Aircraft throttle lever assembly electrical control system test device and test method

Abstract

The invention discloses airplane throttle lever assembly electrical control system test equipment and a test method, a box body of the equipment is internally provided with a general control circuit, a forecabin 118 XSP socket and a forecabin 119 XSP socket, and the general control circuit is connected with a throttle lever assembly through the forecabin 118 XSP socket and the forecabin 119 XSP socket; the general control circuit comprises a plurality of parallel test sub-circuits and corresponding indication assemblies, the test sub-circuits are matched with switches on the accelerator assembly so as to detect the state of the accelerator lever assembly, and the indication assemblies are used for displaying the state of the accelerator lever assembly in real time and displaying the state of the accelerator lever assembly according to signals fed back by the indication assemblies. Therefore, the state of the throttle lever assembly can be visually judged. The device has the characteristics of small size, high test efficiency, high stability and the like, and the test cost of the throttle lever assembly is effectively saved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft throttle lever maintenance, and in particular to an aircraft throttle lever assembly electrical control system testing device and a testing method. Background Art

[0002] In a certain type of aircraft, in addition to the function of mechanically controlling the throttle size, the throttle lever assembly has a variety of control switches integrated on the throttle lever assembly control handle, so that the pilot can control multiple functions without leaving the lever during flight. Including T1: avionics main mode switch, T2: electronic warfare switch, T3: speed brake control switch, T4: transmit / receive control switch, T5: target calibration control switch, T6: missile position marker control (GAGE) switch, T7: radar antenna pitch control switch, T8: nose wheel turn (NWS) control rate selection switch. At present, during the manufacturing and repair process of the existing throttle lever assembly operating handle, simple conduction test and visual inspection methods are often used to check whether the welding of each switch is correct. There is a lack of offline test equipment, and it is impossible to perform offline functional testing on the electrical control part of the throttle lever assembly. Functional testing mainly relies on the on-board power-on inspection after the throttle lever assembly is installed.

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

[0004] (1) Offline functional testing of the electrical control system T1 to T8 of a certain type of engine throttle lever assembly cannot be performed.

[0005] (2) Post-repair testing and inspection test time is long. In the past, after the throttle lever assembly was manufactured and repaired, the operator could only test the on / off status of the throttle lever assembly T1~T8 switches one by one by conducting, and two people were required to cooperate in the operation. The test time was about 20 minutes. The inspection personnel also needed two people to cooperate in the completion inspection, and the test time was about 20 minutes.

[0006] (3) Human error is prone to occur. In the past, after the manufacture and repair of the throttle lever assembly of this type of engine, the T1 to T8 switches were tested for continuity one by one, which was a large workload and prone to human error.

[0007] (4) When the throttle lever assembly is tested on the aircraft, if any quality problems are found, it needs to be removed from the aircraft and reworked. When removing the throttle lever assembly, all cockpit-related interference equipment needs to be removed, which results in a large workload and high rework costs. Summary of the invention

[0008] The technical problem to be solved by the present invention is that, in view of the fact that human factors in the prior art have a great influence on the measurement results of the throttle lever assembly, and that low-level quality problems of the second generation are easily caused by human factors; and that after the throttle lever assembly is installed, problems with the throttle lever assembly switch and wiring harness often lead to defects such as malfunction when the whole machine is tested on an aircraft. The present invention provides an aircraft throttle lever assembly electrical control system test device and a test method that have a compact structure, are easy to operate, have high stability and high visualization.

[0009] In order to solve the above technical problems, the technical solution adopted by the present invention is:

[0010] A test device for an electrical control system of an aircraft throttle lever assembly, wherein the throttle lever assembly is provided with: a T1 avionics main mode switch, a T2 electronic warfare switch, a T3 speed brake control switch, a T4 transmission / reception control switch, a T5 target calibration control switch, a T6 missile position marker control switch, a T7 radar antenna pitch control switch and a T8 front wheel turning control rate selection switch, and the wiring harness plug of the throttle lever assembly includes a 118XPS plug and a 119XPS plug; the test device includes a box body, wherein a master control circuit is provided in the box body, and a front cabin 118XSP socket and a front cabin 119XSP socket are provided on the side of the box body, and the master control circuit is connected with the 118XPS plug and the 119XPS plug of the throttle lever assembly through the front cabin 118XSP socket and the front cabin 119XSP socket; the master control circuit includes a plurality of parallel test subcircuits and corresponding indication components, wherein the test subcircuits are used to detect the state of the throttle lever assembly, and the indication component is used to display the state of the throttle lever assembly in real time;

[0011] The test subcircuit includes: an avionics main mode switch test circuit, an electronic warfare switch test circuit, a speed brake control switch test circuit, a transmit / receive control switch test circuit, a target calibration control switch test circuit, a missile position marker control switch test circuit, a radar antenna pitch control switch test circuit and a front wheel turn control rate selection switch test circuit;

[0012] The indication components include: an avionics main mode switch indication component, an electronic warfare switch indication component, a speed brake control switch indication component, a transmit / receive control switch indication component, a target calibration control switch indication component, a missile position marker control switch indication component, a radar antenna pitch control switch indication component and a front wheel turn control rate selection switch indication component.

