Aircraft throttle lever assembly electrical control system test apparatus and method

Abstract

The application discloses an aircraft throttle lever assembly electric control system test equipment and a test method, a box body of the equipment is provided with a general control circuit, a front cabin 118XSP socket and a front cabin 119XSP socket, the general control circuit is connected with the throttle lever assembly through the front cabin 118XSP socket and the front cabin 119XSP socket; the general control circuit comprises a plurality of parallel test sub-circuits and corresponding indication components, the test sub-circuit is matched with each switch on the throttle assembly, so as to detect the state of the throttle lever assembly, and the indication component is used for displaying the state of the throttle lever assembly in real time, according to the signal fed back by the indication component, the state of the throttle lever assembly can be directly judged. The application has the characteristics of small size, high test efficiency and high stability, and effectively saves the test cost of the throttle lever assembly.

Description

Technical Field

[0001] This invention relates to the field of aircraft throttle lever maintenance technology, specifically to a testing device and testing method for the electrical control system of an aircraft throttle lever assembly. Background Technology

[0002] On a certain type of aircraft, the throttle lever assembly, in addition to its mechanical function of controlling throttle size, integrates multiple control switches on its control handle, allowing the pilot to perform various functions without taking their hands off the stick during flight. These include T1: Avionics Main Mode Switch, T2: Electronic Warfare Switch, T3: Speed ​​Brake Control Switch, T4: Transmit / Receive Control Switch, T5: Target Identification Control Switch, T6: Missile Position Controller (GAGE) Control Switch, T7: Radar Antenna Pitch Control Switch, and T8: Nose Wheel Turn (NWS) Control Rate Selection Switch. Currently, the manufacturing and repair of existing throttle lever assembly control handles often rely on simple continuity tests and visual inspections to check the correct soldering of each switch. There is a lack of offline testing equipment, making it impossible to perform offline functional testing of the electrical control components of the throttle lever assembly. Functional testing mainly depends on onboard power-on checks after the throttle lever assembly is installed.

[0003] Specifically, the throttle lever assembly operating handle has the following main drawbacks in the current manufacturing and repair processes:

[0004] (1) Offline functional testing of electrical control systems T1 to T8 of a certain type of oil valve assembly cannot be performed.

[0005] (2) Post-repair testing and inspection are time-consuming. Previously, after the throttle lever assembly was manufactured and repaired, the operator could only test the on / off state of the throttle lever assembly's T1-T8 switches one by one by means of conductivity, and two people were required to operate the test. The test time was about 20 minutes. The inspection personnel also needed two people to operate the final inspection, and the test time was about 20 minutes.

[0006] (3) It is prone to human error. In the past, after the manufacture and repair of this type of oil valve assembly, the T1 to T8 switches were tested one by one for continuity, which was a lot of work and prone to human error.

[0007] (4) If a quality problem is found when the throttle lever assembly is tested on the aircraft, it needs to be removed from the aircraft for rework. When disassembling the throttle lever assembly, all related interference equipment in the cockpit must be removed, which involves a large workload and high rework costs. Summary of the Invention

[0008] The technical problem this invention aims to solve is that, in the existing technology, human factors have a significant impact on the measurement results of the throttle lever assembly, which can easily lead to second-generation low-level quality problems due to human factors; moreover, after the throttle lever assembly is installed on the aircraft, problems with the throttle lever assembly switch and wiring harness often cause malfunctions and other defects during whole-aircraft testing. This invention provides a test device and test method for the electrical control system of the aircraft throttle lever assembly that is compact in structure, easy to operate, highly stable, and highly visualized.

[0009] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is as follows:

[0010] A test device for the electrical control system of an aircraft throttle lever assembly is disclosed. The throttle lever assembly includes: a T1 avionics main mode switch, a T2 electronic warfare switch, a T3 speed brake control switch, a T4 transmit / receive control switch, a T5 target calibration control switch, a T6 missile position indicator control switch, a T7 radar antenna elevation control switch, and a T8 nose wheel steering rate selection switch. The wiring harness connectors of the throttle lever assembly include 118XPS and 119XPS connectors. The test device includes a housing containing a central control circuit. A front nacelle 118XPS socket and a front nacelle 119XPS socket are located on the side of the housing. The central control circuit is connected to the 118XPS and 119XPS connectors of the throttle lever assembly via the front nacelle 118XPS and 119XPS connectors. The central control circuit includes multiple parallel test sub-circuits and corresponding indicator components. The test sub-circuits are used to detect the status of the throttle lever assembly, and the indicator components are used to display the status of the throttle lever assembly in real time.

[0011] The test sub-circuits include: avionics main mode switch test circuit, electronic warfare switch test circuit, speed brake control switch test circuit, transmit / receive control switch test circuit, target calibration control switch test circuit, missile position marker control switch test circuit, radar antenna elevation control switch test circuit, and front wheel steering control rate selection switch test circuit.

[0012] The indicator components include: avionics main mode switch indicator component, electronic warfare switch indicator component, speed brake control switch indicator component, transmit / receive control switch indicator component, target designation control switch indicator component, missile position marker control switch indicator component, radar antenna elevation control switch indicator component, and front wheel steering control rate selection switch indicator component.

[0013] As a further improvement of the present invention, the enclosure is also provided with two adapter boards, and the side of the enclosure is also provided with a rear cabin 450XSP socket and a rear cabin 453XSP socket; the rear cabin 450XSP socket and the front cabin 118XSP socket are connected in parallel on one adapter board, and the rear cabin 453XSP socket and the front cabin 119XSP socket are connected in parallel on the other adapter board. The adapter board is connected to the main control circuit to realize the testing of single-seat throttle lever assembly or double-seat throttle lever assembly.

[0014] As a further improvement of the present invention, the 118XPS plug is provided with output pins A, B, E, F, G, J, L and M, and the front cabin 118XSP socket is provided with input pins A, B, E, F, G, J, L and M; when the 118XPS plug is connected to the front cabin 118XSP socket, the T3 deceleration board control switch is connected to the deceleration board control switch test circuit, and the T4 transmit / receive control switch is connected to the transmit / receive control switch test circuit.

[0015] As a further improvement of the present invention, the T3 gearshift control switch is connected to input pin A and output pin B of the 118XSP socket in the front cabin via a 118XPS plug. The T3 gearshift control switch has two positions: on and off. When the T3 gearshift control switch is moved backward along the aircraft's heading, the T3 gearshift control switch is on; when it is released, the switch is off. The gearshift control switch indicator component uses a green indicator light to indicate the switch status; the green light is on when the switch is on and off when it is released.

[0016] The T4 transmit / receive control switch is connected to input pins E, F, G, and J of the 118XPS connector in the front cabin via a 118XPS plug. The T4 transmit / receive control switch has three positions: forward, middle, and rear. When the T4 transmit / receive control switch is pushed forward along the aircraft's heading, it is in the forward position; when the T4 transmit / receive control switch is in the middle position, it is in the middle position; and when the T4 transmit / receive control switch is pulled back, it is in the rear position. The indicator component of the transmit / receive control switch uses yellow, red, and green lights to indicate the switch position. When the T4 transmit / receive control switch is pushed forward, the yellow light is on; when the T4 transmit / receive control switch is in the middle position, the red light is on; and when the T4 transmit / receive control switch is pulled back, the green light is on.

[0017] As a further improvement of the present invention, the 119XPS plug is provided with output pins A, B, C, D, E, F, G, H, J, K, L, M, N, P, R, S, T, U, and V, and the forward 119XSP socket is provided with input pins A, B, C, D, E, F, G, H, J, K, L, M, N, P, R, S, T, U, and V; when the 119XPS plug is connected to the forward 119XSP socket, the T1 avionics main mode switch is connected to the avionics main mode switch test circuit, the T2 electronic warfare switch is connected to the electronic warfare switch test circuit, the T5 target calibration control switch is connected to the target calibration control switch test circuit, the T6 missile position indicator control switch is connected to the target calibration control switch test circuit, and the T7 radar antenna elevation control switch is connected to the radar antenna elevation control switch test circuit.

