Method and device for determining fault position of aircraft reverse thrust system and aircraft

Abstract

The invention provides a method and a device for determining a fault position of a reverse thrust system of an aircraft and the aircraft. The method comprises the following steps: receiving fault warning information of a reverse thrust system; wherein the fault alarm information comprises a fault type; the reverse thrust system comprises an aircraft airborne system, an aircraft reverse thrust control system and an aircraft reverse thrust actuation system; detecting whether the fault type is that the reverse thrust system cannot be expanded or not; under the condition that the fault type is determined to be that the reverse thrust system cannot be unfolded, receiving an input signal sent by an aircraft airborne system; detecting the input signal to obtain a first detection result; and under the condition that the first detection result is unqualified, determining that the fault position is located in the airborne system of the aircraft. Based on the method, comprehensive fault position detection can be carried out on the reverse thrust system, and the detection efficiency is improved.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft fault detection, and in particular to a method and device for determining a fault position of an aircraft reverse thrust system, and an aircraft. Background Art

[0002] The reverse thrust system in an aircraft can provide negative thrust to the aircraft when it lands or aborts takeoff to slow down the aircraft and reduce the taxiing distance. There are many devices and controllers in the reverse thrust system. In the prior art, fault detection is usually only performed on a certain controller or device, and there is a lack of a comprehensive fault detection solution for the entire reverse thrust system, which makes it impossible to quickly and accurately locate the location of the fault. Summary of the invention

[0003] The present application provides a method and device for determining the fault position of an aircraft reverse thrust system, and an aircraft, so as to solve the technical problem that the position where the fault occurs cannot be quickly and accurately located.

[0004] In a first aspect, the present application provides a method for determining a fault location of an aircraft reverse thrust system, the method comprising:

[0005] Receiving fault warning information of a reverse thrust system; wherein the fault warning information includes a fault type; the reverse thrust system includes: an aircraft onboard system, an aircraft reverse thrust control system, and an aircraft reverse thrust actuation system;

[0006] Detecting whether the fault type is that the reverse thrust system cannot be deployed;

[0007] In the case where it is determined that the fault type is that the reverse thrust system cannot be deployed, receiving an input signal sent by the aircraft onboard system;

[0008] Detecting the input signal to obtain a first detection result;

[0009] In the case where the first detection result includes a failure, it is determined that the fault location is located in the aircraft onboard system.

[0010] In some embodiments, the aircraft onboard system includes: a landing gear system, a throttle lever system, and a navigation system;

[0011] The input signals include: a wheel load signal generated by a landing gear system, a throttle lever angle signal generated by a throttle lever system, and a radio altitude signal generated by a navigation system;

[0012] Detecting the input signal to obtain a first detection result includes:

[0013] Detecting whether the wheel load signal is equal to a first preset value, and obtaining a wheel load signal detection result;

[0014] Detecting whether the throttle lever angle signal is less than a second preset value, and obtaining a throttle lever angle signal detection result;

[0015] Detecting whether the radio altitude signal is less than a third preset value, and obtaining a radio altitude signal detection result;

[0016] The wheel load signal detection result, the throttle lever angle signal detection result, and the radio altitude signal detection result are combined to obtain a first detection result.

[0017] In some embodiments, after detecting the input signal and obtaining the first detection result, the method further includes:

[0018] When the first detection results are all qualified, receiving a control signal sent by the aircraft reverse thrust control system;

[0019] Detecting the control signal to obtain a second detection result;

[0020] In the case where the second detection result includes a failure, it is determined that the fault location is located in the aircraft reverse thrust control system.

[0021] In some embodiments, the aircraft reverse thrust control system includes: an engine controller, an engine interface controller, and a flight control computer;

[0022] Detecting the control signal to obtain a second detection result includes:

[0023] Detecting whether the control signal sent by the engine controller is equal to a fourth preset value, and obtaining a first control signal detection result;

[0024] Detecting whether the control signal sent by the engine interface controller is equal to a fourth preset value, and obtaining a second control signal detection result;

[0025] Detecting whether the control signal sent by the flight control computer is equal to a fourth preset value, and obtaining a third control signal detection result;

[0026] The first control signal detection result, the second control signal detection result, and the third control signal detection result are combined to obtain a second detection result.

