Airplane flap and slat section testing system, method, equipment and medium

Abstract

The invention discloses an aircraft flap and slat section test system, method and device and a medium. The system comprises a motor controller, a motor driver, a motor and a computer. The motor controller is connected with the motor driver; the computer is connected with the motor driver; the motor driver is connected with the motor; the motor controller is used for transmitting a motor driving signal to the motor driver; the computer is used for transmitting a test signal corresponding to the flaps and slats of the airplane to the motor driver; and the motor driver is used for controlling the torque of a torsion bar on the motor according to the motor driving signal and the test signal. According to the technical scheme of the embodiment of the invention, the integrated system for carrying out the section test on the flaps and the slats of the airplane is provided, faults of the wings of the airplane can be found at the section level, and the testing efficiency of the flaps and the slats of the airplane is improved.

Description

Technical Field

[0001] The embodiments of the present invention relate to the technical field of substations, and in particular, to an aircraft flap and slat section test system, method, device, and medium. Background Art

[0002] Currently, the system installation and functional testing of aircraft wings are concentrated in the final assembly stage. The final assembly work cycle is long, the task volume is large, and fault problems are not discovered at the section level, resulting in the shift of faults and affecting the final assembly efficiency. In order to develop a typical wing section modular process system, achieve demonstration verification, and greatly improve the production efficiency and quality of civil aircraft final assembly, it is necessary to conduct research on the test drive device for the aircraft flap and slat for section testing.

[0003] However, in the prior art, there is a lack of an effective integrated testing method that can achieve section testing of the aircraft flap and slat for the adaptive flexible assembly requirements of the aircraft in multiple delivery states. Summary of the Invention

[0004] The embodiments of the present invention provide an aircraft flap and slat section test system, method, device, and medium, which can discover faults in aircraft wings at the section level, improve the test efficiency of aircraft flaps and slats, and ensure the production efficiency and quality of aircraft final assembly.

[0005] In a first aspect, the embodiments of the present invention provide an aircraft flap and slat section test system, including a motor controller, a motor driver, a motor, and a computer;

[0006] The motor controller is connected to the motor driver; the computer is connected to the motor driver; the motor driver is connected to the motor;

[0007] The motor controller is configured to transmit a motor drive signal to the motor driver;

[0008] The computer is configured to transmit a test signal corresponding to the aircraft flap and slat component to the motor driver;

[0009] The motor driver is configured to control the torque of the torsion bar on the motor according to the motor drive signal and the test signal.

[0010] Optionally, the system further includes a programmable logic controller;

[0011] The programmable logic controller is connected to the motor controller and is configured to control the business logic of the motor controller.

[0012] Optionally, the system further includes a power supply device;

[0013] The power supply device is connected to the motor driver and is configured to supply power to the motor driver.

[0014] Optionally, the power supply device includes a power source, a circuit breaker, an electromagnetic contactor, and an electromagnetic interference filter.

[0015] In a second aspect, an embodiment of the present invention further provides a method for testing an aircraft flap and slat section. The method is applied to the motor driver provided in any embodiment and includes:

[0016] Receiving a motor drive signal and a test signal transmitted by a motor controller and a computer respectively;

[0017] Controlling the torque of the torsion bar on the motor according to the motor drive signal and the test signal, so that the motor controls the movement of the wing movable surface actuator rod through the torsion bar.

[0018] Optionally, controlling the torque of the torsion bar on the motor according to the motor drive signal and the test signal includes:

[0019] Controlling the torque of the torsion bar on the motor in a pulse control mode according to the motor drive signal and the test signal.

[0020] Optionally, after controlling the torque of the torsion bar on the motor according to the motor drive signal and the test signal, so that the motor controls the movement of the wing movable surface actuator rod through the torsion bar, it further includes:

[0021] Determining the test results corresponding to the aircraft flap and slat under different test items according to the movement results of the wing movable surface actuator rod;

[0022] The test items include main flight control movable surface test and flap and slat movable surface test.

