An automated aircraft maintenance testing method and apparatus

Abstract

An automated aircraft maintenance testing method and apparatus are disclosed. In this invention, an aircraft maintenance testing process, such as an upward pressure test sequence and a downward pressure test sequence, is initiated when a valid wheel load signal is detected and the ground speed signal is less than a ground speed threshold. The upward pressure test sequence is executed when the hydraulic system is in operation, and the downward pressure test sequence is executed when the hydraulic system is not in operation. Thus, the system can automatically perform the corresponding maintenance tests.

Description

Technical Field

[0001] This invention relates to the field of aviation applications, and more particularly to an automated aircraft maintenance and testing method and apparatus. Background Technology

[0002] In the safety analysis of civil aircraft flight control systems, under the assumption of periodic detection of hidden faults, failure mode and effects analysis (FMEA) is used to obtain the failure probability of system equipment. Therefore, to ensure the effectiveness of system safety analysis, it is necessary to conduct regular inter-institutional maintenance tests (IBIT) to detect hidden faults.

[0003] Because the system has numerous monitors, the conditions for conducting related maintenance tests vary. For example, the Actuator Control Electronic Monitor (AMT) test aims to check whether the actuators in the AMT function as expected. During the test, some anticipated fault signals are injected into the monitor, and then the triggering of the relevant monitor is checked. Since these tests are only performed within the AMT, they only require power-on. Other tests, such as the rudder surface initialization self-test, require rudder surface movement to check whether the system's monitoring and execution are normal. Therefore, performing this type of maintenance test requires that the hydraulic system pressure value of the corresponding rudder surface meets the requirements for normal operation.

[0004] In summary, due to the varying time requirements and interconnected system needs for different types of system maintenance tests, traditional aircraft typically use maintenance documents to specify specific times for manual performance by maintenance personnel. According to data provided by domestic and international component manufacturers, periodic inspection intervals are generally 3 flight hours (FH), 20 FH, 30 FH, 200 FH, or 1000 FH. Therefore, requiring maintenance personnel to perform these tasks periodically not only places higher demands on personnel qualifications but also increases the aircraft maintenance workload and costs for airlines.

[0005] In existing technologies, performing periodic hidden fault detection and maintenance tests requires manual operation by maintenance personnel, which increases the maintenance test items for flight operations, as well as turnaround time and operating costs.

[0006] Therefore, there is a need in the art for an improved automated aircraft maintenance testing method and apparatus. Summary of the Invention

[0007] This invention proposes an improved automated aircraft maintenance testing method and apparatus.

[0008] Based on the flight control system, this invention adds an automated hidden fault detection and execution module to the flight control computer maintenance partition. It can automatically calculate and determine the time to execute hidden fault detection maintenance tests based on the aircraft flight status, hydraulic system status, and power system status. When the logic is met, the system will execute the corresponding maintenance test and provide relevant instructions for the crew or maintenance personnel.

[0009] In one embodiment of the present invention, an automated aircraft maintenance testing method is provided, comprising: detecting wheel load signals and ground speed signals of the aircraft; in response to detecting that the wheel load signals are valid and when the ground speed signals are less than a ground speed threshold, initiating an aircraft maintenance testing process, wherein the aircraft maintenance testing process includes an up-pressure test sequence and a down-pressure test sequence, the up-pressure test sequence including one or more test items requiring support from the aircraft hydraulic system, and the down-pressure test sequence including one or more test items not requiring support from the aircraft hydraulic system; determining the operating state of the aircraft hydraulic system; executing the up-pressure test sequence when the hydraulic system is in an operating state; and executing the down-pressure test sequence when the hydraulic system is in a non-operating state.

[0010] In one aspect, executing the uppressure test sequence includes: determining whether the detection periodicity of each test item in the uppressure test sequence is met, wherein if the detection periodicity of one or more test items is met, then the corresponding one or more test items are executed; if the detection periodicity of one or more test items is not met, then the corresponding one or more test items are not executed; and executing the downpressure test sequence includes: determining whether the detection periodicity of each test item in the downpressure test sequence is met, wherein if the detection periodicity of one or more test items is met, then the corresponding one or more test items are executed; if the detection periodicity of one or more test items is not met, then the corresponding one or more test items are not executed.

[0011] On one hand, the test items in the up-pressure test sequence and the down-pressure test sequence each have a corresponding detection periodicity. When the flight hours since the last execution of the test item reach the threshold range of its corresponding detection periodicity, it is determined that the detection periodicity of the test item is met and the test item is executed.