[0018] As a further improvement of the present invention, the T1 avionics main mode switch is connected to the input pins H, J, K and L of the 119XSP socket in the front cabin via a 119XPS plug. The T1 avionics main mode switch has three positions: forward, middle and rear. When the T1 avionics main mode switch is pushed forward along the aircraft heading, it is in the forward position; when the T1 avionics main mode switch is in the middle position, it is in the middle position; and when the T1 avionics main mode switch is pulled back, it is in the rear position. The avionics main mode switch indicator component uses three-color lights, namely yellow, red and green, to indicate the switch position. When the T1 avionics main mode switch is pushed forward, the yellow light is on; when the T1 avionics main mode switch is in the middle position, the red light is on; and when the T1 avionics main mode switch is pulled back, the green light is on.

[0019] The T2 electronic warfare switch is connected to the input pins P, R, S, T, and U of the 119XSP socket in the forward cabin via a 119XPS plug. The T2 electronic warfare switch has three positions: forward, middle, and rear. When the T2 electronic warfare switch is pushed forward along the aircraft's heading, it is in the forward position; when the T2 electronic warfare switch is in the middle position, it is in the middle position; and when the T2 electronic warfare switch is pulled back, it is in the rear position. The electronic warfare switch indicator component uses yellow, red, and green lights to indicate the switch position. When the T2 electronic warfare switch is pushed forward, the yellow light is on; when the T2 electronic warfare switch is in the middle position, the red light is on; and when the T2 electronic warfare switch is pulled back, the green light is on.

[0020] As a further improvement of the present invention, the T5 target calibration control switch is connected to input pins A, B, C, D, F, G, H, and N in the 119XSP socket in the front cabin via a 119XPS plug. The T5 target calibration control switch consists of a force-sensitive sensor and an on / off switch. The target calibration control switch indicating component displays the detected V using a dual-channel voltmeter. X and V YThe voltage is indicated by red and green lights showing the state of the T5 target calibration control switch along its central axis; when the T5 target calibration control switch is moved up and down along the heading direction, the X-axis voltage V... X As the value of U / 2 changes, when the T5 target calibration control switch is flipped upwards, V... X When it gets bigger and is pulled down, V X The voltage decreases; when the T5 target calibration control switch is moved along the forward / backward direction, the Y-axis voltage V... Y As the value of U / 2 changes, when the T5 target calibration control switch is moved forward, V... Y When it gets bigger and is pulled back, V Y When the T5 target calibration control switch is not pressed down along the central axis, the red light is on and the green light is off; when the T5 target calibration control switch is pressed down along the central axis, the green light is on and the red light is off.

[0021] As a further improvement of the present invention, the T6 missile position indicator control switch is connected to the input pins H and M of the 119XSP socket in the front cabin via a 119XPS plug. The T6 missile position indicator control switch has two states: on and off. When the T6 missile position indicator control switch is pressed, the switch is on; when the T6 missile position indicator control switch is released, the switch is off. The missile position indicator control switch indicator component uses a green light to indicate the switch state. When the T6 missile position indicator control switch is pressed, the green light is on; when the T6 missile position indicator control switch is released, the green light is off.

[0022] As a further improvement of the present invention, the T7 radar antenna elevation control switch is connected to input pins E, F, and G of the 119XSP socket in the front cabin via a 119XPS plug. The T7 radar antenna elevation control switch is a sliding rheostat switch. The radar antenna elevation control switch indicator component uses a voltmeter to display the detected voltage V. Y Voltage, when the T7 radar antenna pitch control switch is pushed forward along the heading, the voltage reading V Y When the T7 radar antenna elevation control switch is moved backward, the voltmeter reading V decreases. Y It gets bigger.

[0023] As a further improvement of the present invention, when the 118XPS plug is connected to the 118XSP socket in the front cabin and the 119XPS plug is connected to the 119XSP socket in the front cabin, the T8 front wheel steering control rate selection switch is connected to the front wheel steering control rate selection switch test circuit.

[0024] The T8 front wheel steering control rate selection switch is connected to the input pins L and M of the 118XSP socket in the front compartment via a 118XPS plug, and to the input pins H and V of the 119XSP socket in the front compartment via a 119XPS plug. The indicator component of the front wheel steering control rate selection switch uses red and green lights to indicate the switch status. When the T8 front wheel steering control rate selection switch is pressed, the green light is on and the red light is off; when the T8 front wheel steering control rate selection switch is released, the green light is off and the red light is on.

[0025] As a general technical concept, the present invention also provides a test method based on the above-mentioned test equipment for the electrical control system of the aircraft throttle lever assembly, comprising the following steps:

[0026] Step S1: Connect the 118XPS and 119XPS plugs of the throttle lever to the 118XSP and 119XSP sockets in the front compartment of the test equipment, respectively.

[0027] Step S2: Turn the main switch on the enclosure to the "ON" position. The power voltage display will show "UV".

[0028] Step S3, T1 Avionics Main Mode Switch Test: Push the T1 Avionics Main Mode Switch forward along the aircraft's heading. The yellow light in the Avionics Main Mode Switch indicator component will illuminate. When the T1 Avionics Main Mode Switch is in the middle position, the red light in the Avionics Main Mode Switch indicator component will illuminate. When the T1 Avionics Main Mode Switch is pulled back, the green light in the Avionics Main Mode Switch indicator component will illuminate.

[0029] Step S4, T2 Electronic Warfare Switch Test: Push the T2 electronic warfare switch forward along the aircraft's heading, and the yellow light of the electronic warfare switch indicator component will illuminate. When the T2 electronic warfare switch is in the middle position, the red light of the electronic warfare switch indicator component will illuminate. When the T2 electronic warfare switch is pulled back, the green light of the electronic warfare switch indicator component will illuminate.

[0030] Step S5, T3 speed brake control switch test: For a single-seat aircraft, when the T3 speed brake control switch is pulled back along the aircraft's heading, the green light on the speed brake control switch indicator component illuminates; when the T3 speed brake control switch is released, the green light on the speed brake control switch indicator component goes out. For a two-seat aircraft in the front cabin, when the T3 speed brake control switch is pulled back along the aircraft's heading, the green light on the speed brake control switch indicator component illuminates and the red light goes out; when the T3 speed brake control switch is pushed forward, the green light on the speed brake control switch indicator component goes out and the red light illuminates.

[0031] Step S6, T4 Transmit / Receive Control Switch Test: When the T4 transmit / receive control switch is pushed forward along the aircraft's heading, the yellow light of the transmit / receive control switch indicator component illuminates; when the T4 transmit / receive control switch is in the middle position, the red light of the transmit / receive control switch indicator component illuminates; when the T4 transmit / receive control switch is pulled back, the green light of the transmit / receive control switch indicator component illuminates.

[0032] Step S7, T5 Target Calibration Control Switch Test: When the equipment switch is turned on, the voltage V X and V Y All display (U / 2)V; when the T5 target calibration control switch is moved up and down along the heading direction, the X-axis voltage V X As the value of (U / 2)V changes, when the lever is moved upwards, V... X As (U / 2)V gradually increases, when the lever is pulled downwards, V X The voltage (U / 2)V gradually decreases; when the T5 target calibration control switch is moved along the forward and backward direction, the Y-axis voltage V... Y As the value of (U / 2)V changes, when the lever is moved forward, V Y As (U / 2)V gradually increases, when it is pulled backward, V Y The value of (U / 2)V gradually decreases; when the T5 target calibration control switch is not pressed down along the central axis, the red light of the target calibration control switch indicator component is on and the green light is off; when the T5 target calibration control switch is pressed down along the central axis, the green light of the target calibration control switch indicator component is on and the red light is off.

[0033] Step S8, T6 missile position indicator control switch test: When the T6 missile position indicator control switch is pressed, the green light of the missile position indicator control switch indicator component lights up; when released, the green light goes out.