[0023] In a third aspect, an embodiment of the present invention further provides a testing device for an aircraft flap and slat section. The device is applied to the motor driver provided in any embodiment and includes:

[0024] A signal receiving module, configured to receive a motor drive signal and a test signal transmitted by a motor controller and a computer respectively;

[0025] A torque control module, configured to control the torque of the torsion bar on the motor according to the motor drive signal and the test signal, so that the motor controls the movement of the wing movable surface actuator rod through the torsion bar.

[0026] In a fourth aspect, an embodiment of the present invention further provides an electronic device, and the electronic device includes:

[0027] One or more processors;

[0028] A storage device, configured to store one or more programs;

[0029] When the one or more programs are executed by the one or more processors, the one or more processors execute the aircraft flap and slat segment testing method provided by any embodiment of the present invention.

[0030] In a fifth aspect, an embodiment of the present invention further provides a computer-readable storage medium, on which a computer program is stored, and when the program is executed by a processor, it implements the aircraft flap and slat segment testing method provided by any embodiment of the present invention.

[0031] The technical solution of the embodiment of the present invention transmits the motor drive signal to the motor driver through the motor controller, transmits the test signal corresponding to the aircraft flap and slat component to the motor driver through the computer, and controls the torque of the torsion bar on the motor according to the motor drive signal and the test signal through the motor driver, providing an integrated system for segment testing of aircraft flaps and slats, which can detect faults in aircraft wings at the segment level and improve the testing efficiency of aircraft flaps and slats. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1a is a schematic structural diagram of an aircraft flap and slat segment testing system in Embodiment 1 of the present invention;

[0033] Figure 1b is a schematic structural diagram of a motor in Embodiment 1 of the present invention;

[0034] Figure 1c is a schematic installation diagram corresponding to the aircraft flap and slat segment testing system in Embodiment 1 of the present invention;

[0035] Figure 2a is a schematic structural diagram of an aircraft flap and slat segment testing system in Embodiment 2 of the present invention;

[0036] Figure 2b is a schematic structural diagram of a power supply device in Embodiment 2 of the present invention;

[0037] Figure 3 is a flowchart of an aircraft flap and slat segment testing method in Embodiment 3 of the present invention;

[0038] Figure 4 is a schematic structural diagram of an aircraft flap and slat segment testing device in Embodiment 4 of the present invention;

[0039] Figure 5 is a schematic structural diagram of an electronic device in Embodiment 5 of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0040] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It can be understood that the specific embodiments described herein are only for explaining the present invention, rather than limiting the present invention. Additionally, it should be noted that for the sake of description, only the parts related to the present invention rather than all the structures are shown in the drawings.

[0041] Embodiment 1

[0042] Figure 1a It is a schematic structural diagram of an aircraft flap and slat section test system provided in Embodiment 1 of the present invention. The aircraft flap and slat section test system includes a motor controller, a motor driver, a motor, and a computer.

[0043] In this embodiment, as Figure 1a shown, the motor controller is connected to the motor driver; the computer is connected to the motor driver; the motor driver is connected to the motor.

[0044] Among them, the motor controller is used to transmit a motor drive signal to the motor driver. The computer is used to transmit a test signal corresponding to the aircraft flap and slat component to the motor driver. The motor driver is used to control the torque of the torsion bar on the motor according to the motor drive signal and the test signal.

[0045] Optionally, the tester can generate a test instruction on the computer according to the actual test requirements of the aircraft flap and slat, and transmit the test signal corresponding to the test instruction to the motor driver through the computer.

[0046] In a specific embodiment, Figure 1b It can be a schematic structural diagram of the motor in this embodiment. A torsion bar is deployed on the motor, and the motor driver can control the motor to adjust the torque of the torsion bar. Among them, the power of the motor is 7.5KW, the rated speed is 2000rpm, and the rated torque is 48N·M. The reduction ratio of the reducer in the motor is 5:1, and the rated torque is 240N·M. The maximum torque corresponding to the torsion bar is 200N·M, the output rated speed is 420(±10%)rpm, and the AC380V voltage platform is used. The motor can be used to replace the power of the wing actuator to conduct a section test on the aircraft flap and slat to test the performance of the wing. By adjusting the output torque of the torsion bar on the motor, the wing angle change can be controlled.