[0012] On one hand, the test items in the pressure test sequence are executed sequentially or concurrently according to their respective detection cycles, and the test items in the pressure test sequence are executed sequentially or concurrently according to their respective detection cycles.

[0013] In one aspect, the test items in the up-pressure test sequence and the down-pressure test sequence each include injecting a test signal into a target device of the aircraft to detect the response of the target device.

[0014] In one aspect, the automated aircraft maintenance testing method further includes: after initiating the aircraft maintenance testing process, exiting the aircraft maintenance testing process in response to the ground speed signal exceeding the exit threshold.

[0015] On one hand, the pressure test sequence includes one or more of the following: control surface initialization self-test; actuator initialization test.

[0016] In one aspect, the pressure test sequence includes one or more of the following: actuator control electronic monitor test; remote control electronic initialization self-test; motor control electronic initialization test.

[0017] In one respect, the automated aircraft maintenance testing method is performed after the aircraft transitions from the air phase to the landing phase.

[0018] In another embodiment of the present invention, an automated aircraft maintenance testing apparatus is provided, comprising: a memory for storing processor-executable instructions; and a processor coupled to the memory, the processor being configured to implement the fault tree construction method as described in any of the preceding claims when executing the processor-executable instructions.

[0019] In another embodiment of the present invention, an automated aircraft maintenance testing apparatus is provided, comprising: a maintainability condition detection module configured to detect wheel load signals and ground speed signals of the aircraft; a detection initiation module configured to initiate an aircraft maintenance testing process in response to detecting that the wheel load signals are valid and when the ground speed signals are less than a ground speed threshold, wherein the aircraft maintenance testing process includes an uppressure test sequence and a downpressure test sequence, the uppressure test sequence including one or more test items requiring support from the aircraft hydraulic system, and the downpressure test sequence including one or more test items not requiring support from the aircraft hydraulic system; a hydraulic condition detection module configured to determine the operating state of the aircraft's hydraulic system; and a testing module configured to execute the uppressure test sequence when the hydraulic system is in an operating state, and to execute the downpressure test sequence when the hydraulic system is in a non-operating state.

[0020] In one aspect, the test module executing the up-pressure test sequence includes: determining whether the detection periodicity of each test item in the up-pressure test sequence is met, wherein if the detection periodicity of one or more test items is met, then the corresponding one or more test items are executed; if the detection periodicity of one or more test items is not met, then the corresponding one or more test items are not executed; and the test module executing the down-pressure test sequence includes: determining whether the detection periodicity of each test item in the down-pressure test sequence is met, wherein if the detection periodicity of one or more test items is met, then the corresponding one or more test items are executed; if the detection periodicity of one or more test items is not met, then the corresponding one or more test items are not executed.

[0021] On one hand, the test items in the up-pressure test sequence and the down-pressure test sequence each have a corresponding detection periodicity. When the flight hours since the last execution of the test item reach the threshold range of its corresponding detection periodicity, it is determined that the detection periodicity of the test item is met and the test item is executed.

[0022] On one hand, the test items in the pressure test sequence are executed sequentially or concurrently according to their respective detection cycles, and the test items in the pressure test sequence are executed sequentially or concurrently according to their respective detection cycles.

[0023] In one aspect, the test items in the up-pressure test sequence and the down-pressure test sequence each include injecting a test signal into a target device of the aircraft to detect the response of the target device.

[0024] On one hand, the detection initiation module is configured to: after initiating the aircraft maintenance detection process, exit the aircraft maintenance detection process in response to the ground speed signal exceeding the exit threshold.

[0025] On one hand, the pressure test sequence includes one or more of the following: control surface initialization self-test; actuator initialization test.

[0026] In one aspect, the pressure test sequence includes one or more of the following: actuator control electronic monitor test; remote control electronic initialization self-test; motor control electronic initialization test.

[0027] In another embodiment of the present invention, a fly-by-wire flight control system is provided, including an automated aircraft maintenance and testing apparatus as described in any of the preceding claims. Attached Figure Description

[0028] Figure 1 This is a flowchart of an automated aircraft maintenance testing method according to an embodiment of the present invention.

[0029] Figure 2 This is a logic diagram of initiating an aircraft maintenance and testing process according to an embodiment of the present invention.

[0030] Figure 3 This is a logic diagram of starting a test project according to an embodiment of the present invention.

