simulate a GPS signal, a physical layer fault injection box is used for simulating latitude fault injection, and fault detection and fault diagnosis are realized through a fault diagnosis prototype machine. And after the fault diagnosis model detects the fault, outputting a fault code 0xA2122200 corresponding to the fault GPS signal fault. The fault diagnosis prototype model carries out fault processing, and parameter output values such as altitude, latitude, longitude and the like of the flight are kept unchanged, so that the flight test is not influenced.

B) The power supply fault test of the flight control system comprises the steps of simulating power supply of the flight control system through a DA signal output by analog quantity, simulating power supply open-circuit fault injection of a flight control computer through a physical layer fault injection box, realizing fault detection and fault diagnosis through a fault diagnosis prototype, normally outputting a model when a fault is not injected, injecting an FCM power supply fault through fault diagnosis test software, and outputting a fault code 0xA3130000 corresponding to the fault FCM power supply fault after the fault diagnosis model detects the fault. The fault diagnosis prototype model performs fault processing, and comprehensive voting of the flight control system is not affected.

C) And simulating a state detection signal of the atmospheric data sensor through a discrete quantity signal DO, simulating a sensor state fault injection scene through a physical layer fault injection box, and realizing fault detection and fault diagnosis through a fault diagnosis prototype. And after the fault diagnosis model detects the fault, outputting a fault code 0xA4100000 corresponding to the fault of the faulty atmospheric sensor 1. The fault diagnosis prototype model performs fault processing, and the comprehensive acquisition and the flight state of the atmospheric data are not affected.

In this embodiment, an aircraft fault diagnosis system is further provided, and the system is used to implement the foregoing embodiments and preferred embodiments, and will not be described in detail. As used below, the term "module" may be a combination of software and/or hardware that implements a predetermined function. While the means described in the following embodiments are preferably implemented in software, implementation in hardware, or a combination of software and hardware, is also possible and contemplated.

The present embodiment provides an aircraft fault diagnosis system, as shown in fig. 3, including:

The fault expert knowledge base module 301 is configured to obtain a fault tree model of the target aircraft and a fault code knowledge base, where the fault tree model represents each fault logic relationship in the on-board device of the aircraft, and the fault code knowledge base represents each fault code information in the on-board device of the aircraft.

The fault simulation and injection module 302 is configured to perform fault simulation on the on-board device of the target aircraft according to a hierarchy based on the fault tree model and the fault code knowledge base of the target aircraft to obtain a fault simulation result, where the hierarchy includes at least one of an application layer, a physical layer, a protocol layer, and an electrical layer.

The fault diagnosis prototype module 303 is configured to perform fault real-time positioning and diagnosis based on the fault simulation result, so as to obtain a fault diagnosis result.

In an alternative embodiment, the fault simulation and injection module 302 is further configured to inject the fault simulation result into a fault diagnosis prototype through the hardware interface resource and the hardware fault injection adaptation device, where the fault diagnosis prototype is configured to simulate the on-board device of the aircraft.

In an alternative embodiment, the fault expert knowledge base module 301 is further configured to update the fault tree model and the fault code knowledge base based on the fault diagnosis result.

In an alternative embodiment, the fault simulation and injection module 302 includes:

The system comprises an application layer simulation unit, an application layer fault simulation unit and a control system simulation unit, wherein the application layer simulation unit is used for establishing an application layer fault model and performing fault simulation on an application layer, and the application layer fault model comprises an integrated navigation sensor fault, a flight control system fault and a steering engine fault.

And the physical layer simulation unit is used for establishing a physical layer fault model and performing fault simulation on the physical layer, wherein the physical layer fault model comprises a signal-to-power short circuit, a signal-to-ground short circuit and an open circuit.

The protocol layer simulation unit is used for establishing a protocol layer fault model and performing fault simulation on a protocol layer, wherein the protocol layer fault model comprises a serial communication bus electrical fault.

And the electric layer simulation unit is used for establishing an electric layer fault model and performing fault simulation on an electric layer, wherein the electric layer fault model comprises power supply abnormality and signal fluctuation.

In an alternative embodiment, the fault diagnosis result includes at least one of a fault code, a fault location, a fault occurrence time, a fault type, and a fault handling measure.

In an alternative embodiment, the fault expert knowledge base module 301 includes:

The first fault tree model acquisition unit is used for determining a top event, an intermediate event and a basic fault, wherein the top event is a main fault event of airborne equipment of the aircraft, the intermediate event is a specific fault event which causes the top event, and the basic fault is a basic fault which causes the intermediate event.