[0034] Step S9, T7 Radar Antenna Elevation Control Switch Test: When the device switch is turned on, the voltage V X The display shows (U / 2)V; When the T7 radar antenna pitch control switch is pushed forward along the heading, the voltage reading V of the radar antenna pitch control switch indicator component is displayed. Y As (U / 2)V gradually decreases, when the T7 radar antenna elevation control switch is moved backward, the voltage reading V of the radar antenna elevation control switch indicator component changes. Y The value of (U / 2)V gradually increases.

[0035] Step S10, T8 front wheel steering control rate selection switch test: When the T8 front wheel steering control rate selection switch is pressed, the green light of the front wheel steering control rate selection switch indicator component is on and the red light is off. When the T8 front wheel steering control rate selection switch is released, the green light of the front wheel steering control rate selection switch indicator component is off and the red light is on.

[0036] Compared with the prior art, the advantages of the present invention are as follows:

[0037] The present invention relates to a testing device and method for the electrical control system of an aircraft throttle lever assembly. The device housing includes a main control circuit, a front cockpit 118XSP socket, and a front cockpit 119XSP socket. The main control circuit connects to the throttle lever assembly via these sockets, ensuring simple operation and reliable connection. Furthermore, the main control circuit includes multiple parallel test sub-circuits and corresponding indicator components. These test sub-circuits are matched to the individual switches on the throttle assembly. The test sub-circuits detect the state of the throttle lever assembly, and the indicator components display this state in real time. Based on the feedback signals from the indicator components, the state of the throttle lever assembly can be intuitively determined, providing strong visualization and reducing the likelihood of human error. Previously, testing the conduction of each of the T1 to T8 switches on the throttle lever assembly was labor-intensive and prone to human error. This invention requires only one person to complete the test, which takes no more than two minutes, significantly reducing human error and improving the efficiency of throttle lever assembly testing. Attached Figure Description

[0038] Figure 1 A schematic diagram illustrating the connection principle between the throttle lever assembly and the aircraft system;

[0039] Figure 2 A schematic diagram illustrating the wiring harness connection principle of a single-seat throttle lever assembly;

[0040] Figure 3 This is a schematic diagram illustrating the connection principle between the throttle lever assembly and the testing equipment in a specific embodiment of the present invention;

[0041] Figure 4 This is a schematic diagram of the internal circuit principle of the test device in a specific embodiment of the present invention;

[0042] Figure 5 This is a schematic diagram of the T1 avionics main mode switch test circuit in a specific embodiment of the present invention;

[0043] Figure 6 This is a schematic diagram of the T2 electronic warfare switch test circuit in a specific embodiment of the present invention;

[0044] Figure 7 This is a schematic diagram of the T3 speed reducer control switch test circuit in a specific embodiment of the present invention;

[0045] Figure 8 This is a schematic diagram of the T4 transmit / receive control switch test circuit in a specific embodiment of the present invention;

[0046] Figure 9 This is a schematic diagram of the T5 target calibration control switch test circuit in a specific embodiment of the present invention;

[0047] Figure 10 This is a schematic diagram of the test circuit principle of the T6 missile position marker control (GAGE) switch in a specific embodiment of the present invention;

[0048] Figure 11 This is a schematic diagram of the test circuit principle of the T7 radar antenna elevation control switch in a specific embodiment of the present invention;

[0049] Figure 12 This is a schematic diagram of the T8 front wheel steering (NWS) control rate selection switch test circuit in a specific embodiment of the present invention;

[0050] Figure 13 A schematic diagram illustrating the wiring harness connection principle of the dual-seat front compartment throttle lever assembly;

[0051] Figure 14 A schematic diagram illustrating the wiring harness connection principle of the rear cabin throttle lever assembly for two-seat configurations;

[0052] Figure 15 This is a schematic diagram of the single / dual-seat compatible adapter line in a specific embodiment of the present invention;

[0053] Figure 16 This is a schematic diagram of the structural principle of the test device panel in a specific embodiment of the present invention;

[0054] Figure 17 This is a schematic diagram of the external structure of the test equipment in a specific embodiment of the present invention; Attached image description:

[0056] 1. Avionics main mode switch indicator assembly; 2. Electronic warfare switch indicator assembly; 3. Speed ​​brake control switch indicator assembly; 4. Transmit / receive control switch indicator assembly; 5. Target designation control switch indicator assembly; 6. Missile position indicator control switch indicator assembly; 7. Radar antenna elevation control switch indicator assembly; 8. Nose wheel steering control rate selection switch indicator assembly; 9. Power voltage display; 10. Main switch; 11. External power socket; 12. Power selection switch; 100. Housing; 101. Control panel; 102. Front compartment 118XSP socket; 103. Front compartment 119XSP socket; 104. Rear compartment 450XSP socket; 105. Rear compartment 453XSP socket; 106. Handle. Detailed Implementation

[0057] The present invention will be further described below with reference to the accompanying drawings and specific preferred embodiments, but this does not limit the scope of protection of the present invention.

[0058] In the description of this invention, it should be understood that the terms "side", "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0059] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more unless otherwise explicitly specified.

[0060] Example 1

[0061] The throttle lever assembly includes: T1 avionics main mode switch, T2 electronic warfare switch, T3 speed brake control switch, T4 transmit / receive control switch (communication control switch), T5 target designation control switch, T6 missile position indicator control switch, T7 radar antenna elevation control switch, and T8 front wheel steering rate selection switch. The throttle lever assembly wiring harness connectors include 118XPS and 119XPS connectors. For example... Figure 1 As shown, the throttle lever assembly has two wiring harnesses and connectors 118XPS and 119XPS, which connect to the aircraft's cable connectors 118XSP and 119XSP respectively. By operating the eight switches T1 to T8 on the throttle lever assembly, multiple systems on the aircraft are controlled, and corresponding functions are achieved. For example... Figure 2 The diagram shown is a schematic of the wiring harness connection for the throttle lever assembly. After the existing throttle lever assembly is manufactured or repaired, it is inspected and tested by conducting the wiring harness one by one.

[0062] like Figure 3 , Figure 4 , Figure 16 and Figure 17As shown, the aircraft throttle lever assembly electrical control system test equipment of the present invention includes a housing 100, in which a main control circuit is provided. A front cabin 118XSP socket 102 and a front cabin 119XSP socket 103 are provided on the side of the housing 100. The main control circuit is connected to the 118XPS and 119XPS plugs of the throttle lever assembly through the front cabin 118XSP socket 102 and the front cabin 119XSP socket 103. The main control circuit includes multiple parallel test sub-circuits and corresponding indicator components. The test sub-circuits are used to detect the state of the throttle lever assembly, and the indicator components are used to display the state of the throttle lever assembly in real time; that is, the test sub-circuits and indicator components are connected in a one-to-one correspondence.

[0063] Specifically, the test sub-circuits include: avionics main mode switch test circuit, electronic warfare switch test circuit, speed brake control switch test circuit, transmit / receive control switch test circuit, target targeting control switch test circuit, missile position marker control switch test circuit, radar antenna elevation control switch test circuit, and front wheel steering control rate selection switch test circuit.

[0064] The indication components include: avionics main mode switch indication component 1, electronic warfare switch indication component 2, speed brake control switch indication component 3, transmit / receive control switch indication component 4, target designation control switch indication component 5, missile position marker control switch indication component 6, radar antenna elevation control switch indication component 7, and front wheel steering control rate selection switch indication component 8.

[0065] After the throttle lever assembly is manufactured or repaired, directly connect the throttle lever wiring harness plugs 118XPS and 119XPS. By toggling the eight switches T1 to T8 on the throttle lever assembly, directly observe the display on the throttle lever electrical control system test equipment to determine whether each switch and wiring harness is normal.

[0066] like Figure 16 and Figure 17 As shown, the side of the enclosure 100 is provided with a handle 106 for easy transport of the equipment. All indicator components are located on the control panel 101 on the top of the enclosure 100. The control panel 101 also includes a main switch 10, an external power socket 11, and a power selection switch 12.

