An aircraft landing system control and functionality check apparatus and method of operation thereof

Abstract

This invention relates to the field of aircraft landing system maintenance technology, specifically to an aircraft landing system control and functional inspection device and its operating method. The device includes a hardware platform and testing software. The hardware platform includes a device housing, a main power module, a power supply module, an NCCI functional module, a signal detection port, and a solenoid valve control port. The testing software includes a joint debugging mode and a single-sided debugging mode. This invention enables accurate measurement of the control functions and endpoint signals of the aircraft landing system. By using an adapter cable to keep the measuring instrument away from the horizontal stabilizer's moving area, it eliminates potential personal injury caused by the movement of the moving control surfaces; it reduces the actual number of personnel required from the conventional three to two, improving the utilization rate of human resources; and it allows some performance checks of the landing system to be performed at the assembly stage, reducing the workload required for troubleshooting.

Description

Technical Field

[0001] This invention relates to the field of aircraft landing system maintenance technology, specifically to an aircraft landing system control and functional inspection device and its working method. Background Technology

[0002] The aircraft landing system ensures the normal operation of takeoff and landing. The landing gear and door retraction / extension are controlled by solenoid valves, while terminal switch signals at various positions assist in determining the aircraft's landing status. However, during the assembly phase, the aircraft cannot receive power, making it impossible to control the landing gear and door retraction / extension via solenoid valves. Furthermore, the status signals of the terminal switches cannot be detected. The retraction / extension status of the landing gear and door relies entirely on visual inspection by the operator, without any auxiliary means, making it impossible to accurately determine the retraction / extension status of the landing gear and door. Summary of the Invention

[0003] To address the aforementioned technical problems, this invention proposes an aircraft landing system control and functional inspection device and its operating method. This reduces the workload and difficulty for operators, minimizes potential human error, and improves the detection effect and accuracy of the landing gear and door retraction / extension positions.

[0004] The technical problem to be solved by this invention is achieved by the following technical solution:

[0005] An aircraft landing system control and functionality testing device, comprising a hardware platform and testing software.

[0006] The hardware platform includes:

[0007] The equipment housing is divided into the lower housing and the upper housing.

[0008] The main power module is located inside the lower shell of the chassis and is responsible for powering the equipment and the signal detection lines.

[0009] The power supply module is located inside the lower housing of the chassis and is responsible for supplying power to the solenoid valve control circuit on the machine.

[0010] The NCCI function module is located inside the lower housing of the chassis and includes a main control board, a signal detection card connected to the main control board, and a peripheral driver board.

[0011] The signal detection port is located on the front side wall of the lower housing of the chassis, connected to the signal detection card, and connected to the port on the machine via an adapter cable;

[0012] The solenoid valve control port is located on the front side wall of the lower housing of the chassis, connected to the main control board, and connected to the machine port via an adapter cable;

[0013] The upper casing of the chassis is equipped with a hydraulic control knob, a display screen, multiple indicator lights with different functions, a motherboard switch, and multiple buttons with different functions. The hydraulic control knob, motherboard switch, and multiple buttons with different functions are connected to the main control board, and the display screen and multiple indicator lights with different functions are connected to the peripheral driver board.

[0014] The testing software includes both joint debugging mode and single-sided debugging mode.

[0015] Preferably, multiple cooling fans and multiple fan air vents are provided on the inner and outer rear walls of the lower casing of the chassis, and multiple fan exhaust vents are provided on the left and right side walls of the lower casing of the chassis.

[0016] Preferably, the lower housing of the chassis is provided with a main power positive terminal, a main power ground terminal, a power supply positive terminal, and a power supply ground terminal.

[0017] One end of the main power positive terminal is connected to the positive terminal of the power supply module, and the other end is connected to the NCCI function module, the hydraulic control knob, and multiple indicator lights with different functions.

[0018] One end of the main power supply grounding terminal is grounded, and the other end is connected to the NCCI function module, the hydraulic control knob, and multiple indicator lights with different functions.