[0031] Figure 4 This is a schematic diagram of automated aircraft maintenance testing according to an embodiment of the present invention.

[0032] Figure 5 This is a block diagram of an automated aircraft maintenance and testing apparatus according to an embodiment of the present invention. Detailed Implementation

[0033] The present invention will be further described below with reference to specific embodiments and accompanying drawings, but this should not be construed as limiting the scope of protection of the present invention.

[0034] This invention proposes an improved automated aircraft maintenance testing method and apparatus. Based on the flight control system, this invention adds an automated hidden fault detection and execution module to the flight control computer's maintenance section. This module can automatically calculate and determine the execution time for hidden fault detection maintenance tests based on the aircraft's flight status, hydraulic system status, and power system status. When the logic is met, the system will execute the corresponding maintenance test and provide relevant instructions for the flight crew or maintenance personnel.

[0035] Figure 1 This is a flowchart of an automated aircraft maintenance testing method 100 according to an embodiment of the present invention. The automated aircraft maintenance testing method 100 may be executed by a fly-by-wire flight control system or its components (e.g., a flight control computer), or by a computer, processor, integrated circuit, or other device.

[0036] Considering that maintenance tests may introduce signals into the system manually or automatically, the flight control system needs to suppress the initiation of maintenance tests during normal operation. Preferably, method 100 can be performed when the aircraft is taxiing on the ground or in a stopped state.

[0037] Optionally, in step 102, it can be determined whether the aircraft has transitioned from the air phase to the landing phase or is on the ground. If the aircraft has entered the landing phase or is on the ground, subsequent steps can be performed. Conversely, if the aircraft is preparing for takeoff or is in the air phase, subsequent steps can be avoided.

[0038] In step 104, the aircraft's wheel-mounted signals and ground speed signals can be detected. Wheel-mounted signals refer to the wheel-mounted status signals of the aircraft's landing system, which can be used to determine whether the aircraft is on the ground or in the air. Wheel-mounted signals can be measured by wheel-mounted sensors. Ground speed signals indicate the aircraft's speed relative to the ground, and can be measured by ground navigation stations, GPS, etc., or calculated from airspeed and altitude.

[0039] In step 106, it is determined whether the wheel-mounted signal is valid and whether the ground speed signal is less than the ground speed threshold. A valid wheel-mounted signal indicates that the aircraft is on the ground, while an invalid wheel-mounted signal indicates that the aircraft is in the air. A ground speed signal less than the ground speed threshold indicates that the ground speed is less than a specified threshold speed, thus meeting the speed conditions for entering maintenance testing.

[0040] In response to the detection of a valid wheel-mounted signal and a ground speed signal below a ground speed threshold, an aircraft maintenance inspection process can be initiated in step 108. This process may include one or more test items. After initiating the process, it can be determined whether the conditions for executing each test item are met, ensuring that each test item is executed only after its corresponding conditions are satisfied. In one embodiment, the aircraft maintenance inspection process may include an upward pressure test sequence and a downward pressure test sequence. The upward pressure test sequence may include one or more test items requiring support from the aircraft's hydraulic system, while the downward pressure test sequence may include one or more test items not requiring support from the aircraft's hydraulic system. Each test item in the upward and downward pressure test sequences includes injecting a test signal into a target device on the aircraft to detect the target device's response.

[0041] As an example and not a limitation, the pressurization test sequence includes one or more of the following: control surface initialization self-test, which can detect whether the system's monitoring and execution are normal through control surface movement; actuator initialization test, which can detect whether the internal components / mechanisms (such as sensors) of the actuator are normal by injecting actuator signals; and other pressurization tests.

[0042] The downforce test sequence includes one or more of the following: actuator control electronics monitor test, which can detect whether the actuators in the actuator control electronics are working as expected; remote control electronics initialization self-test, which can detect whether the monitors in the remote control electronics are working as expected; motor control electronics initialization test, which can detect whether the relevant monitors in the motor control electronics and flight control computer are working as expected; and other downforce tests, etc.

[0043] In step 110, the operating status of the aircraft's hydraulic system can be determined. The hydraulic system may be in an operating state or a non-operating state.

[0044] In step 112, when the hydraulic system is in operation, a pressure test sequence can be executed. Executing the pressure test sequence includes determining whether the detection periodicity of each test item in the pressure test sequence is met. If the detection periodicity of one or more test items is met, then the corresponding one or more test items are executed. If the detection periodicity of one or more test items is not met, then the corresponding one or more test items are not executed.