[0067] like Figure 4 As shown, the 118XPS plug has output pins A, B, E, F, G, J, L, and M, and the front cabin 118XSP socket 102 has input pins A, B, E, F, G, J, L, and M. When the 118XPS plug is connected to the front cabin 118XSP socket 102, the T3 gearbox control switch is connected to the gearbox control switch test circuit, and the T4 transmit / receive control switch is connected to the transmit / receive control switch test circuit.

[0068] In this embodiment, the T3 gearshift control switch is connected to input pin A and output pin B of the 118XPS connector in the forward cabin 118XSP socket 102 via a 118XPS plug. The T3 gearshift control switch has two positions: on and off. When the T3 gearshift control switch is moved backward along the aircraft's heading, the T3 gearshift control switch is on; when released, the switch is off. The gearshift control switch indicator component 3 uses a green indicator light to indicate the switch status; the green light is on when the switch is on and off when it is released.

[0069] Specifically, such as Figure 7 As shown, when the T3 speed brake control switch is moved backward along the aircraft's heading, pins "C" and "NO" are connected. When the T3 speed brake control switch is released, pins "C" and "NO" are disconnected. Therefore, it can be pressed... Figure 7 As shown, the device uses a green LED to indicate the switch status, driven by a 9VDC voltage. When the T3 speed reducer controls the switch to be pulled back, the green light illuminates; when released, the green light goes out.

[0070] In this embodiment, the T4 transmit / receive control switch is connected to input pins E, F, G, and J of the 118XPS connector in the front cabin 118XSP socket 102 via a 118XPS plug. The T4 transmit / receive control switch has three positions: forward, middle, and rear. Pushing the T4 transmit / receive control switch forward along the aircraft's heading activates the forward position; placing it in the middle position activates the middle position; and pulling it backward activates the rear position. The transmit / receive control switch indicator component 4 uses yellow, red, and green lights to indicate the switch position. The yellow light illuminates when the T4 transmit / receive control switch is pushed forward; the red light illuminates when the T4 transmit / receive control switch is in the middle position; and the green light illuminates when the T4 transmit / receive control switch is pulled backward.

[0071] Specifically, such as Figure 8 As shown, when the T4 transmit / receive control switch is pushed forward along the aircraft's heading, pins "5" and "2" are connected, pins "5" and "4" are disconnected, and pins "5" and "3" are disconnected. When the T4 transmit / receive control switch is in the middle position, pins "5" and "2" are disconnected, pins "5" and "4" are connected, and pins "5" and "3" are disconnected. When the T4 transmit / receive control switch is flipped backward, pins "5" and "2" are disconnected, pins "5" and "4" are disconnected, and pins "5" and "3" are connected. Therefore, it can be pressed... Figure 8 As shown, the device uses yellow, red, and green LEDs to indicate the switch position, driven by a 9VDC voltage. When the T4 transmit / receive control switch is pushed forward, the yellow light illuminates; when it is in the middle position, the red light illuminates; and when it is pushed back, the green light illuminates.

[0072] like Figure 4As shown, the 119XPS connector has output pins A, B, C, D, E, F, G, H, J, K, L, M, N, P, R, S, T, U, and V, while the forward 119XSP socket 103 has input pins A, B, C, D, E, F, G, H, J, K, L, M, N, P, R, S, T, U, and V. When the 119XPS connector is connected to the forward 119XSP socket 103, the following circuits are connected: T1 Avionics Main Mode Switch and Avionics Main Mode Switch Test Circuit; T2 Electronic Warfare Switch and Electronic Warfare Switch Test Circuit; T5 Target Calibration Control Switch and Target Calibration Control Switch Test Circuit; T6 Missile Position Detector Control Switch and Target Calibration Control Switch Test Circuit; and T7 Radar Antenna Elevation Control Switch and Radar Antenna Elevation Control Switch Test Circuit.

[0073] In this embodiment, the T1 avionics main mode switch is connected to the input pins H, J, K, and L of the 119XPS connector in the forward cabin 119XSP socket 103 via a 119XPS plug. The T1 avionics main mode switch has three positions: forward, middle, and rear. Pushing the T1 avionics main mode switch forward along the aircraft's heading activates the forward position; placing it in the middle position activates the middle position; and pulling it backward activates the rear position. The avionics main mode switch indicator component 1 uses yellow, red, and green lights to indicate the switch position. When the T1 avionics main mode switch is pushed forward, the yellow light illuminates; when it is in the middle position, the red light illuminates; and when it is pulled backward, the green light illuminates.

[0074] Specifically, such as Figure 5 As shown, when the T1 avionics main mode switch is pushed forward along the aircraft's heading, pins "5" and "1" are connected, pins "5" and "3" are disconnected, and pins "5" and "6" are disconnected. When the T1 avionics main mode switch is in the middle position, pins "5" and "1" are disconnected, pins "5" and "3" are connected, and pins "5" and "6" are disconnected. When the T1 avionics main mode switch is flipped backward, pins "5" and "1" are disconnected, pins "5" and "3" are disconnected, and pins "5" and "6" are connected. Therefore, it can be used to... Figure 5 As shown, the equipment uses yellow, red, and green LEDs to indicate the switch position, driven by a 9VDC voltage. When the T1 avionics main mode switch is pushed forward, the yellow light illuminates; when it is in the middle position, the red light illuminates; and when it is pushed back, the green light illuminates.

[0075] In this embodiment, the T2 electronic warfare switch is connected to the input pins P, R, S, T, and U of the 119XPS connector in the forward cabin 119XSP socket 103 via a 119XPS plug. The T2 electronic warfare switch has three positions: forward, middle, and rear. Pushing the T2 electronic warfare switch forward along the aircraft's heading activates the forward position; placing it in the middle position activates the middle position; and pulling it backward activates the rear position. The electronic warfare switch indicator component 2 uses yellow, red, and green lights to indicate the switch position. When the T2 electronic warfare switch is pushed forward, the yellow light illuminates; when it is in the middle position, the red light illuminates; and when it is pulled backward, the green light illuminates.

[0076] Specifically, such as Figure 6 As shown, when the T2 electronic warfare switch is pushed forward along the aircraft's heading, pins 5 and 2 are connected, pins 5 and 4 are disconnected, and pins 5 and 3 are disconnected. When the T2 electronic warfare switch is in the middle position, pins 5 and 2 are disconnected, pins 5 and 4 are connected, and pins 5 and 3 are disconnected. When the T2 electronic warfare switch is flipped backward, pins 5 and 2 are disconnected, pins 5 and 4 are disconnected, and pins 5 and 3 are connected. Therefore, it can be used to... Figure 6 As shown, the device uses yellow, red, and green LEDs to indicate the switch position, driven by a 9VDC voltage. When the T2 electronic warfare switch is pushed forward, the yellow light illuminates; when it is in the middle position, the red light illuminates; and when it is pulled back, the green light illuminates.

[0077] In this embodiment, the T5 target calibration control switch is connected to input pins A, B, C, D, F, G, H, and N in the front cabin 119XSP socket 103 via a 119XPS plug. The T5 target calibration control switch consists of a force sensor and an on / off switch. The target calibration control switch indicator component 5 displays the detected V using a dual-channel voltmeter. X and V Y The voltage is indicated by red and green lights on the T5 target calibration control switch along its central axis. When the T5 target calibration control switch is moved up and down along the heading direction, the X-axis voltage V... X As the value of U / 2 changes, when the T5 target calibration control switch is flipped upwards, V... X When it gets bigger and is pulled down, V X The voltage decreases. When the T5 target calibration control switch is moved along the forward / backward direction, the Y-axis voltage V... Y As the value of U / 2 changes, when the T5 target calibration control switch is moved forward, V... Y When it gets bigger and is pulled back, V Y The target size decreases. When the T5 target calibration control switch is not pressed down along the central axis, the red light is on and the green light is off; when the T5 target calibration control switch is pressed down along the central axis, the green light is on and the red light is off.