[0047] In an implementation manner of this embodiment, Figure 1c It can be an installation schematic diagram corresponding to the aircraft flap and slat section test system in this embodiment. As Figure 1cAs shown, the above-mentioned motor and torsion bar can be installed on the device mounting bracket under the wing, connecting the wing movable surface actuator rod to the torsion bar. By controlling the torque of the torsion bar on the motor, the movement of the wing movable surface actuator rod can be controlled, thereby controlling the deflection angles of the trailing edge flap, leading edge slat, spoiler, etc., achieving the purpose of remote section flight control testing and wing section-level testing.

[0048] In this embodiment, through the aircraft flap and slat section test system, precise control of the torque and speed of the motor can be achieved, and the flight control angle test of the flap and slat components can be completed in sequence, and the section test of the aircraft flap and slat can be completed.

[0049] The technical solution provided by the embodiment of the present invention transmits the motor drive signal to the motor driver through the motor controller, transmits the test signal corresponding to the aircraft flap and slat components to the motor driver through the computer, and controls the torque of the torsion bar on the motor according to the motor drive signal and the test signal by the motor driver. A integrated system for section testing of aircraft flaps and slats is provided, which can discover faults in aircraft wings at the section level and improve the test efficiency of aircraft flaps and slats.

[0050] Embodiment Two

[0051] Figure 2a FIG. is a schematic structural diagram of an aircraft flap and slat section test system in the second embodiment of the present invention. This embodiment is refined based on the above embodiment. In this embodiment, the system further includes a Programmable Logic Controller (PLC), which is connected to the motor controller for controlling the business logic of the motor controller. The system further includes a power supply device; the power supply device is connected to the motor driver for providing power to the motor driver.

[0052] In this embodiment, optionally, the motor driver can adopt a pulse control mode to precisely control the torque of the torsion bar on the motor. By using the programmable logic controller to control the business logic of the motor controller, the section test of the aircraft flap and slat can be quickly and effectively carried out, improving the test efficiency and the reliability of the test results.

[0053] In a specific embodiment, the computer and the motor driver can be connected through a short-distance wireless communication mechanism (such as a Bluetooth module or an infrared module, etc.) or a long-distance wireless communication mechanism (such as WIFI, mobile data or Ethernet, etc.) to remotely and precisely control the motor.

[0054] In an implementation manner of this embodiment, Figure 2b FIG. is a schematic structural diagram of a power supply device in this embodiment, asFigure 2b As shown, the power supply device may include a power source, a circuit breaker, an electromagnetic contactor, and an electromagnetic interference (EMI) filter for supplying power to the motor driver.

[0055] The technical solution provided by the embodiment of the present invention controls the service logic of the motor controller through a programmable logic controller, transmits the motor drive signal to the motor driver through the motor controller, transmits the test signal corresponding to the aircraft flap component to the motor driver through the computer, supplies power to the motor driver through the power supply device, and controls the torque of the torsion bar on the motor according to the motor drive signal and the test signal, providing an integrated system for segment testing of the aircraft flap, which can detect faults in the aircraft wing at the segment level and improve the test efficiency of the aircraft flap.

[0056] Embodiment III

[0057] Figure 3 It is a flowchart of a method for segment testing of an aircraft flap provided by Embodiment III of the present invention. This embodiment is applicable to the situation of segment testing of an aircraft flap. This method can be executed by the motor driver in the aircraft flap segment testing system. The method specifically includes the following steps:

[0058] Step 310: Receive the motor drive signal and the test signal transmitted by the motor controller and the computer respectively.

[0059] In this step, the motor driver can receive the motor drive signal (such as a switch signal, etc.) transmitted by the motor controller, and at the same time can also receive the test signal transmitted by the computer. The test signal can be generated by the tester on the computer according to the actual test requirements for the aircraft flap.

[0060] Step 320: Control the torque of the torsion bar on the motor according to the motor drive signal and the test signal, so that the motor controls the movement of the actuator rod of the wing moving surface through the torsion bar.