[0045] In step 114, when the hydraulic system is in a non-operating state, a pressure test sequence can be executed. Executing the pressure test sequence includes determining whether the detection periodicity of each test item in the pressure test sequence is met. If the detection periodicity of one or more test items is met, then the corresponding one or more test items are executed. If the detection periodicity of one or more test items is not met, then the corresponding one or more test items are not executed.

[0046] In one embodiment, each test item in the up-pressure test sequence and down-pressure test sequence has a corresponding detection periodicity. The system can maintain a timer for each test item, the timer indicating the flight hours since the last execution of the test item. In one embodiment, when the flight hours since the last execution of the test item reach its corresponding detection periodicity, it is determined that the detection periodicity of the test item is met and the test item is executed. In another embodiment, when the flight hours since the last execution of the test item reach a threshold range of its corresponding detection periodicity, it is determined that the detection periodicity of the test item is met and the test item is executed.

[0047] In one embodiment, the test items in the pressure test sequence or the pressure test sequence may be executed sequentially according to their respective detection periodicity. By way of example and not limitation, the pressure test sequence and the pressure test sequence may each include multiple test items arranged in a predetermined order. This predetermined order may be a priority order of the test items, a default order of the test items, a time order of the test items (e.g., according to a countdown of the detection period), etc. When executing the pressure test sequence or the pressure test sequence, the detection periodicity of each test item may be determined sequentially according to this predetermined order. If it is satisfied, the corresponding test item is executed; otherwise, the process proceeds to the next test item until the end of the test sequence.

[0048] In one embodiment, some test items in the up-pressure test sequence or down-pressure test sequence can be executed concurrently according to their respective detection periodicity. For example, if the system supports the concurrent execution of two or more test items, it can be determined concurrently whether the detection periodicity of the two or more test items is met, and if so, the corresponding test item is executed.

[0049] In one embodiment, test items in the up-pressure test sequence or down-pressure test sequence can be executed concurrently in batches according to their respective testing periodicity. For example, a first batch of test items, which includes two or more test items that can be executed concurrently, can be executed first, followed by a second batch of test items, which includes two or more test items that can be executed concurrently, and so on.

[0050] Optionally, the automated aircraft maintenance testing method 100 may further include: after initiating the aircraft maintenance testing process, exiting the aircraft maintenance testing process in response to a ground speed signal exceeding an exit threshold. For example, the aircraft's ground speed signal can be continuously tracked, and after initiating the aircraft maintenance testing process in step 108, if a ground speed signal exceeding an exit threshold is detected, the aircraft maintenance testing process can be exited.

[0051] Optionally, the automated aircraft maintenance testing method 100 may also include recording the execution status and / or results of each test item. For example, if a test item indicates that the corresponding test target has failed, a warning message may be provided.

[0052] Figure 2 This is a logic diagram of initiating an aircraft maintenance and testing process according to an embodiment of the present invention. The present invention can be implemented through multiple logic modules: a logic module for determining whether maintenance can be entered, a hidden fault detection initiation module, and a test signal injection module.

[0053] As mentioned above, considering that maintenance tests may inject signals into the system manually or automatically, the flight control system needs to suppress the entry into maintenance testing during normal use. In one embodiment, the system is only allowed to enter maintenance mode after the aircraft has landed and the ground speed is below a certain value, at which point the control surface efficiency is almost zero, and subsequent maintenance tests may be initiated. This ensures that the initiation of maintenance tests will not have any unsafe impact on the aircraft or flight control system.

[0054] This is an example, not a limitation. Figure 2 The logical relationship for determining whether maintenance can be entered is given. 'Maintenance can be entered' is true when all of the following conditions are met:

[0055] 1) Both the wheel-mounted signal and the ground speed signal are valid;

[0056] 2) The ground speed (a) is lower than the entry threshold (b), preferably for a duration exceeding a threshold time (e.g., 1 second or other time), while the ground speed signal does not meet the exit threshold (c).

[0057] Preferably, the exit threshold (c) is higher than the entry threshold (b) to avoid repeatedly entering or exiting the maintenance test process.

[0058] In an alternative embodiment, the 'access to maintenance state' condition may be true only if the following additional conditions are met:

[0059] 3) The wheel-mounted signal is valid and true, while the radio altitude signal (d) is valid and its value is less than the threshold value (e), and the airspeed signal (g) is valid and its value is less than the airspeed threshold (g), preferably for a duration exceeding a threshold time (e.g., 10 seconds or other time).