[0013] As a further improvement of the present invention, two adapter plates are further provided in the box body, and a rear cabin 450XSP socket and a rear cabin 453XSP socket are further provided on the side of the box body; the rear cabin 450XSP socket and the front cabin 118XSP socket are connected in parallel on one of the adapter plates, and the rear cabin 453XSP socket and the front cabin 119XSP socket are connected in parallel on the other adapter plate, and the adapter plate is connected to the master control circuit to realize the test of a single-seat throttle lever assembly or a 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 with the front cabin 118XSP socket, the T3 speed brake control switch is connected with the speed brake control switch test circuit, and the T4 transmit / receive control switch is connected with the transmit / receive control switch test circuit.

[0015] As a further improvement of the present invention, the T3 deceleration brake control switch is connected to the input pin A and the output pin B in the 118XSP socket in the front cabin through the 118XPS plug, and the T3 deceleration brake control switch is divided into on and off positions; when the T3 deceleration brake control switch is pulled backward along the aircraft heading, the T3 deceleration brake control switch is turned on, and when it is released, the switch is turned off; the deceleration brake control switch indicator assembly uses a "green" indicator light to indicate the switch state, the green light is on when it is turned on, and the green light is off when it is released;

[0016] The T4 transmit / receive control switch is connected to the input pins E, F, G and J in the 118XSP socket in the front cabin through the 118XPS plug. The T4 transmit / receive control switch is divided into three gears: front, middle and rear. When the T4 transmit / receive control switch is pushed forward along the aircraft heading, it is the front gear, when the T4 transmit / receive control switch is placed in the middle position, it is the middle gear, and when the T4 transmit / receive control switch is pulled backward, it is the rear gear; the transmit / receive control switch indication component uses "yellow", "red" and "green" three-color lights to indicate the switch position respectively. When the T4 transmit / receive control switch is pushed forward, the yellow light is on, when the T4 transmit / receive control switch is placed in the middle position, the red light is on, and when the T4 transmit / receive control switch is pulled backward, 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 front cabin 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 with the front cabin 119XSP socket, the T1 avionics main mode switch is connected with the avionics main mode switch test circuit, the T2 electronic warfare switch is connected with the electronic warfare switch test circuit, the T5 target calibration control switch is connected with the target calibration control switch test circuit, the T6 missile position marker control switch is connected with the target calibration control switch test circuit, and the T7 radar antenna pitch control switch is connected with the radar antenna pitch 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 in the front cabin 119XSP socket through the 119XPS plug. The T1 avionics main mode switch is divided into three gears: front, middle and rear. When the T1 avionics main mode switch is pushed forward along the aircraft heading, it is the front gear, when the T1 avionics main mode switch is placed in the middle position, it is the middle gear, and when the T1 avionics main mode switch is pulled back, it is the rear gear; the avionics main mode switch indication component uses "yellow", "red" and "green" three-color lights 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 placed 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 in the 119XSP socket in the front cabin through the 119XPS plug. The T2 electronic warfare switch is divided into three gears: front, middle and rear. When the T2 electronic warfare switch is pushed forward along the aircraft heading, it is the front gear, when the T2 electronic warfare switch is placed in the middle position, it is the middle gear, and when the T2 electronic warfare switch is pulled backward, it is the rear gear; the electronic warfare switch indication component uses "yellow", "red" and "green" three-color 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 placed in the middle position, the red light is on, and when the T2 electronic warfare switch is pulled backward, the green light is on.

[0020] As a further improvement of the present invention, the T5 target calibration control switch is connected to the input pins A, B, C, D, F, G, H and N in the front compartment 119XSP socket through the 119XPS plug. The T5 target calibration control switch is composed of a force sensitive sensor and an on-off switch. The target calibration control switch indicator component uses a dual-channel voltmeter to display the detection V X and V YVoltage, with "red" and "green" two-color lights to display the state of the T5 target calibration control switch along the center axis of the switch; when the T5 target calibration control switch is turned up and down, the X-axis voltage V X Since the U / 2 value changes, when the T5 target calibration control switch is turned upward, V X When you pull it down, V X When the T5 target calibration control switch is turned in the forward and backward direction, the Y-axis voltage V Y Since the U / 2 value changes, when the T5 target calibration control switch is moved forward, V Y When you pull it back, V Y becomes smaller; when the T5 target calibration control switch is not pressed down along the center axis, the red light is on and the green light is off; when the T5 target calibration control switch is pressed down along the center 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 marker control switch is connected to the input pins H and M in the front cabin 119XSP socket through the 119XPS plug. The T6 missile position marker control switch is divided into two states: on and off. When the T6 missile position marker control switch is pressed, the switch is turned on. When the T6 missile position marker control switch is released, the switch is disconnected. The missile position marker control switch indicator component uses a "green" light to indicate the switch state. After the T6 missile position marker control switch is pressed, the green light is on. When the T6 missile position marker control switch is released, the green light is off.