[0027] In some embodiments, after detecting whether the fault type is that the thrust reverser system cannot be deployed, the method further includes:

[0028] When it is determined that the fault type is that the reverse thrust system cannot be retracted, receiving a throttle lever angle signal sent by the aircraft onboard system;

[0029] Detecting the throttle lever angle signal to obtain a throttle lever angle signal detection result;

[0030] When the throttle lever angle signal detection result includes failure, it is determined that the fault location is located in the throttle lever system in the aircraft onboard system.

[0031] In some embodiments, after detecting the throttle lever angle signal and obtaining a throttle lever angle signal detection result, the method further includes:

[0032] When the throttle lever angle signal detection result includes qualified, receiving a control signal sent by the aircraft reverse thrust control system;

[0033] Detecting the control signal to obtain a second detection result;

[0034] In the case where the second detection result includes a failure, it is determined that the fault location is located in the aircraft reverse thrust control system.

[0035] In some embodiments, the aircraft reverse thrust control system includes: an engine controller, an engine interface controller, and a flight control computer;

[0036] Detecting the control signal to obtain a second detection result includes:

[0037] Detecting whether the control signal sent by the engine controller is equal to a fifth preset value, and obtaining a first control signal detection result;

[0038] Detecting whether the control signal sent by the engine interface controller is equal to a fifth preset value, and obtaining a second control signal detection result;

[0039] Detecting whether the control signal sent by the flight control computer is equal to a fifth preset value, and obtaining a third control signal detection result;

[0040] The first control signal detection result, the second control signal detection result, and the third control signal detection result are combined to obtain a second detection result.

[0041] In some embodiments, after detecting the control signal and obtaining a second detection result, the method further includes: when the second detection results are all qualified, determining that the fault location is located in the aircraft reverse thrust actuation system; wherein the aircraft reverse thrust actuation system includes a displacement sensor, a motor, a motor controller, and a screw actuator.

[0042] In a second aspect, the present application further proposes a device for determining a fault position of an aircraft reverse thrust system, the device comprising:

[0043] A first receiving module is used to receive fault warning information of a reverse thrust system; wherein the fault warning information includes a fault type; the reverse thrust system includes: an aircraft onboard system, an aircraft reverse thrust control system, and an aircraft reverse thrust actuation system;

[0044] A first detection module is used to detect whether the fault type is that the reverse thrust system cannot be deployed;

[0045] A second receiving module is used to receive an input signal sent by the aircraft onboard system when it is determined that the fault type is that the reverse thrust system cannot be deployed;

[0046] A second detection module, used to detect the input signal to obtain a first detection result;

[0047] The determination module is used to determine that the fault location is located in the aircraft onboard system when the first detection result includes failure.

[0048] In a third aspect, the present application further proposes an aircraft, wherein the aircraft is equipped with electronic equipment, wherein the electronic equipment includes a processor and a memory for storing instructions executable by the processor, and when the processor executes the instructions, the steps of any of the above-mentioned methods for determining the fault location of the aircraft reverse thrust system are implemented.

[0049] In a fourth aspect, the present application further proposes a storage medium having computer instructions stored thereon, which, when executed by a processor, implement the steps of any of the above-mentioned methods for determining the fault location of an aircraft reverse thrust system.

[0050] The present application can achieve the following beneficial effects: the present application regards the reverse thrust system as a whole, and formulates corresponding fault location detection methods for the two different fault types of the reverse thrust system being unable to be deployed and the reverse thrust system being unable to be retracted, respectively, so as to conduct a comprehensive detection of the reverse thrust system, which can cover most of the fault scenarios of the reverse thrust system and expand the scope of fault location detection; and the process does not require manual troubleshooting, which reduces the requirements for the technical capabilities of maintenance personnel, saves time and cost for troubleshooting, and improves the efficiency of fault location detection. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0052] Figure 1A schematic flow chart of a method for determining a fault location of an aircraft reverse thrust system provided in an embodiment of the present application;

[0053] Figure 2 A structural schematic diagram of a reverse thrust fault detection system provided in an embodiment of the present application;

[0054] Figure 3 A structural schematic diagram of a reverse thrust fault detection system provided in an embodiment of the present application;

[0055] Figure 4 A schematic structural diagram of a device for determining a fault position of an aircraft reverse thrust system provided in an embodiment of the present application;

[0056] Figure 5 A schematic flow chart of a method for determining a fault location of an aircraft reverse thrust system provided in an embodiment of the present application. DETAILED DESCRIPTION

[0057] The technical solutions in the embodiments of the present application will be described clearly and completely below in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0058] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the term "and / or" in this article is only a description of the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. In addition, the character " / " in this article, unless otherwise specified, generally indicates that the associated objects before and after are in an "or" relationship.