[0019] One end of the positive terminal of the power supply is connected to the positive terminal of the power supply module, and the other end is connected to multiple cooling fans and NCCI functional modules.

[0020] One end of the power supply grounding terminal is grounded, and the other end is connected to multiple cooling fans and NCCI functional modules.

[0021] Preferably, the multiple indicator lights with different functions specifically include a front single-sided status indicator light, a left single-sided status indicator light, a right single-sided status indicator light, a signal abnormality indicator light, and an action permission indicator light.

[0022] Preferably, the multiple buttons with different functions specifically include a switch button, an up button, a down button, and an confirm button.

[0023] Preferably, a power-switch-fuse three-in-one socket is provided on the front side wall of the lower housing of the chassis.

[0024] Preferably, the joint debugging mode involves collecting and detecting all input signals, outputting signals according to the joint debugging logic rules, and controlling all indicator lights.

[0025] Preferably, the single-sided debugging mode involves collecting and detecting the input signal on one side, outputting a signal according to the single-sided debugging logic rules, and controlling the indicator light on the one side.

[0026] A method for operating an aircraft landing system control and functional testing device, comprising the following steps:

[0027] Step (1) Connect the landing gear testing oil cart to the high-pressure and return hydraulic lines at the front end of the aircraft landing gear and door solenoid valves. Connect the dedicated cables on the aircraft landing system control and functional inspection equipment to the X349 plug at the cockpit landing gear circuit inspection button, the 16W-X2 plug at the KZH-106 on the left side of the deck, the 31G plug at the landing gear door solenoid valve, and the 8G plug at the landing gear solenoid valve. Pressure is supplied by the oil cart. Adjust the aircraft landing system control and functional inspection equipment to the joint testing mode.

[0028] Step (2): Control the landing gear retraction through the aircraft landing system control and functional check equipment, and check that the indicator lights on the aircraft landing system control and functional check equipment change from green to yellow;

[0029] Step (3) Control the cabin door to close using the aircraft landing system control and functional check equipment, and check that the indicator lights on the aircraft landing system control and functional check equipment change from yellow to red;

[0030] Step (iv) Control the cabin door to lower using the aircraft landing system control and functional check equipment, and check that the indicator lights on the aircraft landing system control and functional check equipment change from red to yellow;

[0031] Step (5) Control the landing gear to lower using the aircraft landing system control and functional check equipment, and check that the landing gear indicator light on the aircraft landing system control and functional check equipment changes from yellow to green;

[0032] Step (6) Depressurize the oil tanker, disconnect the pressure supply lines for the front landing gear and right landing gear, and restore pressure;

[0033] Step (7) Adjust the joint testing mode to the left landing gear retraction and extension mode;

[0034] Step (8) Control the left landing gear to retract via the aircraft landing system control and functional check equipment, and check that the left landing gear indicator light on the aircraft landing system control and functional check equipment changes from green to yellow;

[0035] Step (ix): Control the cabin door to close using the aircraft landing system control and functional check equipment, and check that the left landing gear indicator light on the aircraft landing system control and functional check equipment changes from yellow to red;

[0036] Step (10) Control the cabin door to lower using the aircraft landing system control and functional check equipment, and check that the left landing gear indicator light on the aircraft landing system control and functional check equipment changes from red to yellow;

[0037] Step (xi) Control the landing gear to lower using the aircraft landing system control and functional check equipment, and check that the left landing gear indicator light on the aircraft landing system control and functional check equipment changes from yellow to green.

[0038] The beneficial effects of this invention are:

[0039] This invention enables accurate measurement of the control functions and endpoint signals of the aircraft landing system. By using an adapter cable to keep the measuring instrument away from the horizontal stabilizer's moving area, potential personal injury caused by the movement of the moving control surfaces is eliminated; the actual number of personnel required for operation is reduced from three to two, improving the utilization rate of human resources; and some performance checks of the landing system are performed at the assembly stage, reducing the workload required for troubleshooting. Attached Figure Description

[0040] The present invention will be further described below with reference to the accompanying drawings and embodiments:

[0041] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0042] Figure 2 This is a schematic diagram of the internal three-dimensional structure of the present invention;

[0043] Figure 3 This is a top view of the internal structure of the present invention;

[0044] Figure 4 This is a schematic diagram of the NCCI functional module in this invention;

[0045] Figure 5 This is a schematic diagram of the external top view of the present invention.