[0061] In this step, the actuator rod of the wing moving surface can be connected to the torsion bar. By controlling the torque of the torsion bar on the motor, the movement of the actuator rod of the wing moving surface can be controlled, thereby controlling the deflection angles of the trailing edge flap, leading edge slat, spoiler, etc., achieving the purpose of remote segment flight control testing and wing segment level testing.

[0062] In an implementation manner of this embodiment, controlling the torque of the torsion bar on the motor according to the motor drive signal and the test signal includes: controlling the torque of the torsion bar on the motor in a pulse control mode according to the motor drive signal and the test signal.

[0063] In this embodiment, after controlling the torque of the torsion bar on the motor according to the motor drive signal and the test signal so that the motor controls the movement of the wing movable surface actuator through the torsion bar, it further includes: determining the test results corresponding to the aircraft flap slat under different test items according to the movement results of the wing movable surface actuator. Wherein, the test items include the main flight control movable surface test and the flap slat movable surface test.

[0064] Specifically, the main flight control movable surface test mainly includes: aileron, multifunctional spoiler, ground spoiler and other tests. During the test, by using the aircraft flap slat section test system, the movement control of the main flight control and high-lift system movable surfaces of the aircraft wing can be realized.

[0065] The technical solution provided by the embodiment of the present invention, through the motor driver in the aircraft flap slat section test system, receives the motor drive signal and the test signal respectively transmitted by the motor controller and the computer, and controls the torque of the torsion bar on the motor according to the motor drive signal and the test signal, so that the motor controls the movement of the wing movable surface actuator through the torsion bar. By this technical means, the section test of the aircraft flap slat can be realized, faults of the aircraft wing can be found at the section level, the test efficiency of the aircraft flap slat can be improved, and the production efficiency and quality of the aircraft final assembly can be guaranteed.

[0066] Embodiment Four

[0067] Figure 4 It is a schematic structural diagram of an aircraft flap slat section test device provided by an embodiment of the present invention. The device is applied to the motor driver in the aircraft flap slat section test system, as Figure 4 shown, the device includes: a signal receiving module 410 and a torque control module 420.

[0068] The signal receiving module 410 is used to receive the motor drive signal and the test signal respectively transmitted by the motor controller and the computer;

[0069] The torque control module 420 is used to control the torque of the torsion bar on the motor according to the motor drive signal and the test signal, so that the motor controls the movement of the wing movable surface actuator through the torsion bar.

[0070] The technical solution provided by the embodiment of the present invention, through the motor driver in the aircraft flap and slat segment test system, receives the motor drive signal and the test signal transmitted by the motor controller and the computer respectively, and controls the torque of the torsion bar on the motor according to the motor drive signal and the test signal, so that the motor controls the movement of the wing movable surface actuator through the torsion bar, can realize the segment test of the aircraft flap and slat, can discover the faults of the aircraft wing at the segment level, improve the test efficiency of the aircraft flap and slat, and ensure the production efficiency and quality of the aircraft final assembly.

[0071] Based on the above embodiment, the torque control module 420 includes:

[0072] A pulse control unit, configured to control the torque of the torsion bar on the motor in a pulse control mode according to the motor drive signal and the test signal

[0073] A test result determination unit, configured to determine the test results corresponding to the aircraft flap and slat under different test items according to the movement results of the wing movable surface actuator; the test items include the main flight control movable surface test and the flap and slat movable surface test.

[0074] The above device can execute the methods provided by all the foregoing embodiments of the present invention, and has the corresponding functional modules and beneficial effects for executing the above methods. For the technical details not described in detail in the embodiments of the present invention, reference may be made to the methods provided by all the foregoing embodiments of the present invention.

[0075] Embodiment Five

[0076] Figure 5 The structural schematic diagram of the electronic device 10 that can be used to implement the embodiment of the present invention is shown. The electronic device is a motor driver in the aircraft flap and slat segment test system.