[0059] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0060] The reverse thrust system in an aircraft can provide negative thrust to the aircraft when it lands or aborts takeoff to slow down the aircraft and reduce the taxiing distance. There are many devices and controllers in the reverse thrust system. In the prior art, fault detection is usually only performed on a certain controller or device, and there is a lack of a comprehensive fault detection solution for the entire reverse thrust system, which makes it impossible to quickly and accurately locate the location of the fault.

[0061] The present application proposes a method, a device and an aircraft for determining a fault position of an aircraft reverse thrust system, which can quickly locate the fault position in the aircraft reverse thrust system.

[0062] A method, device and aircraft for determining the fault location of an aircraft reverse thrust system provided by the present application are introduced below in conjunction with the accompanying drawings.

[0063] In some embodiments, please refer to Figure 1 The present application proposes a method for determining the fault location of an aircraft reverse thrust system. The reverse thrust system is an electric reverse thrust system. In specific implementation, the method may include the following contents.

[0064] S101: Receive fault warning information of a reverse thrust system; wherein the fault warning information includes a fault type; the reverse thrust system includes: an aircraft onboard system, an aircraft reverse thrust control system, and an aircraft reverse thrust actuation system.

[0065] In some embodiments, the failure type includes one of the following: the thrust reverser system cannot be deployed, and the thrust reverser system cannot be retracted.

[0066] S102: Detect whether the fault type is that the reverse thrust system cannot be deployed.

[0067] In some embodiments, the present application adopts different methods to determine the fault location for two different fault types: the reverse thrust system cannot be deployed and the reverse thrust system cannot be retracted.

[0068] S103: When it is determined that the fault type is that the reverse thrust system cannot be deployed, receiving an input signal sent by the aircraft onboard system.

[0069] In some embodiments, the aircraft onboard system includes: a landing gear system, a throttle lever system, and a navigation system. The input signal includes: a wheel load signal generated by the landing gear system, a throttle lever angle signal generated by the throttle lever system, and a radio altitude signal generated by the navigation system.

[0070] S104: Detect the input signal to obtain a first detection result.

[0071] In some embodiments, detecting the input signal to obtain a first detection result specifically includes:

[0072] S1: Detect whether the wheel load signal is equal to a first preset value, and obtain a wheel load signal detection result;

[0073] S2: Detect whether the throttle lever angle signal is less than a second preset value, and obtain a throttle lever angle signal detection result;

[0074] S3: Detect whether the radio altitude signal is less than a third preset value, and obtain a radio altitude signal detection result;

[0075] S4: Combining the wheel load signal detection result, the throttle lever angle signal detection result, and the radio altitude signal detection result to obtain a first detection result.

[0076] In some embodiments, the first preset value may be set equal to 1. In the case where there is no fault in the landing gear system, the landing gear system may generate a wheel load signal equal to 1. In the case where there is a fault in the landing gear system, the landing gear system may generate a wheel load signal equal to 0. Therefore, in the case where the wheel load signal is equal to the first preset value, the wheel load signal detection result is determined to be qualified; in the case where the wheel load signal is not equal to the first preset value (that is, the wheel load signal is equal to 0), the wheel load signal detection result is determined to be unqualified.

[0077] In some embodiments, the second preset value may be set equal to the "reverse thrust position". When the throttle lever angle signal is less than the reverse thrust position, the throttle lever angle signal detection result is determined to be qualified; when the throttle lever angle signal is greater than or equal to the reverse thrust position, the throttle lever angle signal detection result is determined to be unqualified.

[0078] In some embodiments, the third preset value may be set equal to 6 feet. When the radio altitude signal is less than the third preset value, the radio altitude signal detection result is determined to be qualified; when the radio altitude signal is greater than or equal to the third preset value, the radio altitude signal detection result is determined to be unqualified.

[0079] S105: When the first detection result includes failure, determine that the fault location is located in the aircraft onboard system.

[0080] In some embodiments, it is further detected whether the first detection result includes "failure", and if the first detection result includes failure, it is determined that the fault location is located in the aircraft onboard system.