Fault tree analysis, also known as accident tree analysis, is the most important analysis method in security system engineering. The accident tree analysis starts from a possible accident, searches the direct cause and the indirect cause of the top event from top to bottom, until the basic cause event, and expresses the logic relation between the events by using a logic diagram.

And the second fault tree model acquisition unit is used for generating a fault tree model according to the logical relationship among the top event, the intermediate event and the basic fault.

Further functional descriptions of the above respective modules and units are the same as those of the above corresponding embodiments, and are not repeated here.

An aircraft fault diagnosis system in this embodiment is presented in the form of functional units, where the units are ASIC (Application SPECIFIC INTEGRATED Circuit) circuits, processors and memories executing one or more software or firmware programs, and/or other devices that can provide the above functions.

The embodiment of the invention also provides computer equipment, which is provided with the aircraft fault diagnosis system shown in the figure 3.

Referring to fig. 4, fig. 4 is a schematic structural diagram of a computer device according to an alternative embodiment of the present invention, and as shown in fig. 4, the computer device includes one or more processors 10, a memory 20, and interfaces for connecting components, including a high-speed interface and a low-speed interface. The various components are communicatively coupled to each other using different buses and may be mounted on a common motherboard or in other manners as desired. The processor may process instructions executing within the computer device, including instructions stored in or on memory to display graphical information of the GUI on an external input/output device, such as a display device coupled to the interface. In some alternative embodiments, multiple processors and/or multiple buses may be used, if desired, along with multiple memories and multiple memories. Also, multiple computer devices may be connected, each providing a portion of the necessary operations (e.g., as a server array, a set of blade servers, or a multiprocessor system). One processor 10 is illustrated in fig. 4.

The processor 10 may be a central processor, a network processor, or a combination thereof. The processor 10 may further include a hardware chip, among others. The hardware chip may be an application specific integrated circuit, a programmable logic device, or a combination thereof. The programmable logic device may be a complex programmable logic device, a field programmable gate array, a general-purpose array logic, or any combination thereof.

Wherein the memory 20 stores instructions executable by the at least one processor 10 to cause the at least one processor 10 to perform a method for implementing the embodiments described above.

The memory 20 may include a storage program area that may store an operating system, application programs required for at least one function, and a storage data area that may store data created according to the use of the computer device, etc. In addition, the memory 20 may include high-speed random access memory, and may also include non-transitory memory, such as at least one magnetic disk storage device, flash memory device, or other non-transitory solid-state storage device. In some alternative embodiments, memory 20 may optionally include memory located remotely from processor 10, which may be connected to the computer device via a network. Examples of such networks include, but are not limited to, the internet, intranets, local area networks, mobile communication networks, and combinations thereof.

The memory 20 may comprise volatile memory, such as random access memory, or nonvolatile memory, such as flash memory, hard disk or solid state disk, or the memory 20 may comprise a combination of the above types of memory.

The computer device further comprises input means 30 and output means 40. The processor 10, memory 20, input device 30, and output device 40 may be connected by a bus or other means, for example in fig. 4.

The input device 30 may receive input numeric or character information and generate key signal inputs related to user settings and function control of the computer apparatus, such as a touch screen, a keypad, a mouse, a trackpad, a touchpad, a pointer stick, one or more mouse buttons, a trackball, a joystick, and the like. The output means 40 may include a display device, auxiliary lighting means (e.g., LEDs), tactile feedback means (e.g., vibration motors), and the like. Such display devices include, but are not limited to, liquid crystal displays, light emitting diodes, displays and plasma displays. In some alternative implementations, the display device may be a touch screen.

The embodiments of the present invention also provide a computer readable storage medium, and the method according to the embodiments of the present invention described above may be implemented in hardware, firmware, or as a computer code which may be recorded on a storage medium, or as original stored in a remote storage medium or a non-transitory machine readable storage medium downloaded through a network and to be stored in a local storage medium, so that the method described herein may be stored on such software process on a storage medium using a general purpose computer, a special purpose processor, or programmable or special purpose hardware. The storage medium may be a magnetic disk, an optical disk, a read-only memory, a random-access memory, a flash memory, a hard disk, a solid state disk, or the like, and further, the storage medium may further include a combination of the above types of memories. It will be appreciated that a computer, processor, microprocessor controller or programmable hardware includes a storage element that can store or receive software or computer code that, when accessed and executed by the computer, processor or hardware, implements the methods illustrated by the above embodiments.