[0022] As a further improvement of the present invention, the T7 radar antenna pitch control switch is connected to the input pins E, F and G in the front cabin 119XSP socket through the 119XPS plug, and the T7 radar antenna pitch control switch is a sliding rheostat switch; the radar antenna pitch control switch indicator component uses a voltmeter to display the detection V Y Voltage, when the T7 radar antenna pitch control switch is pushed forward along the heading, the voltage is expressed in V Y When the T7 radar antenna pitch control switch is moved backward, the voltage is displayed as V. Y Get bigger.

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

[0024] The T8 front wheel turning control rate selection switch is connected to the input pins L and M of the 118XSP socket in the front cabin through the 118XPS plug, and the T8 front wheel turning control rate selection switch is connected to the input pins H and V of the 119XSP socket in the front cabin through the 119XPS plug; the front wheel turning control rate selection switch indicator component uses "red" and "green" lights to indicate the switch state. When the T8 front wheel turning control rate selection switch is pressed, the green light is on and the red light is off; when the T8 front wheel turning 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 aircraft throttle lever assembly electrical control system test device, comprising the following steps:

[0026] Step S1, connecting the 118XPS plug and the 119XPS plug of the throttle lever to the front cabin 118XSP socket and the front cabin 119XSP socket of the test equipment respectively;

[0027] Step S2, turn on the main switch on the box to the "on" position, and the power supply voltage display screen displays "UV";

[0028] Step S3, T1 avionics main mode switch test: When the T1 avionics main mode switch is pushed forward along the aircraft heading, the yellow light in the avionics main mode switch indicator assembly is on; when the T1 avionics main mode switch is placed in the middle position, the red light in the avionics main mode switch indicator assembly is on; when the T1 avionics main mode switch is pulled backward, the green light in the avionics main mode switch indicator assembly is on;

[0029] Step S4, T2 electronic warfare switch test: When the T2 electronic warfare switch is pushed forward along the aircraft heading, the yellow light of the electronic warfare switch indicator assembly is on; when the T2 electronic warfare switch is placed in the middle position, the red light of the electronic warfare switch indicator assembly is on; when the T2 electronic warfare switch is pulled backward, the green light of the electronic warfare switch indicator assembly is on;

[0030] Step S5, T3 speed brake control switch test: for a single-seat aircraft, the T3 speed brake control switch is pulled backward along the aircraft heading, and the green light of the speed brake control switch indicator assembly is on. When the T3 speed brake control switch is released, the green light of the speed brake control switch indicator assembly is off. For the front cabin of a two-seat aircraft, when the T3 speed brake control switch is pulled backward along the aircraft heading, the green light of the speed brake control switch indicator assembly is on and the red light is off. When the T3 speed brake control switch is pushed forward, the green light of the speed brake control switch indicator assembly is off and the red light is on.

[0031] 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 assembly is on; when the T4 transmit / receive control switch is in the middle position, the red light of the transmit / receive control switch indicator assembly is on; when the T4 transmit / receive control switch is pulled backward, the green light of the transmit / receive control switch indicator assembly is on;

[0032] Step S7, T5 target calibration control switch test: when the device switch is turned on, the voltage V X and V Y Both display (U / 2)V; when the T5 target calibration control switch is turned up and down, the X-axis voltage V X The value of (U / 2)V changes. When you turn it upward, V X It gradually increases from (U / 2)V. When it is pulled downward, V X It gradually decreases from (U / 2)V; when the T5 target calibration control switch is turned in the forward and backward direction, the Y-axis voltage V Y The value of (U / 2)V changes. When you push it forward, V Y It gradually increases from (U / 2)V. When it is pulled back, V Y It gradually decreases from (U / 2)V; when the T5 target calibration control switch is not pressed down along the center 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 center 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 marker control switch test: After the T6 missile position marker control switch is pressed, the green light of the missile position marker control switch indicator component is on, and when it is released, the green light goes out;

[0034] Step S9, T7 radar antenna pitch control switch test: When the device switch is turned on, the voltage V X Display (U / 2)V; when the T7 radar antenna pitch control switch is pushed forward along the heading, the voltage of the radar antenna pitch control switch indicator component is displayed in V Y It gradually decreases from (U / 2)V. When the T7 radar antenna pitch control switch is turned back, the voltage of the radar antenna pitch control switch indicator component indicates the number V. Y It gradually increases from (U / 2)V;

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

[0037] The aircraft throttle lever assembly electrical control system test equipment and test method of the present invention are provided with a master control circuit, a front cabin 118XSP socket and a front cabin 119XSP socket in the box of the equipment, and the master control circuit is connected to the throttle lever assembly through the front cabin 118XSP socket and the front cabin 119XSP socket, and the operation is simple and the connection is reliable; further, the master control circuit includes a plurality of parallel test sub-circuits and corresponding indication components, and the test sub-circuits are matched with each switch on the throttle assembly, and the state of the throttle lever assembly is detected by the test sub-circuit, and the state of the throttle lever assembly is displayed in real time by the indication component. According to the signal fed back by the indication component, the state of the throttle lever assembly can be intuitively judged, and the visualization is strong, and it is not easy to produce human errors. In the past, the T1-T8 switches on the throttle lever assembly were turned on one by one, which was labor-intensive and prone to human errors. The present invention only requires one person to complete the test, and the test time is no more than two minutes, which reduces human errors and significantly improves the efficiency of the throttle lever assembly test. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 It is a schematic diagram of the connection relationship between the throttle lever assembly and the aircraft system;