[0046] In the diagram: 1. Lower chassis; 2. Upper chassis; 3. Fan vent; 4. Fan exhaust vent; 5. Hydraulic control knob; 6. Display screen; 7. Front single-sided status indicator; 8. Left single-sided status indicator; 9. Right single-sided status indicator; 10. Signal abnormality indicator; 11. Allow action indicator; 12. Mainboard switch; 13. Switch key; 14. Up key; 15. Down key; 16. Confirm key; 17. Main power module; 18. Power supply module; 19. NCCI function module; 19a. Main control board; 19b. Signal detection card; 19c. Peripheral driver board; 20. Main power positive terminal; 21. Main power ground terminal; 22. Power supply positive terminal; 23. Power supply ground terminal; 24. Signal detection port; 25. Solenoid valve control port; 26. Power-switch-fuse three-in-one socket; 27. Cooling fan. Detailed Implementation

[0047] To make the technical means, creative features, objectives and effects of this invention easier to understand, the invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0048] like Figures 1 to 5 As shown, an aircraft landing system control and functional testing device is provided, which is interconnected with an onboard port via an adapter cable. Furthermore, the schematic diagram includes a hardware platform and testing software.

[0049] The hardware platform comprises a device housing, a hydraulic control knob 5, a display screen 6, multiple indicator lights with different functions, a motherboard switch 12, multiple buttons with different functions, a power module, an NCCI function module 19, a signal detection port 24, a solenoid valve control port 25, a power-switch-fuse three-in-one socket 26, a cooling fan 27, etc.

[0050] Furthermore, the equipment housing adopts an aluminum box-type structure, which is divided into a lower housing 1 and an upper housing 2.

[0051] The power module, NCCI function module 19, signal detection port 24, solenoid valve control port 25, power-switch-fuse three-in-one socket 26, and cooling fan 27 are respectively installed inside the lower shell 1 of the chassis.

[0052] The power supply module includes a main power supply module 17 and a power supply module 18. The main power supply module 17 is located inside the lower housing 1 of the chassis and is responsible for powering the equipment and signal detection circuits. The power supply module 18 is located inside the lower housing 1 of the chassis and is responsible for powering the solenoid valve control circuit on the machine.

[0053] The NCCI functional module 19 includes a main control board 19a, a signal detection card 19b, and a peripheral driver board 19c.

[0054] The main control board 19a is connected to the multiple buttons with different functions, the hydraulic control knob 5, the signal detection card 19b, and the peripheral driver board 19c.

[0055] The signal detection card 19b is connected to the signal detection port 24 and the main control board 19a.

[0056] The peripheral driver board 19c is connected to multiple indicator lights with different functions, the display screen 6, and the main control board 19a.

[0057] The control logic of the main control board 19a consists of device connection input signals, device connection output signals, input signal logic, and indicator light signal display logic. The main control board 19a selects the input data acquisition channel and display screen according to the operator's function. The operator selects the control and measurement mode via buttons. The main control board 19a selects the input device control channel based on the operator's knob position, controlling the voltage output of the solenoid valve control port 25. Onboard signals are input to the device through the signal detection port 24. The main control board 19a detects and judges whether the landing gear retraction / extension status is normal according to the predefined input / output signal logic, generating an indicator light output signal and sending it to the peripheral drive board 19c. The peripheral drive board 19c controls the switching of indicator light and display screen 6 signals, assisting the operator in completing the landing gear retraction / extension system debugging work during the assembly phase.

[0058] The signal detection card 19b is used to detect signals on a designated on-board circuit according to the data acquisition channel and transmit the detected signals back to the main control board 19a.

[0059] The peripheral driver board 19c is used to control the indicator lights according to the output signals of the main control board.