[0081] In some embodiments, if the wheel load signal detection result is unqualified, the fault location is located in the landing gear system. If the throttle lever angle signal detection result is unqualified, the fault location is located in the throttle lever system. If the radio altitude signal detection result is unqualified, the fault location is located in the navigation system.

[0082] In some embodiments, if the first detection results are all "qualified", the fault location is located in the aircraft reverse thrust control system or the aircraft reverse thrust actuation system.

[0083] In some embodiments, after detecting the input signal and obtaining the first detection result, the method further includes:

[0084] S1: When the first detection results are all qualified, receiving a control signal sent by the aircraft reverse thrust control system;

[0085] S2: Detect the control signal to obtain a second detection result;

[0086] S3: When the second detection result includes a failure, determining that the fault location is located in the aircraft reverse thrust control system.

[0087] In some embodiments, the aircraft reverse thrust control system includes: an engine controller, an engine interface controller, and a flight control computer. The control signal specifically includes: a control signal sent by the engine controller, a control signal sent by the engine interface controller, and a control signal sent by the flight control computer.

[0088] In some embodiments, detecting the control signal to obtain a second detection result specifically includes:

[0089] S1: Detect whether the control signal sent by the engine controller is equal to a fourth preset value, and obtain a first control signal detection result;

[0090] S2: Detect whether the control signal sent by the engine interface controller is equal to a fourth preset value, and obtain a second control signal detection result;

[0091] S3: Detect whether the control signal sent by the flight control computer is equal to a fourth preset value, and obtain a third control signal detection result;

[0092] S4: Combine the first control signal detection result, the second control signal detection result, and the third control signal detection result to obtain a second detection result.

[0093] In some embodiments, the fourth preset value can be set equal to 1. When the control signal sent by the engine controller is equal to the fourth preset value, the first control signal detection result is determined to be qualified; when the control signal sent by the engine controller is not equal to the fourth preset value, the first control signal detection result is determined to be unqualified. When the control signal sent by the engine interface controller is equal to the fourth preset value, the second control signal detection result is determined to be qualified; when the control signal sent by the engine interface controller is not equal to the fourth preset value, the second control signal detection result is determined to be unqualified. When the control signal sent by the flight control computer is equal to the fourth preset value, the third control signal detection result is determined to be qualified; when the control signal sent by the flight control computer is not equal to the fourth preset value, the third control signal detection result is determined to be unqualified.

[0094] In some embodiments, it is further detected whether the second detection result includes "failure". If the second detection result includes "failure", it is determined that the fault location is located in the aircraft reverse thrust control system.

[0095] In some embodiments, if the first control signal detection result is unqualified, the fault location is located in the engine controller. If the second control signal detection result is unqualified, the fault location is located in the engine interface controller. If the third control signal detection result is unqualified, the fault location is located in the flight control computer.

[0096] In some embodiments, the engine controller, engine interface controller, and flight control computer can be called three independent lines of defense. Each line of defense (i.e., each controller / computer) can generate a separate control signal, and different logics reside in different controllers. Therefore, it is necessary to test the engine controller, engine interface controller, and flight control computer separately to ensure the comprehensiveness of the detection.

[0097] In some embodiments, if the second detection results are all "qualified", it is determined that the fault location is located in the aircraft reverse thrust actuation system; wherein the aircraft reverse thrust actuation system includes a displacement sensor, a motor, a motor controller, and a screw actuator. Specifically, the displacement sensor is installed on the screw actuator. Further, the motor controller can be used to detect whether the motor and the motor controller itself are faulty, and the engine controller EEC can be used to detect whether the displacement sensor and the screw actuator are faulty, so as to determine the specific fault location and obtain the third detection result.

[0098] In some embodiments, after detecting whether the fault type is that the thrust reverser system cannot be deployed, the method further includes:

[0099] S201: When it is determined that the fault type is that the reverse thrust system cannot be retracted, receiving a throttle lever angle signal sent by the aircraft onboard system;

[0100] S202: Detecting the throttle lever angle signal to obtain a throttle lever angle signal detection result;

[0101] S203: When the throttle lever angle signal detection result includes failure, determining that the fault location is located in the throttle lever system in the aircraft onboard system.

[0102] In some embodiments, the throttle lever angle signal is detected to obtain a throttle lever angle signal detection result, specifically including:

[0103] S1: Check whether the throttle lever angle signal is at or above positive slow speed;

[0104] S2: when it is determined that the throttle lever angle signal is at or above positive slow speed, determining that the throttle lever angle signal detection result is qualified;

[0105] S3: When it is determined that the throttle lever angle signal is below the positive idle state, determining that the throttle lever angle signal detection result is unqualified.