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

[0040] Figure 3 It is a schematic diagram of the connection relationship between the throttle lever assembly and the test equipment in a specific embodiment of the present invention;

[0041] Figure 4 It is a schematic diagram of the circuit principle inside the test equipment in a specific embodiment of the present invention;

[0042] Figure 5 It is a schematic diagram of the principle 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 principle of the T2 electronic warfare switch test circuit in a specific embodiment of the present invention;

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

[0045] Figure 8 It is a schematic diagram of the principle of the T4 transmission / reception control switch test circuit in a specific embodiment of the present invention;

[0046] Fig. 9 It is a schematic diagram of the principle of the T5 target calibration control switch test circuit in a specific embodiment of the present invention;

[0047] Fig.10 It is a schematic diagram of the principle of the T6 missile coordinator control (GAGE) switch test circuit in a specific embodiment of the present invention;

[0048] Fig.11 It is a schematic diagram of the principle of the pitch control switch test circuit of the T7 radar antenna in a specific embodiment of the present invention;

[0049] Fig.12 It is a schematic diagram of the principle of the T8 front wheel turning (NWS) control rate selection switch test circuit in a specific embodiment of the present invention;

[0050] Fig.13 This is a schematic diagram of the wiring harness connection principle of the two-seat front cabin throttle lever assembly;

[0051] Fig.14 This is a schematic diagram of the wiring harness connection principle of the two-seat rear cabin throttle lever assembly;

[0052] Fig.15 It is a schematic diagram of the principle of a single-seat and double-seat compatible switching line in a specific embodiment of the present invention;

[0053] Fig.16 It is a schematic diagram of the structural principle of the test equipment panel in a specific embodiment of the present invention;

[0054] Fig.17 It is a schematic diagram of the appearance, structure and principle of the testing device in a specific embodiment of the present invention; Description of the drawings:

[0056] 1. Avionics main mode switch indication assembly; 2. Electronic warfare switch indication assembly; 3. Speed ​​brake control switch indication assembly; 4. Transmit / receive control switch indication assembly; 5. Target calibration control switch indication assembly; 6. Missile position marker control switch indication assembly; 7. Radar antenna pitch control switch indication assembly; 8. Front wheel turn control rate selection switch indication assembly; 9. Power supply voltage display screen; 10. Main switch; 11. External power socket; 12. Power selection switch; 100. Box; 101. Control panel; 102. Front cabin 118XSP socket; 103. Front cabin 119XSP socket; 104. Rear cabin 450XSP socket; 105. Rear cabin 453XSP socket; 106. Handle. DETAILED DESCRIPTION

[0057] The present invention is further described below in conjunction with the accompanying drawings and specific preferred embodiments, but the protection scope of the present invention is not limited thereby.

[0058] In the description of the present invention, it should be understood that the terms "side", "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0059] In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "multiple" means two or more, unless otherwise clearly and specifically defined.

[0060] Example 1

[0061] The throttle lever assembly is equipped with: T1 avionics main mode switch, T2 electronic warfare switch, T3 speed brake control switch, T4 transmit / receive control switch (communication control switch), T5 target calibration control switch, T6 missile position marker control switch, T7 radar antenna pitch control switch and T8 front wheel turn control rate selection switch. The wiring harness plugs of the throttle lever assembly include 118XPS plug and 119XPS plug. Figure 1 As shown, the throttle lever assembly comes with two wiring harnesses and plugs 118XPS and 119XPS, which are connected to the cable plugs 118XSP and 119XSP on the aircraft respectively, and by operating a total of 8 switches T1 to T8 on the throttle lever assembly, multiple systems on the aircraft are controlled and corresponding functions are realized. Figure 2 The figure shows the schematic diagram of the throttle lever assembly wiring harness connection. After the existing throttle lever assembly is manufactured or repaired, it is inspected and tested by connecting each wiring harness one by one.

[0062] like Figure 3 , Figure 4 , Fig.16 and Fig.17As shown, the electrical control system test equipment of the aircraft throttle lever assembly of the present invention comprises a box 100, a master control circuit is arranged in the box 100, and a front compartment 118XSP socket 102 and a front compartment 119XSP socket 103 are arranged on the side of the box 100. The master control circuit is connected to the 118XPS plug and the 119XPS plug of the throttle lever assembly through the front compartment 118XSP socket 102 and the front compartment 119XSP socket 103. The master control circuit comprises a plurality of parallel test sub-circuits and corresponding indication components, the test sub-circuits are used to detect the state of the throttle lever assembly, and the indication components are used to display the state of the throttle lever assembly in real time; that is, the test sub-circuits and the indication components are connected in a one-to-one correspondence.