[0060] The signal detection port 24, the solenoid valve control port 25, and the power-switch-fuse three-in-one socket 26 are respectively installed on the front outer wall of the lower housing 1 of the chassis. The signal detection port 24 is connected to the machine port via an adapter cable; the solenoid valve control port 25 is connected to the machine port via an adapter cable.

[0061] Multiple cooling fans 27 are provided and correspondingly distributed on the rear inner shell wall of the lower casing 1 of the chassis. Multiple fan air outlets 3 are provided on the rear outer shell wall of the lower casing 1 of the chassis, corresponding to the positions of the multiple cooling fans 27. Multiple fan exhaust outlets 4 are provided on the left and right shell walls of the lower casing 1 of the chassis.

[0062] The hydraulic control knob 5, display screen 6, multiple indicator lights with different functions, main board switch 12, and multiple buttons with different functions are respectively set on the upper shell 2 of the chassis.

[0063] The indicator lights with different functions include the front single-sided status indicator light 7, the left single-sided status indicator light 8, the right single-sided status indicator light 9, the signal abnormality indicator light 10, and the action permission indicator light 11.

[0064] The various buttons with different functions include switch button 13, up button 14, down button 15, and confirm button 16.

[0065] The device uses a microcontroller program to detect input signals and make corresponding logical judgments, and then outputs corresponding status signals to control the indicator lights and display screen to switch signals.

[0066] The lower casing 1 of the chassis is provided with a main power positive terminal 20, a main power ground terminal 21, a power power positive terminal 22, and a power power ground terminal 23.

[0067] One end of the main power positive terminal 20 is connected to the positive terminal of the power supply module 18, and the other end is connected to the NCCI function module 19, the hydraulic control knob 5, and multiple indicator lights with different functions.

[0068] One end of the main power grounding terminal 21 is grounded, and the other end is connected to the NCCI function module 19, the hydraulic control knob 5, and multiple indicator lights with different functions.

[0069] One end of the positive terminal 22 of the power supply is connected to the positive terminal of the power supply module 18, and the other end is connected to multiple cooling fans 27 and NCCI functional module 19.

[0070] One end of the power supply grounding terminal 23 is grounded, and the other end is connected to multiple cooling fans 27 and NCCI functional modules 19.

[0071] The testing software is mainly divided into joint debugging mode and single-sided debugging mode. The joint debugging mode collects and detects all input signals, outputs signals according to the joint debugging logic rules, and controls all indicator lights. The single-sided debugging mode detects the input signal on one side, outputs signals according to the single-sided debugging logic rules, and controls the indicator lights on that side.

[0072] The control logic is shown in Table 1 below.

[0073] Table 1 Equipment Logic Control Table

[0074]

[0075] A method for operating an aircraft landing system control and functional testing device, comprising the following steps:

[0076] Step (1) Connect the landing gear testing oil cart to the high-pressure and return hydraulic lines at the front end of the aircraft landing gear and door solenoid valves. Connect the dedicated cables on the aircraft landing system control and functional inspection equipment to the X349 plug at the cockpit landing gear circuit inspection button, the 16W-X2 plug at the KZH-106 on the left side of the deck, the 31G plug at the landing gear door solenoid valve, and the 8G plug at the landing gear solenoid valve. With the oil cart pressurized, adjust the aircraft landing system control and functional inspection equipment to the joint testing mode.

[0077] Step (2) Control the landing gear retraction through the aircraft landing system control and functional check equipment, and check that the indicator lights on the aircraft landing system control and functional check equipment change from green to yellow.

[0078] Step (3) Control the cabin door to close using the aircraft landing system control and functional check equipment, and check that the indicator lights on the aircraft landing system control and functional check equipment change from yellow to red.

[0079] Step (iv) Control the cabin door to lower using the aircraft landing system control and functional check equipment, and check that the indicator lights on the aircraft landing system control and functional check equipment change from red to yellow.