[0106] In some embodiments, after detecting the throttle lever angle signal and obtaining a throttle lever angle signal detection result, the method further includes:

[0107] S1: receiving a control signal sent by the aircraft reverse thrust control system when the throttle lever angle signal detection result is qualified;

[0108] S2: Detect the control signal to obtain a second detection result;

[0109] S3: When the second detection result includes a failure, determining that the fault location is located in the aircraft reverse thrust control system.

[0110] In some embodiments, detecting the control signal to obtain a second detection result specifically includes:

[0111] S1: Detect whether the control signal sent by the engine controller is equal to a fifth preset value, and obtain a first control signal detection result;

[0112] S2: Detect whether the control signal sent by the engine interface controller is equal to a fifth preset value, and obtain a second control signal detection result;

[0113] S3: Detect whether the control signal sent by the flight control computer is equal to a fifth preset value, and obtain a third control signal detection result;

[0114] S4: Combine the first control signal detection result, the second control signal detection result, and the third control signal detection result to obtain a second detection result.

[0115] In some embodiments, the fifth preset value can be set equal to 0. When the control signal sent by the engine controller is equal to the fifth preset value, the first control signal detection result is determined to be qualified; when the control signal sent by the engine controller is not equal to the fifth preset value, the first control signal detection result is determined to be unqualified. When the control signal sent by the engine interface controller is equal to the fifth preset value, the second control signal detection result is determined to be qualified; when the control signal sent by the engine interface controller is not equal to the fifth preset value, the second control signal detection result is determined to be unqualified. When the control signal sent by the flight control computer is equal to the fifth preset value, the third control signal detection result is determined to be qualified; when the control signal sent by the flight control computer is not equal to the fifth preset value, the third control signal detection result is determined to be unqualified.

[0116] In some embodiments, it is further detected whether the second detection result includes "failure". If the second detection result includes "failure", it is determined that the fault location is located in the aircraft reverse thrust control system.

[0117] In some embodiments, if the first control signal detection result is unqualified, the fault location is located in the engine controller. If the second control signal detection result is unqualified, the fault location is located in the engine interface controller. If the third control signal detection result is unqualified, the fault location is located in the flight control computer.

[0118] In some embodiments, if the second detection results are all "qualified", it is determined that the fault location is located in the aircraft reverse thrust actuation system; wherein the aircraft reverse thrust actuation system includes a displacement sensor, a motor, a motor controller, and a lead screw actuation cylinder. Specifically, the displacement sensor is installed on the lead screw actuation cylinder. Further, the motor controller can be used to detect whether the motor and the motor controller itself are faulty, and the engine controller EEC can be used to detect whether the displacement sensor and the lead screw actuation cylinder are faulty, so as to determine the specific fault location.

[0119] In some embodiments, the fault location may be sent to a display terminal for display to prompt maintenance personnel to repair the fault.

[0120] Based on the above embodiments, the present application regards the reverse thrust system as a whole, and formulates corresponding fault location detection methods for the two different fault types of the reverse thrust system being unable to be deployed and the reverse thrust system being unable to be retracted, respectively, so as to conduct a comprehensive detection of the reverse thrust system, which can cover most of the fault scenarios of the reverse thrust system and expand the scope of fault location detection; and the process does not require manual troubleshooting, which reduces the requirements on the technical capabilities of maintenance personnel, saves time and cost for troubleshooting, and improves the efficiency of fault location detection.

[0121] This application proposes an embodiment of a reverse thrust fault detection system, see Figure 2 As shown, the system includes: a central maintenance system OMS, a display terminal MFD, a throttle control component TCQ, an engine interface controller EICU, an engine controller EEC, and a reverse thrust system controller TRCU. The central maintenance system OMS is respectively connected to or electrically connected with the display terminal MFD, the throttle control component TCQ, the engine interface controller EICU, the engine controller EEC, and the reverse thrust system controller TRCU. The above-mentioned method for determining the fault position of the aircraft reverse thrust system can be applied to the central maintenance system OMS. The central maintenance system OMS can receive data and signals sent by the throttle control component TCQ, the engine interface controller EICU, the engine controller EEC, and the reverse thrust system controller TRCU. Specifically, the central maintenance system OMS can receive control signals sent by the engine interface controller EICU and control signals sent by the engine controller EEC, and then execute the above-mentioned method for determining the fault position of the aircraft reverse thrust system to determine the fault position. The central maintenance system OMS can also send the fault position to the display terminal MFD for display.