[0063] Specifically, the test subcircuit includes: 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 pitch control switch test circuit and front wheel turn 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 calibration control switch indication component 5, missile position marker control switch indication component 6, radar antenna pitch control switch indication component 7 and front wheel turn control rate selection switch indication component 8.

[0065] After the throttle lever assembly is manufactured or repaired, directly connect the throttle lever harness plugs 118XPS and 119XPS, and judge whether each switch and harness is normal by toggling the 8 switches T1 to T8 on the throttle lever assembly and directly observing the display on the throttle lever electrical control system test equipment.

[0066] like Fig.16 and Fig.17 As shown, a handle 106 is provided on the side of the box 100 to facilitate the carrying of the device. All indicator components are arranged on a control panel 101 on the top of the box 100. And the control panel 101 is also provided with 9, a main switch 10, an external power socket 11 and a power selection switch 12.

[0067] like Figure 4 As shown, the 118XPS plug is provided with output pins A, B, E, F, G, J, L and M, and the front compartment 118XSP socket 102 is provided with input pins A, B, E, F, G, J, L and M. When the 118XPS plug is connected with the front compartment 118XSP socket 102, the T3 speed brake control switch is connected with the speed brake control switch test circuit, and the T4 transmission / reception control switch is connected with the transmission / reception control switch test circuit.

[0068] In this embodiment, the T3 speed brake control switch is connected to the input pin A and the output pin B in the front cabin 118XSP socket 102 through the 118XPS plug, and the T3 speed brake control switch is divided into on and off positions. When the T3 speed brake control switch is pulled backward along the aircraft heading, the T3 speed brake control switch is turned on, and when it is released, the switch is turned off. The speed brake control switch indicator component 3 uses a "green" indicator light to indicate the switch state. The green light is on when it is turned on, and the green light is off when it is released.

[0069] Specifically, Figure 7 As shown in the figure, when the T3 speed brake control switch is pulled backward along the aircraft heading, the "C" pin and the "NO" pin of the switch are connected. When the T3 speed brake control switch is released, the "C" pin and the "NO" pin of the switch are disconnected. Figure 7 As shown, the device part uses a "green" LED light to indicate the switch status, which is driven by a 9VDC voltage. When the T3 speed brake control switch is pulled back, the green light is on, and when it is released, the green light goes out.

[0070] In the present embodiment, the T4 transmitting / receiving control switch is connected to the input pins E, F, G and J in the front cabin 118XSP socket 102 through the 118XPS plug, and the T4 transmitting / receiving control switch is divided into three gears: front, middle and back. When the T4 transmitting / receiving control switch is pushed forward along the aircraft heading, it is the front gear, when the T4 transmitting / receiving control switch is placed in the middle position, it is the middle gear, and when the T4 transmitting / receiving control switch is pulled back, it is the back gear. The transmitting / receiving control switch indicating assembly 4 uses "yellow", "red" and "green" tricolor lights to indicate the switch position respectively, when the T4 transmitting / receiving control switch is pushed forward, the yellow light is on, when the T4 transmitting / receiving control switch is placed in the middle position, the red light is on, and when the T4 transmitting / receiving control switch is pulled back, the green light is on.

[0071] Specifically, Figure 8 As shown, when the T4 transmit / receive control switch is pushed forward along the aircraft heading, the switch's "5" pin and "2" pin are connected, the "5" pin and "4" pin are disconnected, and the "5" pin and "3" pin are disconnected. When the T4 transmit / receive control switch is placed in the middle position, the switch's "5" pin and "2" pin are disconnected, the "5" pin and "4" pin are connected, and the "5" pin and "3" pin are disconnected. When the T4 transmit / receive control switch is pulled backward, the switch's "5" pin and "2" pin are disconnected, the "5" pin and "4" pin are disconnected, and the "5" pin and "3" pin are connected. In this way, the Figure 8 As shown, the device part uses "yellow", "red" and "green" three-color LED lights to indicate the switch position, which is driven by 9VDC voltage. When the T4 transmit / receive control switch is pushed forward, the yellow light is on, when it is placed in the middle position, the red light is on, and when it is pulled back, the green light is on.

[0072] like Figure 4As shown, 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 front cabin 119XSP socket 103 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 with the front cabin 119XSP socket 103, the T1 avionics main mode switch is connected with the avionics main mode switch test circuit, the T2 electronic warfare switch is connected with the electronic warfare switch test circuit, the T5 target calibration control switch is connected with the target calibration control switch test circuit, the T6 missile position marker control switch is connected with the target calibration control switch test circuit, and the T7 radar antenna pitch control switch is connected with the radar antenna pitch 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 in the front cabin 119XSP socket 103 through the 119XPS plug, and the T1 avionics main mode switch is divided into three gears: front, middle and rear. When the T1 avionics main mode switch is pushed forward along the aircraft heading, it is the front gear, when the T1 avionics main mode switch is placed in the middle position, it is the middle gear, and when the T1 avionics main mode switch is pulled back, it is the rear gear. The avionics main mode switch indication component 1 uses "yellow", "red" and "green" three-color lights 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 placed 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.