[0060] Figure 3 This is a logic diagram of starting a test project according to an embodiment of the present invention.

[0061] In one embodiment of the present invention, based on the cycle of hidden fault detection in the security analysis, an instruction to perform relevant maintenance tests is issued when logical conditions are met.

[0062] Three main points need to be considered when automatically conducting hidden fault detection. First, in safety analysis, the periodic detection requirements for each hidden fault may be different, so the detection time for each hidden fault needs to be calculated separately. Second, some tests need to be carried out under hydraulic system pressure, so the pressure value of the hydraulic system needs to be determined for these tests. Finally, if multiple hidden fault detections need to be performed after this sortie, they can be completed sequentially to prevent them from interfering with each other and causing the detection to fail.

[0063] Figure 3 The logical relationship of the hidden fault detection startup module is given.

[0064] As described above, a timer can be maintained for each test item, indicating the flight hours since the last execution of that test item. Subtracting these flight hours from the detection periodicity yields the remaining detection time (j) for that test item. In another embodiment, a timer (e.g., a countdown) can also be maintained for the remaining detection time, initialized to the detection periodicity, from which the remaining detection time for each flight is subtracted to obtain the remaining detection time for that test item.

[0065] In one embodiment, when the remaining detection time (j) is less than the next flight time (k, or a specified threshold time k), it indicates that the test item should be performed before the next flight. In another embodiment, the test item can also be determined to be performed after the remaining detection time is less than or equal to 0. That is, when the flight hours since the last execution of the test item reach its corresponding detection periodicity (or within the threshold range of its corresponding detection periodicity), it is determined that the detection periodicity of the test item is met and the test item is performed.

[0066] For the test items in the upper pressure test sequence, the corresponding test item can be performed if the hydraulic system pressure (m) is greater than (or equal to) the pressure threshold (n) for which the test can be performed. For the test items in the lower pressure test sequence, the corresponding test item can be performed if the hydraulic system pressure (m) is less than the pressure threshold (n) for which the test can be performed.

[0067] For test items that are executed sequentially, the next maintenance test item X+1 can be started after the previous maintenance test item X is completed (for example, determine whether to execute X+1 and act accordingly).

[0068] For hidden fault detection and maintenance testing, the traditional manual steps need to be replaced by automatic injection in the flight control computer software. At the same time, the integrity requirements of the injected signal must be considered to prevent erroneous signal injection from increasing the system's failure modes.

[0069] Traditional methods for detecting hidden faults require maintenance personnel to manually perform certain operations, which must be confirmed by the maintenance system before proceeding to the next step. The detection process is only complete after all operations are finished. This invention, to achieve automation, allows for the configuration of a corresponding test signal injection module within the maintenance system. When the maintenance test program runs, relevant parameters can be injected as needed, thereby automating the detection process.

[0070] Figure 4 This is a schematic diagram of automated aircraft maintenance testing according to an embodiment of the present invention.

[0071] An aircraft's flight phases may include takeoff, cruise, descent, approach, landing, taxiing, and parking, among which cruise, descent, and approach are considered air phases.

[0072] After the aircraft completes its flight, it will taxi from the landing point to the apron along the runway at a speed of approximately 20-30 km / h. At this time, at least one engine is running, and at least one hydraulic system maintains pressure sufficient for normal operation of the aircraft's control surfaces. When the aircraft meets the logic for entering a maintenance-ready state during the low-speed taxiing phase, the concealed fault detection initiation module will sequentially determine whether to initiate any tests in the pressure test sequence, such as X1, X2, X3, etc. Once the concealed fault detection X1 initiation command is issued, the maintenance partition in the flight control computer will start the concealed fault detection X1 program and simultaneously call parameters from the test signal injection module as needed, completing the entire concealed fault detection X1 process. Next, it will determine whether to initiate concealed fault detection X2, continuing until the pressure phase test is completed.

[0073] After the aircraft taxis to the parking apron, the crew will shut down the engines and hydraulic system. The concealed fault detection initiation module will then sequentially determine whether to initiate any of the test items in the down-pressure test sequence, such as Y1, Y2, Y3, etc. When the concealed fault detection Y1 initiation test command is issued, the maintenance partition in the flight control computer will start the concealed fault detection Y1 program and simultaneously call parameters from the test signal injection module as needed to complete the entire concealed fault detection Y1 process. Next, it will determine whether to initiate concealed fault detection Y2, until the down-pressure phase test is completed.