Portions of the present invention may be implemented as a computer program product, such as computer program instructions, which when executed by a computer, may invoke or provide methods and/or aspects in accordance with the present invention by way of operation of the computer. Those skilled in the art will appreciate that the existence of computer program instructions in a computer-readable medium includes, but is not limited to, source files, executable files, installation package files, and the like, and accordingly, the manner in which computer program instructions are executed by a computer includes, but is not limited to, the computer directly executing the instructions, or the computer compiling the instructions and then executing the corresponding compiled programs, or the computer reading and executing the instructions, or the computer reading and installing the instructions and then executing the corresponding installed programs. Herein, a computer-readable medium may be any available computer-readable storage medium or communication medium that can be accessed by a computer.

Although embodiments of the present invention have been described in connection with the accompanying drawings, various modifications and variations may be made by those skilled in the art without departing from the spirit and scope of the invention, and such modifications and variations fall within the scope of the invention as defined by the appended claims.

Claims (10)

1. A method of diagnosing an aircraft fault, the method comprising:

the method comprises the steps of obtaining a fault tree model of a target aircraft and a fault code knowledge base, wherein the fault tree model represents each fault logic relation in aircraft airborne equipment;

Performing fault simulation on the airborne equipment of the target aircraft according to a hierarchy based on a fault tree model and a fault code knowledge base of the target aircraft to obtain a fault simulation result, wherein the hierarchy comprises at least one of an application layer, a physical layer, a protocol layer and an electric layer;

And based on the fault simulation result, carrying out fault real-time positioning and diagnosis to obtain a fault diagnosis result.

2. The method according to claim 1, wherein the fault simulation is performed on the on-board equipment of the target aircraft according to the level based on the fault tree model and the fault code knowledge base of the target aircraft, and after obtaining the fault simulation result, the method further comprises:

And injecting the fault simulation result into a fault diagnosis prototype through hardware interface resources and hardware fault injection adapting equipment, wherein the fault diagnosis prototype is used for simulating aircraft-mounted equipment.

3. The method according to claim 1, wherein the method further comprises:

and updating the fault tree model and the fault code knowledge base based on the fault diagnosis result.

4. The method of claim 1, wherein the step of hierarchically modeling faults comprises:

Establishing an application layer fault model and performing fault simulation on an application layer, wherein the application layer fault model comprises an integrated navigation sensor fault, a flight control system fault and a steering engine fault;

Establishing a physical layer fault model and performing fault simulation on a physical layer, wherein the physical layer fault model comprises a signal-to-power short circuit, a signal-to-ground short circuit and an open circuit;

Establishing a protocol layer fault model and performing fault simulation on a protocol layer, wherein the protocol layer fault model comprises a serial communication bus electrical fault;

and establishing an electrical layer fault model at an electrical layer, and performing fault simulation, wherein the electrical layer fault model comprises power supply abnormality and signal fluctuation.

5. The method of claim 1, wherein the fault diagnosis includes at least one of a fault code, a fault location, a fault occurrence time, a fault type, and a fault handling measure.

6. The method of claim 1, wherein the obtaining a fault tree model of an aircraft comprises:

determining a top event, an intermediate event and a basic fault, wherein the top event is a main fault event of airborne equipment of an aircraft, the intermediate event is a specific fault event which causes the top event to occur, and the basic fault is a basic fault which causes the intermediate event to occur;

And generating the fault tree model according to the logic relation among the top event, the intermediate event and the basic fault.

7. An aircraft fault diagnosis system, the system comprising:

The fault expert knowledge base module is used for acquiring a fault tree model of the target aircraft and a fault code knowledge base, wherein the fault tree model represents each fault logic relation in the aircraft airborne equipment;

The fault simulation and injection module is used for carrying out fault simulation on the airborne equipment of the target aircraft according to a hierarchy based on a fault tree model and a fault code knowledge base of the target aircraft to obtain a fault simulation result, wherein the hierarchy comprises at least one of an application layer, a physical layer, a protocol layer and an electric layer;

And the fault diagnosis prototype module is used for carrying out real-time fault positioning and diagnosis based on the fault simulation result to obtain a fault diagnosis result.

8. The system of claim 7, wherein the fault simulation and injection module is further configured to inject the fault simulation result into a fault diagnosis prototype for simulating an aircraft on-board device via hardware interface resources and a hardware fault injection adaptation device.

9. The system of claim 7, wherein the fault expert knowledge base module is further configured to update the fault tree model and the fault code knowledge base based on the fault diagnosis results.

10. A computer device, comprising:

A memory and a processor in communication with each other, the memory having stored therein computer instructions which, upon execution, cause the processor to perform the method of any of claims 1 to 6.