[0078] Specifically, such as Figure 9 As shown, when a voltage U is applied between the "red" and "black" pins of the T5 target calibration control switch, the voltage between "blue" and "black" is the X-axis voltage, with a value of U / 2. The voltage between "gray" and "black" is the Y-axis voltage, with a value of U / 2. When the T5 target calibration control switch is moved up and down, the X-axis voltage V... X As the value of U / 2 changes, V changes when the lever is pulled upwards. X When it gets bigger and is pulled down, V X The voltage decreases. When the T5 target calibration control switch is moved in the forward / backward direction, the Y-axis voltage V... Y As the value of U / 2 changes, V changes when the lever is moved forward. Y When it gets bigger and is pulled back, V Y The target size decreases. When the T5 target calibration control switch is not pressed down along the central axis, pins 1 and 2 are connected, and pins 3 and 4 are disconnected. When the T5 target calibration control switch is pressed down along the central axis, pins 1 and 2 are disconnected, and pins 3 and 4 are connected. Therefore... Figure 9 As shown, a 9VDC voltage is used for driving, and the device part detects V through dual-channel voltmeters. X and V Y The voltage is detected by red and green LEDs, showing the state of the T5 target calibration control switch along its central axis. When the T5 target calibration control switch is moved up and down in the heading direction, the X-axis voltage V... X As the value of U / 2 changes, V changes when the lever is pulled upwards. X When it gets bigger and is pulled down, V X The voltage decreases. When the T5 target calibration control switch is moved along the forward / backward direction, the Y-axis voltage V... Y As the value of U / 2 changes, V changes when the lever is moved forward. Y When it gets bigger and is pulled back, V Y The target size decreases. When the T5 target calibration control switch is not pressed down along the central axis, the red light is on and the green light is off. When the T5 target calibration control switch is pressed down along the central axis, the green light is on and the red light is off.

[0079] In this embodiment, the T6 missile position indicator control switch is connected to input pins H and M of the 119XSP socket 103 in the forward compartment via a 119XPS plug. The T6 missile position indicator control switch has two states: on and off. When the T6 missile position indicator control switch is pressed, the switch is on; when the T6 missile position indicator control switch is released, the switch is off. The missile position indicator control switch indicator component 6 uses a green light to indicate the switch status. When the T6 missile position indicator control switch is pressed, the green light is on; when the T6 missile position indicator control switch is released, the green light is off.

[0080] Specifically, such as Figure 10As shown, when the T6 missile position indicator control switch is pressed, pins "1(4)" and "3" of the switch are connected. When the T6 missile position indicator control switch is released, pins "1(4)" and "3" of the switch are disconnected. Therefore, it is possible to press... Figure 9 As shown, the device uses a green LED to indicate the switch status, driven by a 9VDC voltage. When the T6 missile position indicator control switch is pressed, the green light illuminates; when released, the green light goes out.

[0081] In this embodiment, the T7 radar antenna elevation control switch is connected to input pins E, F, and G of the 119XPS connector in the front cabin 119XSP socket 103 via a 119XPS plug. The T7 radar antenna elevation control switch is a sliding rheostat switch. The radar antenna elevation control switch indicator component 7 uses a voltmeter to display the detected V. Y Voltage, when the T7 radar antenna pitch control switch is pushed forward along the heading, the voltage reading V Y When the T7 radar antenna elevation control switch is moved backward, the voltmeter reading V decreases. Y It gets bigger.

[0082] Specifically, such as Figure 11 As shown, when a voltage U is applied between pins "2" and "1" of the T7 radar antenna elevation control switch, the output voltage V between pins "3" and "1" will be... Y The value is U / 2. When the T7 radar antenna pitch control switch is moved along the aircraft's forward / backward direction, the voltage V... Y As the value of U / 2 changes, V propels forward along the heading. Y When it shrinks and is pulled back, V Y It grows larger. Therefore, as... Figure 11 As shown, a 9VDC voltage is used for driving, and the test equipment detects V through a voltmeter. Y Voltage. After power is applied, the voltmeter reading is U / 2 = 4.5VDC. The voltmeter reading V is as follows: When the T7 radar antenna elevation control switch is pushed forward along the heading... Y When the lever is pulled back, the voltmeter reading V decreases. Y It gets bigger.

[0083] like Figure 4 As shown, when the 118XPS plug is connected to the 118XSP socket 102 in the front compartment and the 119XPS plug is connected to the 119XSP socket 103 in the front compartment, the T8 front wheel steering control rate selection switch is connected to the front wheel steering control rate selection switch test circuit.

[0084] In this embodiment, the T8 front wheel steering control rate selection switch is connected to the input pins L and M of the front compartment 118XSP socket 102 via a 118XPS plug, and the T8 front wheel steering control rate selection switch is connected to the input pins H and V of the front compartment 119XSP socket 103 via a 119XPS plug. The front wheel steering control rate selection switch indicator component 8 uses red and green lights to indicate the switch status. When the T8 front wheel steering control rate selection switch is pressed, the green light is on and the red light is off; when the T8 front wheel steering control rate selection switch is released, the green light is off and the red light is on.

[0085] Specifically, such as Figure 12 As shown, when the T8 front wheel steering control rate selection switch is pressed, pins "1(4)" and "3" of the switch are connected, and pins "4(1)" and "2" are disconnected. When the T8 front wheel steering control rate selection switch is released, pins "1(4)" and "3" of the switch are disconnected, and pins "4(1)" and "2" are connected. The equipment uses red and green LEDs to indicate the switch status, driven by a 9VDC voltage. When the T8 front wheel steering control rate selection switch is pressed, the green light is on and the red light is off. When the T8 front wheel steering control rate selection switch is released, the green light is off and the red light is on.

[0086] To ensure equipment compatibility, testing was conducted on both single-seat and two-seat aircraft, including both the front and rear cockpit throttle levers. After studying the principle of the two-seat rear cockpit throttle lever, it was found that it functions identically to the single-seat and front cockpit throttle levers, differing only in the connector used on the aircraft: 450XPS and 453XPS. Figure 13 The schematic diagram of the throttle lever wiring harness in the front compartment of a two-seat aircraft is as follows: Figure 14 This is a schematic diagram of the wiring harness for the throttle lever in the rear compartment of a two-seat aircraft.

[0087] In this embodiment, the enclosure 100 also includes two adapter boards. The side of the enclosure 100 also features a rear cabin 450XSP socket 104 and a rear cabin 453XSP socket 105. The rear cabin 450XSP socket 104 and the front cabin 118XSP socket 102 are connected in parallel on one adapter board, and the rear cabin 453XSP socket 105 and the front cabin 119XSP socket 103 are connected in parallel on the other adapter board. The adapter boards are connected to the main control circuit to enable testing of single-seat or double-seat throttle lever assemblies. To ensure that both single-seat and double-seat throttle levers in the front and rear cabins can be tested, adapter wiring is involved, compatible with both single-seat and double-seat throttle levers in the front and rear cabins. The adapter wiring is as follows: Figure 15 As shown.

[0088] like Figure 17As shown, the equipment is equipped with front cabin 118XSP socket 102 and front cabin 119XSP socket 103, which are compatible with the 118XPS and 119XSP plugs of the single-seat or double-seat front cabin throttle lever. It is also equipped with rear cabin 450XSP socket 104 and rear cabin 453XSP socket 105, which are compatible with the 450XPS and 453XSP plugs of the double-seat rear cabin throttle lever. It is compatible with both single-seat and double-seat front and rear cabin throttle levers and can be tested.

[0089] Example 2

[0090] The test method for the electrical control system of the aircraft throttle lever assembly in this embodiment is implemented based on the test equipment for the electrical control system of the aircraft throttle lever assembly in Embodiment 1. The test of the throttle lever for a single-seat aircraft / the forward cockpit throttle lever for a two-seat aircraft includes the following steps:

[0091] Step S1: Connect the 118XPS and 119XPS plugs of the single-seat engine throttle lever or the front compartment throttle lever of the two-seat engine to the front compartment 118XSP socket 102 and the front compartment 119XSP socket 103 of the equipment, respectively. Figure 16 As shown, if using the built-in power supply, the power selection switch 12 should be set to "Internal Power" to power the device via the internal 9VDC battery. Alternatively, "External Power" can be selected. When selecting "External Power," a "220VAC to 9VDC" power adapter must be connected to the external power socket 11 on the control panel 101 and then connected to 220VAC AC power.