[0074] Specifically, Figure 5 As shown, when the T1 avionics main mode switch is pushed forward along the aircraft heading, the switch's "5" pin and "1" pin are connected, the "5" pin and "3" pin are disconnected, and the "5" pin and "6" pin are disconnected. When the T1 avionics main mode switch is placed in the middle position, the switch's "5" pin and "1" pin are disconnected, the "5" pin and "3" pin are connected, and the "5" pin and "6" pin are disconnected. When the T1 avionics main mode switch is pulled backward, the switch's "5" pin and "1" pin are disconnected, the "5" pin and "3" pin are disconnected, and the "5" pin and "6" pin are connected. In this way, the switch can be pressed Figure 5 As shown, the equipment part uses "yellow", "red" and "green" three-color LED lights to indicate the switch position, which is driven by 9VDC voltage. When the T1 avionics main mode switch is pushed forward, the yellow light is on, when it is placed in the middle position, the red light is on, and when it is pulled back, the green light is on.

[0075] In this embodiment, the T2 electronic warfare switch is connected to the input pins P, R, S, T and U in the front cabin 119XSP socket 103 through the 119XPS plug, and the T2 electronic warfare switch is divided into three gears: front, middle and rear. When the T2 electronic warfare switch is pushed forward along the aircraft heading, it is the front gear, when the T2 electronic warfare switch is placed in the middle position, it is the middle gear, and when the T2 electronic warfare switch is pulled back, it is the rear gear. The electronic warfare switch indication component 2 uses "yellow", "red" and "green" three-color lights to indicate the switch position respectively. When the T2 electronic warfare switch is pushed forward, the yellow light is on, when the T2 electronic warfare switch is placed in the middle position, the red light is on, and when the T2 electronic warfare switch is pulled back, the green light is on.

[0076] Specifically, Figure 6 As shown, when the T2 electronic warfare switch is pushed forward along the aircraft's heading, the switch's "5" pin and "2" pin are connected, "5" pin and "4" pin are disconnected, and "5" pin and "3" pin are disconnected. When the T2 electronic warfare switch is placed in the middle position, the switch's "5" pin and "2" pin are disconnected, "5" pin and "4" pin are connected, and "5" pin and "3" are disconnected. When the T2 electronic warfare switch is pulled backward, the switch's "5" pin and "2" pin are disconnected, "5" pin and "4" pin are disconnected, and "5" pin and "3" are connected. In this way, the switch can be pressed Figure 6 As shown, the device uses three-color LED lights, "yellow", "red" and "green", to indicate the switch position, which is driven by a 9VDC voltage. When the T2 electronic warfare switch is pushed forward, the yellow light is on, when it is placed in the middle position, the red light is on, and when it is pulled back, the green light is on.

[0077] In this embodiment, the T5 target calibration control switch is connected to the input pins A, B, C, D, F, G, H and N in the front compartment 119XSP socket 103 through the 119XPS plug. The T5 target calibration control switch is composed of a force sensitive sensor and an on-off switch. The target calibration control switch indicator component 5 uses a dual-channel voltmeter to display the detection V X and V Y Voltage, with "red" and "green" two-color lights to display the state of the T5 target calibration control switch along the center axis of the switch. When the T5 target calibration control switch is turned up and down, the X-axis voltage V X Since the U / 2 value changes, when the T5 target calibration control switch is turned upward, V X When you pull it down, V X When the T5 target calibration control switch is turned in the forward and backward direction, the Y-axis voltage V Y Since the U / 2 value changes, when the T5 target calibration control switch is moved forward, V Y When you pull it back, V Y When the T5 target calibration control switch is not pressed down along the center axis, the red light is on and the green light is off; when the T5 target calibration control switch is pressed down along the center axis, the green light is on and the red light is off.

[0078] Specifically, Fig. 9 As shown in the figure, when 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, and the value is U / 2. The voltage between "gray" and "black" is the Y-axis voltage, and the value is U / 2. When the T5 target calibration control switch is moved up and down, the X-axis voltage V X Changes from U / 2 value, when V is pulled upward X When you pull it down, V X When the T5 target calibration control switch is turned forward and backward, the Y-axis voltage V Y Changes from U / 2 value, when V is pulled forward Y When you pull it back, V Y When the T5 target calibration control switch is not pressed down along the center axis, "pin 1" and "pin 2" are connected, and "pin 3" and "pin 4" are disconnected. When the T5 target calibration control switch is pressed down along the center axis, "pin 1" and "pin 2" are disconnected, and "pin 3" and "pin 4" are connected. Fig. 9 As shown, it is driven by 9VDC voltage, and the device is partially detected by a dual-channel voltmeter. X and V Y Voltage, through the "red" and "green" LED lights, detect the state of the T5 target calibration control switch along the center axis of the switch. When the T5 target calibration control switch is turned up and down, the X-axis voltage V X Changes from U / 2 value, when V is pulled upward X When you pull it down, V X When the T5 target calibration control switch is turned in the forward and backward direction, the Y-axis voltage V Y Changes from U / 2 value, when V is pulled forward Y When you pull it back, V Y When the T5 target calibration control switch is not pressed down along the center axis, the red light is on and the green light is off. When the T5 target calibration control switch is pressed down along the center axis, the green light is on and the red light is off.