[0122] This application proposes another embodiment of a reverse thrust fault detection system, see Figure 3 As shown, the central maintenance system OMS is respectively connected to or electrically connected with the display terminal MFD, the engine interface controller EICU, and the engine controller EEC. The throttle control component TCQ and the reverse thrust system controller TRCU are connected to the engine controller EEC. The throttle control component TCQ and the reverse thrust system controller TRCU communicate with the central maintenance system OMS through the engine controller EEC.

[0123] For a specific scenario example, see Figure 5As shown, the fault warning information of the reverse thrust system is received, and the fault warning information includes the fault type. It is detected whether the fault type is that the reverse thrust system cannot be deployed. In the case where the fault type is that the reverse thrust system cannot be deployed, an input signal sent by the aircraft airborne system is received; the input signal is detected to obtain a first detection result. It is detected whether the first result includes "unqualified". In the case where it is determined that the first detection result includes "unqualified", it is determined that the fault location is located in the aircraft airborne system. In the case where it is determined that the first detection result does not include "unqualified" (that is, the first detection results are all qualified), a control signal sent by the aircraft reverse thrust control system is received, and the control signal is detected to obtain a second detection result. It is detected whether the second result includes "unqualified". In the case where the second detection result includes "unqualified", it is determined that the fault location is located in the aircraft reverse thrust control system. In the case where the second detection result does not include "unqualified" (that is, the second detection results are all qualified), it is determined that the fault location is located in the aircraft reverse thrust actuation system. When the fault type is that the reverse thrust system cannot be retracted, the throttle lever angle signal sent by the aircraft onboard system is received; the throttle lever angle signal is detected to obtain the throttle lever angle signal detection result. When the throttle lever angle signal detection result includes unqualified, it is determined that the fault position is located in the throttle lever system in the aircraft onboard system. When the throttle lever angle signal detection result does not include unqualified (that is, the throttle lever angle signal detection result is qualified), the control signal sent by the aircraft reverse thrust control system is received; the control signal is detected to obtain a second detection result. It is detected whether the second result includes "unqualified". When the second detection result includes "unqualified", it is determined that the fault position is located in the aircraft reverse thrust control system. When the second detection result does not include "unqualified" (that is, the second detection result is qualified), it is determined that the fault position is located in the aircraft reverse thrust actuation system.

[0124] Based on the above-mentioned method for determining a fault position of an aircraft reverse thrust system, one or more embodiments of the present application further provide a device for determining a fault position of an aircraft reverse thrust system. Figure 4 It is a structural schematic diagram of an embodiment of a fault location determination device for an aircraft reverse thrust system provided by the present application. The fault location determination device for an aircraft reverse thrust system provided by the present application may include: a first receiving module 401, a first detection module 402, a second receiving module 403, a second detection module 404, and a determination module 405.

[0125] The first receiving module 401 is used to receive fault warning information of the reverse thrust system; wherein the fault warning information includes the fault type; the reverse thrust system includes: an aircraft onboard system, an aircraft reverse thrust control system, and an aircraft reverse thrust actuation system;

[0126] A first detection module 402 is used to detect whether the fault type is that the reverse thrust system cannot be deployed;

[0127] The second receiving module 403 is used to receive an input signal sent by the aircraft onboard system when it is determined that the fault type is that the reverse thrust system cannot be deployed;

[0128] A second detection module 404, configured to detect the input signal and obtain a first detection result;

[0129] The determination module 405 is used to determine that the fault location is located in the aircraft onboard system when the first detection result includes failure.

[0130] In some embodiments, the device also includes a first processing module, which is used to receive a control signal sent by the aircraft reverse thrust control system when the first detection results are all qualified; detect the control signal to obtain a second detection result; and when the second detection result includes an unqualified result, determine that the fault location is located in the aircraft reverse thrust control system.

[0131] In some embodiments, the device also includes a second processing module, which is used to receive a throttle lever angle signal sent by the aircraft's onboard system when it is determined that the fault type is that the reverse thrust system cannot be retracted; detect the throttle lever angle signal to obtain a throttle lever angle signal detection result; and when the throttle lever angle signal detection result includes an unqualified result, determine that the fault location is located in the throttle lever system in the aircraft's onboard system.