[0074] Although Figure 4 The illustration shows the sequential execution of the pressure test sequence and the pressure test sequence at the end of a flight. However, in other embodiments, the pressure test sequence and the pressure test sequence may be executed in different ways. For example, when the aircraft is not performing a flight mission, automated aircraft maintenance tests as described herein may be performed, which may execute the pressure test sequence and the pressure test sequence depending on the set environment, such as executing the pressure test sequence first and then the pressure test sequence, or executing the pressure test sequence first and then the pressure test sequence, or executing one of the pressure test sequence and the pressure test sequence alone, etc.

[0075] Figure 5 This is a block diagram of an automated aircraft maintenance and testing apparatus 500 according to an embodiment of the present invention. The automated aircraft maintenance and testing apparatus 500 may be executed by a fly-by-wire flight control system 520 or its components (e.g., a flight control computer), or by a computer, processor, integrated circuit, or other device.

[0076] The automated aircraft maintenance testing device 500 may include a maintainability detection module 502, which is configured to detect the aircraft's wheel load signals and ground speed signals, for example, to determine whether the aircraft can enter a maintainable state.

[0077] The automated aircraft maintenance testing apparatus 500 may further include a detection initiation module 504, configured to initiate an aircraft maintenance testing process in response to the detection of a valid wheel load signal and a ground speed signal below a ground speed threshold (e.g., when the maintainable condition detection module 502 indicates that the aircraft can enter a maintainable state). The aircraft maintenance testing process includes an uppressure test sequence and a downpressure test sequence. The uppressure test sequence includes one or more test items requiring support from the aircraft's hydraulic system, and the downpressure test sequence includes one or more test items not requiring support from the aircraft's hydraulic system.

[0078] The automated aircraft maintenance testing device 500 may also include a hydraulic condition detection module 506, which is configured to determine the operating status of the aircraft's hydraulic system.

[0079] The automated aircraft maintenance test apparatus 500 may also include a test module 508 configured to perform an up-pressure test sequence when the hydraulic system is in operation and a down-pressure test sequence when the hydraulic system is not in operation.

[0080] The test module 508 may execute the up-pressure test sequence by: determining whether the detection periodicity of each test item in the up-pressure test sequence is met, wherein if the detection periodicity of one or more test items is met, the corresponding one or more test items are executed; if the detection periodicity of one or more test items is not met, the corresponding one or more test items are not executed.

[0081] The test module 508 may execute the pressure test sequence by: determining whether the detection periodicity of each test item in the pressure test sequence is met, wherein if the detection periodicity of one or more test items is met, the corresponding one or more test items are executed; if the detection periodicity of one or more test items is not met, the corresponding one or more test items are not executed.

[0082] In one embodiment, the test items in the uppressure test sequence and the downpressure test sequence each have a corresponding detection periodicity, wherein when the flight hours since the last execution of the test item reach the threshold range of its corresponding detection periodicity, it is determined that the detection periodicity of the test item is met and the test item is executed.

[0083] In one embodiment, the test items in the uppressure test sequence are executed sequentially or concurrently by the test module 508 according to their respective detection periods, and the test items in the downpressure test sequence are executed sequentially or concurrently by the test module 508 according to their respective detection periods.

[0084] In one embodiment, the test items in the uppressure test sequence and the downpressure test sequence each include injecting a test signal into the target equipment of the aircraft to detect the response of the target equipment.

[0085] The detection initiation module 504 can also be configured to exit the aircraft maintenance detection process after initiating the process, in response to a ground speed signal exceeding the exit threshold.

[0086] The automated aircraft maintenance test apparatus 500 may also include other modules not shown, such as memory, processor, bus, etc.

[0087] The present invention has at least one or more of the following advantages:

[0088] a) An automated aircraft maintenance and testing method applicable to various aircraft with flight control systems using digital bus communication, i.e., aircraft with digital fly-by-wire flight control systems.

[0089] b) It can simplify the operation of maintenance personnel and realize the automated detection of hidden faults;

[0090] c) By using signals such as wheel load signals and hydraulic system pressure to determine the maintenance test start command, the detection of hidden faults can be integrated into the taxiing and engine shutdown phases after each aircraft lands, which greatly simplifies the operation of maintenance personnel and reduces aircraft operating costs.