[0080] Step (5) Control the landing gear to lower using the aircraft landing system control and functional check equipment, and check that the landing gear indicator light on the aircraft landing system control and functional check equipment changes from yellow to green.

[0081] Step (6) Depressurize the oil tanker, disconnect the pressure supply lines for the front landing gear and right landing gear, and restore pressure.

[0082] Step (7) Adjust the joint commissioning mode to the left landing gear retraction and extension mode.

[0083] Step (8) Control the left landing gear to retract via the aircraft landing system control and functional check equipment, and check that the left landing gear indicator light on the aircraft landing system control and functional check equipment changes from green to yellow.

[0084] Step (ix): Control the cabin door to close using the aircraft landing system control and functional check equipment, and check that the left landing gear indicator light on the aircraft landing system control and functional check equipment changes from yellow to red.

[0085] Step (10) Control the cabin door to lower using the aircraft landing system control and functional check equipment, and check that the left landing gear indicator light on the aircraft landing system control and functional check equipment changes from red to yellow.

[0086] Step (xi) Control the landing gear to lower using the aircraft landing system control and functional check equipment, and check that the left landing gear indicator light on the aircraft landing system control and functional check equipment changes from yellow to green.

[0087] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely prisms of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of this invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft landing system control and functional testing device, comprising a hardware platform and testing software, characterized in that: The hardware platform includes: The equipment housing is divided into the lower housing (1) and the upper housing (2). The main power module (17) is located inside the lower shell (1) of the chassis and is responsible for powering the equipment and the signal detection line. The power supply module (18) is located inside the lower housing (1) of the chassis and is responsible for supplying power to the solenoid valve control circuit on the machine. The NCCI function module (19) is located inside the lower housing (1) of the chassis and includes a main control board (19a), a signal detection card (19b) connected to the main control board (19a), and a peripheral driver board (19c). The signal detection port (24) is located on the front side wall of the lower housing (1) of the chassis, and is connected to the signal detection card (19b) and connected to the machine port through an adapter cable; The solenoid valve control port (25) is located on the front side wall of the lower housing (1) of the chassis, and is connected to the main control board (19a). It is connected to the machine port through an adapter cable. The upper casing (2) of the chassis is provided with a hydraulic control knob (5), a display screen (6), multiple indicator lights with different functions, a main board switch (12) and multiple buttons with different functions. The hydraulic control knob (5), the main board switch (12) and the multiple buttons with different functions are connected to the main control board (19a), and the display screen (6) and the multiple indicator lights with different functions are connected to the peripheral drive board (19c). The testing software includes a joint debugging mode and a single-sided debugging mode. In the joint debugging mode, the microcontroller program collects and detects all input signals and outputs signals according to the joint debugging logic rules to control all indicator lights. In the single-sided debugging mode, the microcontroller program collects and detects input signals from one side and outputs signals according to the single-sided debugging logic rules to control the indicator lights on that side. The control logic of the main control board (19a) is composed of device connection input signal, device connection output signal, input signal logic and indicator light signal display logic. The main control board (19a) selects the input data acquisition channel and display screen according to the operator's function. The operator selects the control and measurement mode through the button. The main control board (19a) selects the input device control channel according to the operator's knob position and controls the voltage output of the solenoid valve control port (25). The on-board signal is input to the device through the signal detection port (24). The main control board (19a) detects and judges whether the landing gear retraction and extension status is normal according to the prescribed input and output signal logic, and forms an indicator light output signal to be sent to the peripheral drive board (19c). The peripheral drive board (19c) controls the switching of the indicator light and display screen (6) signals to assist the operator in completing the debugging work of the landing gear retraction and extension system during the assembly stage. The signal detection card (19b) is used to detect signals on a designated on-board circuit according to the data acquisition channel and transmit the detected signals back to the main control board (19a). The peripheral driver board (19c) is used to control the indicator lights according to the output signal of the main control board.

2. The aircraft landing system control and functional testing equipment according to claim 1, characterized in that: Multiple cooling fans (27) and multiple fan air outlets (3) are provided on the inner and outer walls of the rear side of the lower casing (1) of the chassis, and multiple fan exhaust outlets (4) are provided on the left and right side walls of the lower casing (1).