[0132] In some embodiments, the device also includes a third processing module, which is used to determine that the fault location is located in the aircraft reverse thrust actuation system when the second detection results are all qualified; wherein the aircraft reverse thrust actuation system includes a displacement sensor, a motor, a motor controller, and a screw actuator.

[0133] It should be noted that the above-mentioned device may also include other implementation modes according to the description of the method embodiment. The specific implementation mode may refer to the description of the relevant method embodiment, which will not be described one by one here.

[0134] The present application also provides an electronic device, comprising at least one processor and a memory for storing processor executable instructions, wherein the processor can implement any one of the above method embodiments when executing the instructions. For example, when the instructions are executed by the processor, the following steps are implemented: receiving fault warning information of the reverse thrust system; wherein the fault warning information includes the fault type; the reverse thrust system includes: an aircraft onboard system, an aircraft reverse thrust control system, and an aircraft reverse thrust actuation system; detecting whether the fault type is that the reverse thrust system cannot be deployed; in the case where it is determined that the fault type is that the reverse thrust system cannot be deployed, receiving an input signal sent by the aircraft onboard system; detecting the input signal to obtain a first detection result; in the case where the first detection result includes an unqualified result, determining that the fault location is located in the aircraft onboard system.

[0135] In addition, the logic instructions in the above-mentioned memory can be implemented in the form of software functional units and can be stored in a computer-readable storage medium when sold or used as an independent product. Based on this understanding, the technical solution of the present application can be essentially or partly embodied in the form of a software product that contributes to the prior art, and the computer software product is stored in a storage medium, including several instructions to enable a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present application. The aforementioned storage medium includes: various media that can store program codes, such as a USB flash drive, a mobile hard disk, a read-only memory (ROM), a random access memory (RAM), a disk or an optical disk.

[0136] It should be noted that the electronic device described above may also include other implementations according to the description of the method or device embodiment. The specific implementation methods may refer to the description of the relevant method embodiment, which will not be described one by one here.

[0137] The present application also provides an aircraft, wherein the aircraft is equipped with electronic equipment, wherein the electronic equipment includes a processor and a memory for storing instructions executable by the processor, and when the processor executes the instructions, an embodiment of any one of the above-mentioned methods for determining the fault location of the aircraft reverse thrust system is implemented.

[0138] The present application also provides a storage medium, which is a computer-readable storage medium, and the storage medium stores computer program instructions, which, when executed, implement: receiving fault warning information of a reverse thrust system; wherein the fault warning information includes a fault type; the reverse thrust system includes: an aircraft onboard system, an aircraft reverse thrust control system, and an aircraft reverse thrust actuation system; detecting whether the fault type is that the reverse thrust system cannot be deployed; in the case where it is determined that the fault type is that the reverse thrust system cannot be deployed, receiving an input signal sent by the aircraft onboard system; detecting the input signal to obtain a first detection result; in the case where the first detection result includes an unqualified result, determining that the fault location is located in the aircraft onboard system.

[0139] The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative labor.

[0140] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the prior art can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0141] In summary, although the present application has been disclosed as above with preferred embodiments, the above preferred embodiments are not intended to limit the present application. Ordinary technicians in this field can make various changes and modifications without departing from the spirit and scope of the present application. Therefore, the scope of protection of the present application shall be based on the scope defined in the claims.

Claims

1. A method for determining a fault location of an aircraft reverse thrust system, characterized in that: The method comprises: Receiving fault warning information of a reverse thrust system; wherein the fault warning information includes a fault type; the reverse thrust system includes: an aircraft onboard system, an aircraft reverse thrust control system, and an aircraft reverse thrust actuation system; Detecting whether the fault type is that the reverse thrust system cannot be deployed; In the case where it is determined that the fault type is that the reverse thrust system cannot be deployed, receiving an input signal sent by the aircraft onboard system; Detecting the input signal to obtain a first detection result; In the case where the first detection result includes a failure, it is determined that the fault location is located in the aircraft onboard system.