[0079] In this embodiment, the T6 missile position marker control switch is connected to the input pins H and M in the front compartment 119XSP socket 103 through the 119XPS plug, and the T6 missile position marker control switch is divided into two states: on and off. When the T6 missile position marker control switch is pressed, the switch is turned on, and when the T6 missile position marker control switch is released, the switch is turned off. The missile position marker control switch indicator component 6 uses a "green" color light to indicate the switch state. After the T6 missile position marker control switch is pressed, the green light is on, and when the T6 missile position marker control switch is released, the green light is off.

[0080] Specifically, Fig.10As shown in the figure, when the T6 missile position marker control switch is pressed, the "1(4)" pin and the "3" pin of the switch are connected. When the T6 missile position marker control switch is released, the "1(4)" pin and the "3" pin of the switch are disconnected. Fig. 9 As shown, the device part uses a "green" LED light to indicate the switch state, which is driven by a 9VDC voltage. When the T6 missile position marker control switch is pressed, the green light is on, and the green light is off when it is released.

[0081] In this embodiment, the T7 radar antenna pitch control switch is connected to the input pins E, F and G in the front compartment 119XSP socket 103 through the 119XPS plug. The T7 radar antenna pitch control switch is a sliding rheostat switch. The radar antenna pitch control switch indicator component 7 uses a voltmeter to display the detection V Y Voltage, when the T7 radar antenna pitch control switch is pushed forward along the heading, the voltage is expressed in V Y When the T7 radar antenna pitch control switch is moved backward, the voltage is displayed as V. Y Get bigger.

[0082] Specifically, Fig.11 As shown in the figure, a voltage U is applied between the two pins "2" and "1" of the pitch control switch of the T7 radar antenna, and the output voltage V between "3" and "1" Y , the value is U / 2. When the T7 radar antenna pitch control switch is turned along the aircraft heading, the voltage V Y Changes from the value of U / 2, when pushing forward along the heading V Y When you pull it back, V Y Become larger. Fig.11 As shown, the test equipment uses a 9VDC voltage to drive the device, and the voltage meter detects V Y Voltage. After power on, the voltage reading is U / 2 = 4.5 VDC. When the T7 radar antenna pitch control switch is pushed forward along the heading, the voltage reading is V Y When it is pulled back, the voltage is displayed in V. Y Get bigger.

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

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

[0085] Specifically, Fig.12 As shown, when the T8 front wheel turning control rate selection switch is pressed, the "1(4)" pin and the "3" pin of the switch are connected, and the "4(1)" pin and the "2" pin of the switch are disconnected. When the T8 front wheel turning control rate selection switch is released, the "1(4)" pin and the "3" pin of the switch are disconnected, and the "4(1)" pin and the "2" pin of the switch are connected. The device part uses "red" and "green" two-color LED lights to indicate the switch status, which are driven by a 9VDC voltage. When the T8 front wheel turning control rate selection switch is pressed, the green light is on and the red light is off. When the T8 front wheel turning control rate selection switch is released, the green light is off and the red light is on.

[0086] In order to consider the compatibility of the equipment, the throttle levers of the front and rear cabins of both single-seat and two-seat aircraft can be tested. After studying the principle of the throttle lever of the rear cabin of the two-seat aircraft, it is found that the throttle lever of the rear cabin of the two-seat aircraft has the same function as the throttle lever of the single-seat aircraft and the throttle lever of the front cabin of the two-seat aircraft. The difference is that the connection plugs on the aircraft are different, 450XPS and 453XPS. Fig.13 This is the schematic diagram of the throttle lever wiring harness in the front cabin of a two-seater aircraft, such as Fig.14 This is the schematic diagram of the throttle lever wiring harness for the rear cabin of a two-seater aircraft.

[0087] In this embodiment, two adapter boards are further provided in the box 100, and a rear cabin 450XSP socket 104 and a rear cabin 453XSP socket 105 are further provided on the side of the box 100. The rear cabin 450XSP socket 104 and the front cabin 118XSP socket 102 are connected in parallel on one of the adapter boards, and the rear cabin 453XSP socket 105 and the front cabin 119XSP socket 103 are connected in parallel on another adapter board. The adapter board is connected to the master control circuit to implement the test of the single-seat throttle lever assembly or the double-seat throttle lever assembly. In order to ensure that the front and rear cabin throttle levers of single-seat aircraft and double-seat aircraft can be tested, an adapter circuit is involved, which is compatible with the front and rear cabin throttle levers of single-seat aircraft and double-seat aircraft. The adapter circuit is as follows: Fig.15 shown.

[0088] like Fig.17As shown, the equipment is provided with a front cabin 118XSP socket 102 and a front cabin 119XSP socket 103, which match the single-seat throttle lever or the double-seat front cabin throttle lever 118XPS, 119XSP plugs, and a rear cabin 450XSP socket 104 and a rear cabin 453XSP socket 105 are provided to match the double-seat rear cabin throttle lever 450XPS, 453XSP plugs, so that the equipment is compatible with the single-seat aircraft and the front and rear cabin throttle levers of the double-seat aircraft can be tested.