[0077] As Figure 5 shown, the electronic device 10 includes at least one processor 11, and a memory communicatively connected to at least one processor 11, such as a read-only memory (ROM) 12, a random access memory (RAM) 13, etc. Among them, the memory stores a computer program executable by at least one processor, and the processor 11 can execute various appropriate actions and processes according to the computer program stored in the read-only memory (ROM) 12 or the computer program loaded from the storage unit 18 into the random access memory (RAM) 13. In the RAM 13, various programs and data required for the operation of the electronic device 10 can also be stored. The processor 11, the ROM 12, and the RAM 13 are connected to each other through a bus 14. The input / output (I / O) interface 15 is also connected to the bus 14.

[0078] Multiple components in the electronic device 10 are connected to the I / O interface 15, including: an input unit 16, such as a keyboard, a mouse, etc.; an output unit 17, such as various types of displays, speakers, etc.; a storage unit 18, such as a disk, an optical disc, etc.; and a communication unit 19, such as a network card, a modem, a wireless communication transceiver, etc. The communication unit 19 allows the electronic device 10 to exchange information / data with other devices via a computer network such as the Internet and / or various telecommunication networks.

[0079] The processor 11 can be various general-purpose and / or special-purpose processing components with processing and computing capabilities. Some examples of the processor 11 include but are not limited to a central processing unit (CPU), a graphics processing unit (GPU), various dedicated artificial intelligence (AI) computing chips, various processors running machine learning model algorithms, a digital signal processor (DSP), and any suitable processor, controller, microcontroller, etc. The processor 11 executes the various methods and processes described above, such as the aircraft flap and slat section testing method.

[0080] In some embodiments, the aircraft flap and slat section testing method can be implemented as a computer program, which is tangibly contained in a computer-readable storage medium, such as the storage unit 18. In some embodiments, part or all of the computer program can be loaded and / or installed onto the electronic device 10 via the ROM 12 and / or the communication unit 19. When the computer program is loaded into the RAM 13 and executed by the processor 11, one or more steps of the aircraft flap and slat section testing method described above can be executed. Alternatively, in other embodiments, the processor 11 can be configured to execute the aircraft flap and slat section testing method in any other suitable manner (e.g., by means of firmware).

[0081] Various embodiments of the systems and techniques described above in this document can be implemented in digital electronic circuit systems, integrated circuit systems, field-programmable gate arrays (FPGA), application-specific integrated circuits (ASIC), application-specific standard products (ASSP), system-on-chip systems (SOC), complex programmable logic devices (CPLD), computer hardware, firmware, software, and / or combinations thereof. These various embodiments can include: implemented in one or more computer programs that can be executed and / or interpreted on a programmable system including at least one programmable processor, which can be a special or general programmable processor, and can receive data and instructions from a storage system, at least one input device, and at least one output device, and transmit the data and instructions to the storage system, the at least one input device, and the at least one output device.

[0082] A computer program for implementing the method of the present invention may be written in any combination of one or more programming languages. These computer programs can be provided to a processor of a general purpose computer, a special purpose computer, or other programmable data processing device, such that the computer programs, when executed by the processor, cause the functions / operations specified in the flowchart and / or block diagram to be implemented. The computer program may be executed entirely on the machine, partially on the machine, as a stand-alone software package partially on the machine and partially on a remote machine, or entirely on a remote machine or server.

[0083] In the context of the present invention, a computer-readable storage medium may be a tangible medium that can contain or store a computer program for use by or in connection with an instruction execution system, apparatus, or device. The computer-readable storage medium may include, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, apparatus, or devices, or any suitable combination of the foregoing. Alternatively, the computer-readable storage medium may be a machine-readable signal medium. More specific examples of the machine-readable storage medium would include an electrical connection based on one or more wires, a portable computer diskette, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or Flash memory), an optical fiber, a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.

[0084] In order to provide interaction with a user, the systems and techniques described herein may be implemented on an electronic device having: a display device (e.g., a CRT (cathode ray tube) or LCD (liquid crystal display) monitor) for displaying information to the user; and a keyboard and a pointing device (e.g., a mouse or a trackball) by which the user can provide input to the electronic device. Other kinds of devices may also be used to provide interaction with the user; for example, the feedback provided to the user may be any form of sensory feedback (e.g., visual feedback, auditory feedback, or tactile feedback); and input from the user may be received in any form (including acoustic input, voice input, or tactile input).