[0092] Step S2: Turn the main switch 10 on the control panel 101 to the "ON" position. The power voltage display 9 will show "9.00V".

[0093] Step S3, T1 Avionics Main Mode Switch Test: Push the T1 Avionics Main Mode Switch forward along the aircraft's heading. The yellow light in Avionics Main Mode Switch Indicator 1 will illuminate. When the T1 Avionics Main Mode Switch is in the middle position, the red light in Avionics Main Mode Switch Indicator 1 will illuminate. When the T1 Avionics Main Mode Switch is pulled back, the green light in Avionics Main Mode Switch Indicator 1 will illuminate.

[0094] Step S4, T2 Electronic Warfare Switch Test: Push the T2 electronic warfare switch forward along the aircraft's heading, and the yellow light of the electronic warfare switch indicator component 2 will illuminate. When the T2 electronic warfare switch is in the middle position, the red light of the electronic warfare switch indicator component 2 will illuminate. When the T2 electronic warfare switch is pulled back, the green light of the electronic warfare switch indicator component 2 will illuminate.

[0095] Step S5, T3 speed brake control switch test: For a single-seat aircraft, when the T3 speed brake control switch is pulled back along the aircraft's heading, the green light of the speed brake control switch indicator component 3 illuminates; when the T3 speed brake control switch is released, the green light of the speed brake control switch indicator component 3 goes out. For a two-seat aircraft in the front cabin, when the T3 speed brake control switch is pulled back along the aircraft's heading, the green light of the speed brake control switch indicator component 3 illuminates and the red light goes out; when the T3 speed brake control switch is pushed forward, the green light of the speed brake control switch indicator component 3 goes out and the red light illuminates.

[0096] Step S6, T4 Transmit / Receive Control Switch Test: When the T4 transmit / receive control switch is pushed forward along the aircraft's heading, the yellow light of the transmit / receive control switch indicator component 4 illuminates; when the T4 transmit / receive control switch is in the middle position, the red light of the transmit / receive control switch indicator component 4 illuminates; when the T4 transmit / receive control switch is pulled back, the green light of the transmit / receive control switch indicator component 4 illuminates.

[0097] Step S7, T5 Target Calibration Control Switch Test: When the equipment switch is turned on, the voltage V X and V Y All readings show U / 2 = 4.5V; when the T5 target calibration control switch is moved up and down in the heading direction, the X-axis voltage V... X The value changes from 4.5V; when the lever is turned upwards, V... X The voltage gradually increases from 4.5V. When the lever is pulled downwards, V... X The voltage gradually decreases from 4.5V; when the T5 target calibration control switch is moved in the forward / backward direction, the Y-axis voltage V... Y The value changes from 4.5V. When the lever is moved forward, V... Y The voltage gradually increases from 4.5V. When the lever is pulled backward, V... Y The voltage gradually decreases from 4.5V; when the T5 target calibration control switch is not pressed down along the central axis, the red light of the target calibration control switch indicator component 5 is on and the green light is off; when the T5 target calibration control switch is pressed down along the central axis, the green light of the target calibration control switch indicator component 5 is on and the red light is off.

[0098] Step S8, T6 missile position indicator control switch test: After the T6 missile position indicator control switch is pressed, the green light of the missile position indicator control switch indicator component 6 lights up, and when it is released, the green light goes out.

[0099] Step S9, T7 Radar Antenna Elevation Control Switch Test: When the device switch is turned on, the voltage V X The display shows U / 2 = 4.5V; when the T7 radar antenna elevation control switch is pushed forward along the heading, the voltage reading V of the radar antenna elevation control switch indicator component 7 is displayed. YAs the T7 radar antenna elevation control switch is moved backward, the voltage reading V of the radar antenna elevation control switch indicator component 7 gradually decreases from 4.5V. Y The voltage gradually increases from 4.5V.

[0100] Step S10, T8 front wheel steering control rate selection switch test: When the T8 front wheel steering control rate selection switch is pressed, the green light of the front wheel steering control rate selection switch indicator component 8 is on and the red light is off. When the T8 front wheel steering control rate selection switch is released, the green light of the front wheel steering control rate selection switch indicator component 8 is off and the red light is on.

[0101] When using the testing equipment of this invention, only one operator or inspector is needed to complete the test. Moreover, only the status lights and voltmeter on the equipment panel need to be observed, which provides strong visualization, reduces the likelihood of human error, and greatly saves testing time.

[0102] In other embodiments, when testing the throttle lever in the rear compartment of a two-seat aircraft:

[0103] Connect the 450XPS and 453XPS connectors on the rear throttle lever of the two-seat aircraft to the 450XSP and 453XSP connectors on the equipment, respectively. The testing method is the same as that for the single-seat aircraft throttle lever / two-seat aircraft front throttle lever. The testing of the T3 gearshift control switch is the same as that for the two-seat aircraft front T3 gearshift control switch; the two-seat aircraft rear throttle lever does not have a T1 avionics main mode switch.

[0104] The above description is merely a preferred embodiment of the present invention. The scope of protection of the present invention is not limited to the above embodiments. All technical solutions falling within the scope of the present invention's concept are within the scope of protection of the present invention. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principles of the present invention should also be considered within the scope of protection of the present invention.