[0091] The various steps and modules of the methods and apparatus described above can be implemented in hardware, software, or a combination thereof. If implemented in hardware, the various illustrative steps, modules, and circuits described in connection with this disclosure can be implemented or executed using a general-purpose processor, digital signal processor (DSP), application-specific integrated circuit (ASIC), field-programmable gate array (FPGA), or other programmable logic components, hardware components, or any combination thereof. A general-purpose processor can be a processor, microprocessor, controller, microcontroller, or state machine, etc. If implemented in software, the various illustrative steps and modules described in connection with this disclosure can be stored as one or more instructions or codes on a computer-readable medium or transmitted. Software modules implementing the various operations of this disclosure can reside in a storage medium, such as RAM, flash memory, ROM, EPROM, EEPROM, registers, hard disk, removable disk, CD-ROM, cloud storage, etc. The storage medium can be coupled to a processor so that the processor can read and write information from / to the storage medium and execute corresponding program modules to implement the various steps of this disclosure. Moreover, software-based embodiments can be uploaded, downloaded, or remotely accessed through appropriate communication means. Such appropriate means of communication include, for example, the Internet, the World Wide Web, intranets, software applications, cables (including fiber optic cables), magnetic communication, electromagnetic communication (including RF, microwave and infrared communication), electronic communication, or other such means of communication.

[0092] The numerical values ​​given in the various embodiments are merely examples and are not intended to limit the scope of the invention. In practice, the specific parameters of each component can be appropriately set as needed, and are not limited to the specific values ​​given as examples herein. Furthermore, as a whole, there are other components or steps not listed in the claims or specification of this invention. Moreover, a single name for a component does not preclude other names for that component.

[0093] It should also be noted that these embodiments may be described as processes depicted as flowcharts, flow diagrams, structure diagrams, or block diagrams. Although a flowchart may describe the operations as a sequential process, many of these operations can be executed in parallel or concurrently. Furthermore, the order of these operations can be rearranged.

[0094] The disclosed methods, apparatuses, and systems should not be limited in any way. Rather, this disclosure covers all novel and non-obvious features and aspects of the various disclosed embodiments (individually and in various combinations and sub-combinations of each other). The disclosed methods, apparatuses, and systems are not limited to any particular aspect or feature or combination thereof, and no disclosed embodiment is required to have any one or more specific advantages or to solve any particular or all technical problems.

[0095] This invention is not limited to the specific embodiments described above. The specific embodiments described above are merely illustrative and not restrictive. Those skilled in the art can make many other modifications based on the teachings of this invention without departing from the spirit and scope of the claims. All of these modifications are within the scope of protection of this invention.

Claims

1. An automated aircraft maintenance testing method, characterized in that, include: Detect the aircraft's wheel load signals and ground speed signals; In response to the detection of the wheel load signal being valid and when the ground speed signal is less than the ground speed threshold, an aircraft maintenance inspection process is initiated, wherein the aircraft maintenance inspection process includes an upper pressure test sequence and a lower pressure test sequence, the upper pressure test sequence including one or more test items that require support from the aircraft hydraulic system, and the lower pressure test sequence including one or more test items that do not require support from the aircraft hydraulic system. Determine the operating status of the aircraft's hydraulic system; The pressure test sequence is executed while the hydraulic system is in operation. as well as The pressure test sequence is performed when the hydraulic system is not in operation.

2. The automated aircraft maintenance testing method as described in claim 1, characterized in that: Executing the up-pressure test sequence includes: determining whether the detection periodicity of each test item in the up-pressure test sequence is met, wherein if the detection periodicity of one or more test items is met, then the corresponding one or more test items are executed; if the detection periodicity of one or more test items is not met, then the corresponding one or more test items are not executed; and Executing the pressure test sequence includes: determining whether the detection periodicity of each test item in the pressure test sequence is met, wherein if the detection periodicity of one or more test items is met, then the corresponding one or more test items are executed; if the detection periodicity of one or more test items is not met, then the corresponding one or more test items are not executed.

3. The automated aircraft maintenance testing method as described in claim 2, wherein the test items in the upper pressure test sequence and the lower pressure test sequence each have a corresponding detection periodicity, wherein when the flight hours since the last execution of the test item reach the threshold range of its corresponding detection periodicity, it is determined that the detection periodicity of the test item is met and the test item is executed.