3. The aircraft landing system control and functional testing equipment according to claim 2, characterized in that: The lower casing (1) of the chassis is provided with a main power positive terminal (20), a main power ground terminal (21), a power power positive terminal (22), and a power power ground terminal (23). One end of the main power positive terminal (20) is connected to the positive terminal of the power supply module (18), and the other end is connected to the NCCI function module (19), the hydraulic control knob (5), and multiple indicator lights with different functions. One end of the main power supply grounding terminal (21) is grounded, and the other end is connected to the NCCI function module (19), the hydraulic control knob (5), and multiple indicator lights with different functions. One end of the positive terminal (22) of the power supply is connected to the positive terminal of the power supply module (18), and the other end is connected to multiple cooling fans (27) and NCCI functional module (19); One end of the power supply grounding terminal (23) is grounded, and the other end is connected to multiple cooling fans (27) and NCCI functional modules (19).

4. The aircraft landing system control and functional testing equipment according to claim 1, characterized in that: The multiple indicator lights with different functions include the front single-sided status indicator (7), the left single-sided status indicator (8), the right single-sided status indicator (9), the signal abnormality indicator (10), and the action permission indicator (11).

5. The aircraft landing system control and functional testing equipment according to claim 1, characterized in that: The various buttons with different functions include a switch button (13), an up button (14), a down button (15), and an confirm button (16).

6. The aircraft landing system control and functional testing equipment according to claim 1, characterized in that: A power-switch-fuse three-in-one socket (26) is provided on the front side wall of the lower casing (1) of the chassis.

7. A method for operating an aircraft landing system control and functional testing device, characterized in that: The application of the aircraft landing system control and functional testing device according to any one of claims 1 to 6 includes the following steps: Step (1) Connect the landing gear testing oil cart to the high-pressure and return hydraulic lines at the front end of the aircraft landing gear and door solenoid valves. Connect the dedicated cables on the aircraft landing system control and functional inspection equipment to the X349 plug at the cockpit landing gear circuit inspection button, the 16W-X2 plug at the KZH-106 on the left side of the deck, the 31G plug at the landing gear door solenoid valve, and the 8G plug at the landing gear solenoid valve. Pressure is supplied by the oil cart. Adjust the aircraft landing system control and functional inspection equipment to the joint testing mode. Step (2): Control the landing gear retraction through the aircraft landing system control and functional check equipment, and check that the indicator lights on the aircraft landing system control and functional check equipment change from green to yellow; Step (3) Control the cabin door to close using the aircraft landing system control and functional check equipment, and check that the indicator lights on the aircraft landing system control and functional check equipment change from yellow to red; Step (iv) Control the cabin door to lower using the aircraft landing system control and functional check equipment, and check that the indicator lights on the aircraft landing system control and functional check equipment change from red to yellow; Step (5) Control the landing gear to lower using the aircraft landing system control and functional check equipment, and check that the landing gear indicator light on the aircraft landing system control and functional check equipment changes from yellow to green; Step (6) Depressurize the oil tanker, disconnect the pressure supply lines for the front landing gear and right landing gear, and restore pressure; Step (7) Adjust the joint testing mode to the left landing gear retraction and extension mode; Step (8) Control the left landing gear to retract via the aircraft landing system control and functional check equipment, and check that the left landing gear indicator light on the aircraft landing system control and functional check equipment changes from green to yellow; Step (ix): Control the cabin door to close using the aircraft landing system control and functional check equipment, and check that the left landing gear indicator light on the aircraft landing system control and functional check equipment changes from yellow to red; Step (10) Control the cabin door to lower using the aircraft landing system control and functional check equipment, and check that the left landing gear indicator light on the aircraft landing system control and functional check equipment changes from red to yellow; Step (xi) Control the landing gear to lower using the aircraft landing system control and functional check equipment, and check that the left landing gear indicator light on the aircraft landing system control and functional check equipment changes from yellow to green.

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