2. The method according to claim 1, characterized in that The aircraft onboard system includes: a landing gear system, a throttle lever system, and a navigation system; The input signals include: a wheel load signal generated by a landing gear system, a throttle lever angle signal generated by a throttle lever system, and a radio altitude signal generated by a navigation system; Detecting the input signal to obtain a first detection result includes: Detecting whether the wheel load signal is equal to a first preset value, and obtaining a wheel load signal detection result; Detecting whether the throttle lever angle signal is less than a second preset value, and obtaining a throttle lever angle signal detection result; Detecting whether the radio altitude signal is less than a third preset value, and obtaining a radio altitude signal detection result; The wheel load signal detection result, the throttle lever angle signal detection result, and the radio altitude signal detection result are combined to obtain a first detection result.

3. The method according to claim 1, characterized in that After detecting the input signal and obtaining a first detection result, the method further includes: When the first detection results are all qualified, receiving a control signal sent by the aircraft reverse thrust control system; Detecting the control signal to obtain a second detection result; In the case where the second detection result includes a failure, it is determined that the fault location is located in the aircraft reverse thrust control system.

4. The method according to claim 3, characterized in that: The aircraft reverse thrust control system includes: an engine controller, an engine interface controller, and a flight control computer; Detecting the control signal to obtain a second detection result includes: Detecting whether the control signal sent by the engine controller is equal to a fourth preset value, and obtaining a first control signal detection result; Detecting whether the control signal sent by the engine interface controller is equal to a fourth preset value, and obtaining a second control signal detection result; Detecting whether the control signal sent by the flight control computer is equal to a fourth preset value, and obtaining a third control signal detection result; The first control signal detection result, the second control signal detection result, and the third control signal detection result are combined to obtain a second detection result.

5. The method according to claim 1, characterized in that: After detecting whether the fault type is that the thrust reverser system cannot be deployed, the method further includes: When it is determined that the fault type is that the reverse thrust system cannot be retracted, receiving a throttle lever angle signal sent by the aircraft onboard system; Detecting the throttle lever angle signal to obtain a throttle lever angle signal detection result; When the throttle lever angle signal detection result includes failure, it is determined that the fault location is located in the throttle lever system in the aircraft onboard system.

6. The method according to claim 5, characterized in that After detecting the throttle lever angle signal and obtaining a throttle lever angle signal detection result, the method further includes: When the throttle lever angle signal detection result includes qualified, receiving a control signal sent by the aircraft reverse thrust control system; Detecting the control signal to obtain a second detection result; In the case where the second detection result includes a failure, it is determined that the fault location is located in the aircraft reverse thrust control system.

7. The method according to claim 6, characterized in that The aircraft reverse thrust control system includes: an engine controller, an engine interface controller, and a flight control computer; Detecting the control signal to obtain a second detection result includes: Detecting whether the control signal sent by the engine controller is equal to a fifth preset value, and obtaining a first control signal detection result; Detecting whether the control signal sent by the engine interface controller is equal to a fifth preset value, and obtaining a second control signal detection result; Detecting whether the control signal sent by the flight control computer is equal to a fifth preset value, and obtaining a third control signal detection result; The first control signal detection result, the second control signal detection result, and the third control signal detection result are combined to obtain a second detection result.

8. The method according to claim 3 or 6, characterized in that: After detecting the control signal to obtain a second detection result, the method further includes: When the second detection results are all qualified, it is determined that the fault position is located in the aircraft reverse thrust actuation system; wherein the aircraft reverse thrust actuation system includes a displacement sensor, a motor, a motor controller, and a lead screw actuation cylinder.

9. A device for determining a fault position of an aircraft reverse thrust system, characterized in that: The device comprises: A first receiving module is used to receive fault warning information of a reverse thrust system; wherein the fault warning information includes a fault type; the reverse thrust system includes: an aircraft onboard system, an aircraft reverse thrust control system, and an aircraft reverse thrust actuation system; A first detection module is used to detect whether the fault type is that the reverse thrust system cannot be deployed; A second receiving module is used to receive an input signal sent by the aircraft onboard system when it is determined that the fault type is that the reverse thrust system cannot be deployed; A second detection module, used to detect the input signal to obtain a first detection result; The determination module is used to determine that the fault location is located in the aircraft onboard system when the first detection result includes failure.

10. A storage medium, characterized in that: Computer instructions are stored thereon, and when the instructions are executed by a processor, the steps of the method according to any one of claims 1 to 8 are implemented.

11. An aircraft, characterized in that: The aircraft is equipped with electronic equipment, which includes a processor and a memory for storing processor-executable instructions. When the processor executes the instructions, the steps of the method described in any one of claims 1 to 8 are implemented.

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