4. The automated aircraft maintenance testing method as described in claim 3, wherein the test items in the upper pressure test sequence are executed sequentially or concurrently according to their respective detection cycles, and the test items in the lower pressure test sequence are executed sequentially or concurrently according to their respective detection cycles.

5. The automated aircraft maintenance testing method as claimed in claim 1, wherein the test items in the uppressure test sequence and the downpressure test sequence each include injecting a test signal into a target device of the aircraft to detect the response of the target device.

6. The automated aircraft maintenance testing method as described in claim 1, characterized in that, Also includes: After the aircraft maintenance and inspection process is initiated, the process is terminated in response to the ground speed signal exceeding the exit threshold.

7. The automated aircraft maintenance testing method as described in claim 1, wherein the pressure test sequence includes one or more of the following: Control surface initialization self-test; Actuator initialization detection.

8. The automated aircraft maintenance testing method as described in claim 1, wherein the pressure test sequence includes one or more of the following: Actuator control electronic monitor test; Remote control electronic initialization self-test; Motor control electronics initialization test.

9. The automated aircraft maintenance testing method as claimed in claim 1, wherein the automated aircraft maintenance testing method is performed after the aircraft enters the landing phase from the air phase.

10. An automated aircraft maintenance and testing device, comprising: Memory is used to store processor-executable instructions; as well as A processor coupled to the memory, wherein the processor, when executing processor-executable instructions, is configured to implement the automated aircraft maintenance testing method as described in any one of claims 1-9.

11. An automated aircraft maintenance and testing device, characterized in that, include: A maintainable condition detection module is configured to detect the aircraft's wheel load signals and ground speed signals; A detection initiation module is configured to initiate an aircraft maintenance detection process in response to the detection of a valid wheel load signal and when the ground speed signal is less than a ground speed threshold. The aircraft maintenance detection process includes an upper pressure test sequence and a lower pressure test sequence. The upper pressure test sequence includes one or more test items that require support from the aircraft hydraulic system, and the lower pressure test sequence includes one or more test items that do not require support from the aircraft hydraulic system. A hydraulic condition detection module is configured to determine the operating status of the aircraft's hydraulic system; as well as A test module is configured to perform the pressure-up test sequence when the hydraulic system is in an operational state, and to perform the pressure-down test sequence when the hydraulic system is in a non-operational state.

12. The automated aircraft maintenance and testing device as described in claim 11, characterized in that: The test module executes the up-pressure test sequence by: determining whether the detection periodicity of each test item in the up-pressure test sequence is met, wherein if the detection periodicity of one or more test items is met, then the corresponding one or more test items are executed; if the detection periodicity of one or more test items is not met, then the corresponding one or more test items are not executed; and The test module executes the pressure test sequence by: determining whether the detection periodicity of each test item in the pressure test sequence is met, wherein if the detection periodicity of one or more test items is met, then the corresponding one or more test items are executed; if the detection periodicity of one or more test items is not met, then the corresponding one or more test items are not executed.

13. The automated aircraft maintenance testing apparatus of claim 12, wherein the test items in the upper pressure test sequence and the lower pressure test sequence each have a corresponding detection periodicity, wherein when the flight hours since the last execution of the test item reach the threshold range of its corresponding detection periodicity, it is determined that the detection periodicity of the test item is met and the test item is executed.

14. The automated aircraft maintenance testing apparatus of claim 13, wherein the test items in the upper pressure test sequence are executed sequentially or concurrently according to their respective detection cycles, and the test items in the lower pressure test sequence are executed sequentially or concurrently according to their respective detection cycles.

15. The automated aircraft maintenance testing apparatus of claim 11, wherein the test items in the uppressure test sequence and the downpressure test sequence each include injecting a test signal into a target device of the aircraft to detect the response of the target device.

16. The automated aircraft maintenance and testing apparatus as described in claim 11, characterized in that, The detection startup module is configured to: After the aircraft maintenance and inspection process is initiated, the process is terminated in response to the ground speed signal exceeding the exit threshold.

17. The automated aircraft maintenance testing apparatus of claim 11, wherein the pressure test sequence comprises one or more of the following: Control surface initialization self-test; Actuator initialization detection.

18. The automated aircraft maintenance testing apparatus of claim 11, wherein the pressure test sequence comprises one or more of the following: Actuator control electronic monitor test; Remote control electronic initialization self-test; Motor control electronics initialization test.

19. A fly-by-wire flight control system, comprising an automated aircraft maintenance and testing apparatus as described in any one of claims 11-18.

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