Claims

1. A test device for the electrical control system of an aircraft throttle lever assembly, wherein the throttle lever assembly includes: a T1 avionics main mode switch, a T2 electronic warfare switch, a T3 speed brake control switch, a T4 transmit / receive control switch, a T5 target calibration control switch, a T6 missile position indicator control switch, a T7 radar antenna elevation control switch, and a T8 nose wheel steering rate selection switch; the wiring harness connectors of the throttle lever assembly include 118XPS connectors and 119XPS connectors; characterized in that... The testing equipment includes a housing (100), in which a main control circuit is provided. The side of the housing (100) is provided with a front compartment 118XSP socket (102) and a front compartment 119XSP socket (103). The main control circuit is connected to the 118XPS plug and 119XPS plug of the throttle lever assembly through the front compartment 118XSP socket (102) and the front compartment 119XSP socket (103). The main control circuit includes multiple parallel test sub-circuits and corresponding indicator components. The test sub-circuits are used to detect the status of the throttle lever assembly, and the indicator components are used to display the status of the throttle lever assembly in real time. The test sub-circuits include: avionics main mode switch test circuit, electronic warfare switch test circuit, speed brake control switch test circuit, transmit / receive control switch test circuit, target calibration control switch test circuit, missile position marker control switch test circuit, radar antenna elevation control switch test circuit, and front wheel steering control rate selection switch test circuit. The indicator components include: avionics main mode switch indicator component (1), electronic warfare switch indicator component (2), speed brake control switch indicator component (3), transmit / receive control switch indicator component (4), target identification control switch indicator component (5), missile position indicator control switch indicator component (6), radar antenna elevation control switch indicator component (7), and front wheel steering control rate selection switch indicator component (8). When testing using the aforementioned aircraft throttle lever assembly electrical control system testing equipment, the following steps are included: Step S1: Connect the 118XPS plug and 119XPS plug of the throttle lever to the 118XSP socket (102) and 119XSP socket (103) in the front compartment of the test equipment, respectively. Step S2: Turn the main switch (10) on the enclosure (100) to the "ON" position. The power supply voltage display (9) will display "UV". Step S3, T1 Avionics Main Mode Switch Test: Push the T1 Avionics Main Mode Switch forward along the aircraft heading, the yellow light in the Avionics Main Mode Switch Indicator Component (1) will light up; when the T1 Avionics Main Mode Switch is in the middle position, the red light in the Avionics Main Mode Switch Indicator Component (1) will light up; when the T1 Avionics Main Mode Switch is pulled back, the green light in the Avionics Main Mode Switch Indicator Component (1) will light up. Step S4, T2 electronic warfare switch test: Push the T2 electronic warfare switch forward along the aircraft's heading, the yellow light of the electronic warfare switch indicator component (2) will light up; when the T2 electronic warfare switch is in the middle position, the red light of the electronic warfare switch indicator component (2) will light up; when the T2 electronic warfare switch is pulled back, the green light of the electronic warfare switch indicator component (2) will light up. Step S5, T3 speed brake control switch test: For a single-seat aircraft, when the T3 speed brake control switch is pulled back along the aircraft's heading, the green light of the speed brake control switch indicator component (3) illuminates; when the T3 speed brake control switch is released, the green light of the speed brake control switch indicator component (3) goes out. For a two-seat aircraft in the front cabin, when the T3 speed brake control switch is pulled back along the aircraft's heading, the green light of the speed brake control switch indicator component (3) illuminates and the red light goes out; when the T3 speed brake control switch is pushed forward, the green light of the speed brake control switch indicator component (3) goes out and the red light illuminates. Step S6, T4 transmit / receive control switch test: When the T4 transmit / receive control switch is pushed forward along the aircraft heading, the yellow light of the transmit / receive control switch indicator component (4) is lit; when the T4 transmit / receive control switch is in the middle position, the red light of the transmit / receive control switch indicator component (4) is lit; when the T4 transmit / receive control switch is pulled back, the green light of the transmit / receive control switch indicator component (4) is lit. Step S7, T5 Target Calibration Control Switch Test: When the equipment switch is turned on, the voltage V X and V Y All display (U / 2) V; when the T5 target calibration control switch is moved up and down in the heading direction, the X-axis voltage V X As the value of (U / 2)V changes, when the lever is moved upwards, V... X As (U / 2)V gradually increases, when the lever is pulled downwards, V X The voltage (U / 2)V gradually decreases; when the T5 target calibration control switch is moved along the forward and backward direction, the Y-axis voltage V... Y As the value of (U / 2)V changes, when the lever is moved forward, V Y As (U / 2)V gradually increases, when it is pulled backward, V Y The value of (U / 2)V gradually decreases; when the T5 target calibration control switch is not pressed down along the central axis, the red light of the target calibration control switch indicator component (5) is on and the green light is off; when the T5 target calibration control switch is pressed down along the central axis, the green light of the target calibration control switch indicator component (5) is on and the red light is off. Step S8, T6 missile position indicator control switch test: After the T6 missile position indicator control switch is pressed, the green light of the missile position indicator control switch indicator component (6) lights up, and when it is released, the green light goes out; Step S9, T7 Radar Antenna Elevation Control Switch Test: When the device switch is turned on, the voltage V X When the radar antenna pitch control switch (U / 2) V;T7 is pushed forward along the heading, the voltage reading V of the radar antenna pitch control switch indicator component (7) is displayed. Y As (U / 2)V gradually decreases, when the T7 radar antenna elevation control switch is moved backward, the voltage reading V of the radar antenna elevation control switch indicator component (7) changes. Y The value of (U / 2)V gradually increases. Step S10, T8 front wheel steering control rate selection switch test: After the T8 front wheel steering control rate selection switch is pressed, the green light of the front wheel steering control rate selection switch indicator component (8) is on and the red light is off. When the T8 front wheel steering control rate selection switch is released, the green light of the front wheel steering control rate selection switch indicator component (8) is off and the red light is on.

2. The test equipment for the electrical control system of the aircraft throttle lever assembly according to claim 1, characterized in that, The enclosure (100) is also equipped with two adapter boards. The side of the enclosure (100) is also equipped with a rear cabin 450XSP socket (104) and a rear cabin 453XSP socket (105). The rear cabin 450XSP socket (104) and the front cabin 118XSP socket (102) are connected in parallel on one adapter board, and the rear cabin 453XSP socket (105) and the front cabin 119XSP socket (103) are connected in parallel on the other adapter board. The adapter board is connected to the main control circuit to realize the testing of single-seat throttle lever assembly or double-seat throttle lever assembly.

3. The test equipment for the electrical control system of the aircraft throttle lever assembly according to claim 2, characterized in that, The 118XPS plug has output pins A, B, E, F, G, J, L and M, and the front cabin 118XSP socket (102) has input pins A, B, E, F, G, J, L and M. When the 118XPS plug is connected to the front cabin 118XSP socket (102), the T3 decelerator control switch is connected to the decelerator control switch test circuit, and the T4 transmit / receive control switch is connected to the transmit / receive control switch test circuit.

4. The test equipment for the electrical control system of the aircraft throttle lever assembly according to claim 3, characterized in that, The T3 speed brake control switch is connected to the input pin A and output pin B of the 118XPS connector in the front cabin 118XSP socket (102) via a 118XPS plug. The T3 speed brake control switch has two positions: on and off. When the T3 speed brake control switch is moved backward along the aircraft heading, the T3 speed brake control switch is on, and when it is released, the switch is off. The speed brake control switch indicator component (3) uses a "green" indicator light to indicate the switch status. When it is on, the green light is on, and when it is released, the green light is off. The T4 transmit / receive control switch is connected to the input pins E, F, G and J of the 118XPS connector (102) in the front cabin via a 118XPS plug. The T4 transmit / receive control switch has three positions: forward, middle and rear. When the T4 transmit / receive control switch is pushed forward along the aircraft heading, it is in the forward position. When the T4 transmit / receive control switch is in the middle position, it is in the middle position. When the T4 transmit / receive control switch is pulled back, it is in the rear position. The transmit / receive control switch indicator component (4) uses "yellow", "red" and "green" lights to indicate the switch position. When the T4 transmit / receive control switch is pushed forward, the yellow light is on. When the T4 transmit / receive control switch is in the middle position, the red light is on. When the T4 transmit / receive control switch is pulled back, the green light is on.

5. The test equipment for the electrical control system of the aircraft throttle lever assembly according to claim 3, characterized in that, The 119XPS plug has output pins A, B, C, D, E, F, G, H, J, K, L, M, N, P, R, S, T, U, and V, and the front cabin 119XSP socket (103) has input pins A, B, C, D, E, F, G, H, J, K, L, M, N, P, R, S, T, U, and V. When the 119XPS plug is connected to the front cabin 119XSP socket (103), the T1 avionics main mode switch is connected to the avionics main mode switch test circuit, the T2 electronic warfare switch is connected to the electronic warfare switch test circuit, the T5 target calibration control switch is connected to the target calibration control switch test circuit, the T6 missile position marker control switch is connected to the target calibration control switch test circuit, and the T7 radar antenna elevation control switch is connected to the radar antenna elevation control switch test circuit.

6. The test equipment for the electrical control system of the aircraft throttle lever assembly according to claim 5, characterized in that, The T1 avionics main mode switch is connected to the input pins H, J, K and L of the 119XPS connector (103) in the front cabin via a 119XPS plug. The T1 avionics main mode switch has three positions: forward, middle and rear. When the T1 avionics main mode switch is pushed forward along the aircraft heading, it is in the forward position. When the T1 avionics main mode switch is in the middle position, it is in the middle position. When the T1 avionics main mode switch is pulled back, it is in the rear position. The avionics main mode switch indicator component (1) uses three-color lights, namely "yellow", "red" and "green", to indicate the switch position. When the T1 avionics main mode switch is pushed forward, the yellow light is on. When the T1 avionics main mode switch is in the middle position, the red light is on. When the T1 avionics main mode switch is pulled back, the green light is on. The T2 electronic warfare switch is connected to the input pins P, R, S, T and U of the 119XSP socket (103) in the front cabin via a 119XPS plug. The T2 electronic warfare switch has three positions: forward, middle and rear. When the T2 electronic warfare switch is pushed forward along the aircraft's heading, it is in the forward position. When the T2 electronic warfare switch is in the middle position, it is in the middle position. When the T2 electronic warfare switch is pulled back, it is in the rear position. The electronic warfare switch indicator component (2) uses three-color lights, namely "yellow", "red" and "green", to indicate the switch position. When the T2 electronic warfare switch is pushed forward, the yellow light is on. When the T2 electronic warfare switch is in the middle position, the red light is on. When the T2 electronic warfare switch is pulled back, the green light is on.