[0085] The systems and techniques described herein can be implemented in a computing system including backend components (e.g., as a data server), or a computing system including middleware components (e.g., an application server), or a computing system including frontend components (e.g., a user computer having a graphical user interface or a web browser through which a user can interact with an implementation of the systems and techniques described herein), or a computing system including any combination of such backend components, middleware components, or frontend components. The components of the system can be interconnected to each other by digital data communication in any form or medium (e.g., a communication network). Examples of communication networks include: local area network (LAN), wide area network (WAN), blockchain network, and the Internet.

[0086] A computing system can include a client and a server. The client and the server are generally far from each other and typically interact through a communication network. The client-server relationship is created by computer programs running on respective computers and having a client-server relationship with each other. The server can be a cloud server, also known as a cloud computing server or a cloud host, which is a host product in the cloud computing service system, and solves the defects of difficult management and weak business scalability existing in traditional physical hosts and VPS services.

[0087] It should be understood that various forms of the processes shown above can be used, with steps reordered, added, or deleted. For example, the steps recited in the present invention can be executed in parallel, sequentially, or in a different order, as long as the desired results of the technical solution of the present invention can be achieved, and no limitation is imposed herein.

[0088] The above specific embodiments do not constitute a limitation on the protection scope of the present invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations, and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. An aircraft flap and slat section test system, characterized in that It includes a motor controller, a motor driver, a motor, and a computer; The motor controller is connected to the motor driver; the computer is connected to the motor driver; the motor driver is connected to the motor; The motor controller is used to transmit a motor drive signal to the motor driver; The computer is used to transmit a test signal corresponding to an aircraft flap slat component to the motor driver; The motor driver is used to control the torque of the torsion bar on the motor according to the motor drive signal and the test signal.

2. The test system according to claim 1, characterized in that, The system further includes a programmable logic controller; The programmable logic controller is connected to the motor controller and is used to control the business logic of the motor controller.

3. The test system according to claim 1, wherein The system further includes a power supply device; The power supply device is connected to the motor driver and is used to supply power to the motor driver.

4. The test system according to claim 3, characterized in that, The power supply device includes a power source, a circuit breaker, an electromagnetic contactor, and an electromagnetic interference filter.

5. A test method for an aircraft flap and slat section, characterized in that Applied to the motor driver according to any one of claims 1-4, the method includes: Receiving the motor drive signal and the test signal respectively transmitted by the motor controller and the computer; Controlling the torque of the torsion bar on the motor according to the motor drive signal and the test signal, so that the motor controls the movement of the wing movable surface actuator through the torsion bar.

6. The method according to claim 5, wherein Controlling the torque of the torsion bar on the motor according to the motor drive signal and the test signal includes: Controlling the torque of the torsion bar on the motor in a pulse control mode according to the motor drive signal and the test signal.

7. The method according to claim 5, wherein After controlling the torque of the torsion bar on the motor according to the motor drive signal and the test signal, so that the motor controls the movement of the wing movable surface actuator through the torsion bar, it further includes: Determining the test results corresponding to the aircraft flap slat under different test items according to the movement results of the wing movable surface actuator; The test items include the main flight control movable surface test and the flap slat movable surface test.

8. An aircraft flap and slat section test device, characterized in that, Applied to the motor driver according to any one of claims 1-4, the device includes: A signal receiving module, configured to receive the motor drive signal and the test signal respectively transmitted by the motor controller and the computer; A torque control module, configured to control the torque of the torsion bar on the motor according to the motor drive signal and the test signal, so that the motor controls the movement of the wing movable surface actuator through the torsion bar.

9. An electronic device, comprising: One or more processors; A storage device for storing one or more programs; When the one or more programs are executed by the one or more processors, such that the one or more processors execute the programs, the method for testing an aircraft flap slat section as described in any one of claims 5-7 is implemented.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the program is executed by the processor, the method for testing an aircraft flap slat section as described in any one of claims 5-7 is implemented.

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