7. The test equipment for the electrical control system of the aircraft throttle lever assembly according to claim 5, characterized in that, The T5 target calibration control switch is connected to the input pins A, B, C, D, F, G, H, and N of the 119XPS connector in the front cabin 119XSP socket (103) via a 119XPS plug. The T5 target calibration control switch consists of a force sensor and an on / off switch. The target calibration control switch indicator component (5) displays the detected V using a dual-channel voltmeter. X and V Y The voltage is indicated by red and green lights showing the status of the T5 target calibration control switch along its central axis; when the T5 target calibration control switch is moved up and down along the heading direction, the X-axis voltage V... X As the value of U / 2 changes, when the T5 target calibration control switch is flipped upwards, V... X When it gets bigger and is pulled down, V X The voltage decreases; when the T5 target calibration control switch is moved along the forward / backward direction, the Y-axis voltage V... Y As the value of U / 2 changes, when the T5 target calibration control switch is moved forward, V Y When it gets bigger and is pulled back, V Y When the T5 target calibration control switch is not pressed down along the central axis, the red light is on and the green light is off; when the T5 target calibration control switch is pressed down along the central axis, the green light is on and the red light is off.

8. The test equipment for the electrical control system of the aircraft throttle lever assembly according to claim 5, characterized in that, The T6 missile position indicator control switch is connected to the input pins H and M of the 119XPS connector (103) in the front cabin via a 119XPS plug. The T6 missile position indicator control switch has two states: on and off. When the T6 missile position indicator control switch is pressed, the switch is on; when the T6 missile position indicator control switch is released, the switch is off. The missile position indicator control switch indicator component (6) uses a "green" light to indicate the switch state. When the T6 missile position indicator control switch is pressed, the green light is on; when the T6 missile position indicator control switch is released, the green light is off.

9. The test equipment for the electrical control system of the aircraft throttle lever assembly according to claim 5, characterized in that, The T7 radar antenna elevation control switch is connected to the input pins E, F, and G of the 119XPS connector (103) in the front cabin via a 119XPS plug. The T7 radar antenna elevation control switch is a sliding rheostat switch. The radar antenna elevation control switch indicator assembly (7) displays the detected V using a voltmeter. Y Voltage, when the T7 radar antenna pitch control switch is pushed forward along the heading, the voltage reading V Y When the T7 radar antenna elevation control switch is moved backward, the voltmeter reading V decreases. Y It gets bigger.

10. The test equipment for the electrical control system of the aircraft throttle lever assembly according to any one of claims 5 to 9, characterized in that, When the 118XPS plug is connected to the 118XSP socket (102) in the front compartment and the 119XPS plug is connected to the 119XSP socket (103) in the front compartment, the T8 front wheel steering control rate selection switch is connected to the front wheel steering control rate selection switch test circuit. The T8 front wheel steering control rate selection switch is connected to the input pins L and M of the front compartment 118XSP socket (102) via a 118XPS plug, and the T8 front wheel steering control rate selection switch is connected to the input pins H and V of the front compartment 119XSP socket (103) via a 119XPS plug; the front wheel steering control rate selection switch indicator component (8) uses "red" and "green" lights to indicate the switch status. When the T8 front wheel steering control rate selection switch is pressed, the green light is on and the red light is off; when the T8 front wheel steering control rate selection switch is released, the green light is off and the red light is on.

11. A test method for an aircraft throttle lever assembly electrical control system test device according to any one of claims 1 to 10, characterized in that, Includes the following steps: Step S1: Connect the 118XPS plug and 119XPS plug of the throttle lever to the 118XSP socket (102) and 119XSP socket (103) in the front compartment of the test equipment, respectively. Step S2: Turn the main switch (10) on the enclosure (100) to the "ON" position. The power supply voltage display (9) will display "UV". Step S3, T1 Avionics Main Mode Switch Test: Push the T1 Avionics Main Mode Switch forward along the aircraft heading, the yellow light in the Avionics Main Mode Switch Indicator Component (1) will light up; when the T1 Avionics Main Mode Switch is in the middle position, the red light in the Avionics Main Mode Switch Indicator Component (1) will light up; when the T1 Avionics Main Mode Switch is pulled back, the green light in the Avionics Main Mode Switch Indicator Component (1) will light up. Step S4, T2 electronic warfare switch test: Push the T2 electronic warfare switch forward along the aircraft's heading, the yellow light of the electronic warfare switch indicator component (2) will light up; when the T2 electronic warfare switch is in the middle position, the red light of the electronic warfare switch indicator component (2) will light up; when the T2 electronic warfare switch is pulled back, the green light of the electronic warfare switch indicator component (2) will light up. Step S5, T3 speed brake control switch test: For a single-seat aircraft, when the T3 speed brake control switch is pulled back along the aircraft's heading, the green light of the speed brake control switch indicator component (3) illuminates; when the T3 speed brake control switch is released, the green light of the speed brake control switch indicator component (3) goes out. For a two-seat aircraft in the front cabin, when the T3 speed brake control switch is pulled back along the aircraft's heading, the green light of the speed brake control switch indicator component (3) illuminates and the red light goes out; when the T3 speed brake control switch is pushed forward, the green light of the speed brake control switch indicator component (3) goes out and the red light illuminates. Step S6, T4 transmit / receive control switch test: When the T4 transmit / receive control switch is pushed forward along the aircraft heading, the yellow light of the transmit / receive control switch indicator component (4) is lit; when the T4 transmit / receive control switch is in the middle position, the red light of the transmit / receive control switch indicator component (4) is lit; when the T4 transmit / receive control switch is pulled back, the green light of the transmit / receive control switch indicator component (4) is lit. Step S7, T5 Target Calibration Control Switch Test: When the equipment switch is turned on, the voltage V X and V Y All display (U / 2) V; when the T5 target calibration control switch is moved up and down in the heading direction, the X-axis voltage V X As the value of (U / 2)V changes, when the lever is moved upwards, V... X As (U / 2)V gradually increases, when the lever is pulled downwards, V X The voltage (U / 2)V gradually decreases; when the T5 target calibration control switch is moved along the forward and backward direction, the Y-axis voltage V... Y As the value of (U / 2)V changes, when the lever is moved forward, V Y As (U / 2)V gradually increases, when it is pulled backward, V Y The value of (U / 2)V gradually decreases; when the T5 target calibration control switch is not pressed down along the central axis, the red light of the target calibration control switch indicator component (5) is on and the green light is off; when the T5 target calibration control switch is pressed down along the central axis, the green light of the target calibration control switch indicator component (5) is on and the red light is off. Step S8, T6 missile position indicator control switch test: After the T6 missile position indicator control switch is pressed, the green light of the missile position indicator control switch indicator component (6) lights up, and when it is released, the green light goes out; Step S9, T7 Radar Antenna Elevation Control Switch Test: When the device switch is turned on, the voltage V X When the radar antenna pitch control switch (U / 2) V;T7 is pushed forward along the heading, the voltage reading V of the radar antenna pitch control switch indicator component (7) is displayed. Y As (U / 2)V gradually decreases, when the T7 radar antenna elevation control switch is moved backward, the voltage reading V of the radar antenna elevation control switch indicator component (7) changes. Y The value of (U / 2)V gradually increases. Step S10, T8 front wheel steering control rate selection switch test: After the T8 front wheel steering control rate selection switch is pressed, the green light of the front wheel steering control rate selection switch indicator component (8) is on and the red light is off. When the T8 front wheel steering control rate selection switch is released, the green light of the front wheel steering control rate selection switch indicator component (8) is off and the red light is on.

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