[0089] Example 2

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

[0091] Step S1, connect the 118XPS plug and the 119XPS plug of the throttle lever of the single-seat aircraft or the front cabin throttle lever of the double-seat aircraft to the front cabin 118XSP socket 102 and the front cabin 119XSP socket 103 of the equipment respectively, as shown in FIG. Fig.16 As shown, if the built-in power supply is used, the power selection switch 12 is set to "internal power supply" and the internal 9VDC battery of the device is used for power supply. "External power supply" can also be selected. When "external power supply" is selected, the "220VAC to 9VDC" power adapter must be connected to the external power socket 11 on the control panel 101 and connected to 220VAC mains.

[0092] Step S2, turn on the main switch 10 on the control panel 101 to the "on" position, and the power supply voltage display screen 9 displays "9.00V".

[0093] Step S3, T1 avionics main mode switch test: When the T1 avionics main mode switch is pushed forward along the aircraft heading, the yellow light in the avionics main mode switch indication assembly 1 is on; when the T1 avionics main mode switch is placed in the middle position, the red light in the avionics main mode switch indication assembly 1 is on; when the T1 avionics main mode switch is pulled backward, the green light in the avionics main mode switch indication assembly 1 is on.

[0094] Step S4, T2 electronic warfare switch test: When the T2 electronic warfare switch is pushed forward along the aircraft heading, the yellow light of the electronic warfare switch indication component 2 is on; when the T2 electronic warfare switch is placed in the middle position, the red light of the electronic warfare switch indication component 2 is on; when the T2 electronic warfare switch is pulled backward, the green light of the electronic warfare switch indication component 2 is on.

[0095] Step S5, T3 speed brake control switch test: for a single-seat aircraft, when the T3 speed brake control switch is pulled backward along the aircraft heading, the green light of the speed brake control switch indicator component 3 is on; when the T3 speed brake control switch is released, the green light of the speed brake control switch indicator component 3 is off; for the front cabin of a two-seat aircraft, when the T3 speed brake control switch is pulled backward along the aircraft heading, the green light of the speed brake control switch indicator component 3 is on and the red light is off; when the T3 speed brake control switch is pushed forward, the green light of the speed brake control switch indicator component 3 is off and the red light is on.

[0096] 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 on; 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 on; when the T4 transmit / receive control switch is pulled backward, the green light of the transmit / receive control switch indicator component 4 is on.

[0097] Step S7, T5 target calibration control switch test: when the device switch is turned on, the voltage V X and V Y Both display U / 2=4.5V; when the T5 target calibration control switch is turned up and down, the X-axis voltage V X From 4.5V value changes, when the upward push, V X It gradually increases from 4.5V. When it is pulled down, V X It gradually decreases from 4.5V; when the T5 target calibration control switch is turned in the forward and backward direction, the Y-axis voltage V Y From 4.5V value changes, when moving forward, V Y It gradually increases from 4.5V. When it is pulled back, V Y It gradually decreases from 4.5V; when the T5 target calibration control switch is not pressed downward along the center axis, the red light of the target calibration control switch indicating component 5 is on and the green light is off. When the T5 target calibration control switch is pressed downward along the center axis, the green light of the target calibration control switch indicating component 5 is on and the red light is off.

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

[0099] Step S9, T7 radar antenna pitch control switch test: When the device switch is turned on, the voltage V X Display U / 2 = 4.5V; when the T7 radar antenna pitch control switch is pushed forward along the heading, the voltage of the radar antenna pitch control switch indicating component 7 is displayed as V YIt gradually decreases from 4.5V. When the T7 radar antenna pitch control switch is turned back, the voltage of the radar antenna pitch control switch indicating component 7 indicates the number V. Y Gradually increase from 4.5V.

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

[0101] When the test equipment of the present invention is used for testing, only one operator or inspector is needed to complete the test, and only the status light and the voltmeter on the equipment panel need to be observed, which has strong visualization, is not prone to human errors, and greatly saves test time.

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

[0103] Connect the 450XPS and 453XPS plugs of the two-seater rear cabin throttle lever to the 450XSP and 453XSP of the equipment respectively. The test method is the same as the test of the single-seat throttle lever / two-seat front cabin throttle lever. The test of the T3 speed brake control switch is the same as the two-seat front cabin T3 speed brake control switch. The two-seat rear cabin throttle lever does not have the T1 avionics main mode switch.

[0104] The above is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments. All technical solutions under the concept of the present invention belong to the protection scope of the present invention. It should be pointed out that for ordinary technicians in this technical field, some improvements and modifications without departing from the principle of the present invention should also be regarded as the protection scope of the present invention.

Claims

1. An aircraft throttle lever assembly electrical control system test equipment, wherein the throttle lever assembly is provided with: T1 avionics main mode switch, T2 electronic warfare switch, T3 speed brake control switch, T4 transmission / reception control switch, T5 target calibration control switch, T6 missile position marker control switch, T7 radar antenna pitch control switch and T8 front wheel turning control rate selection switch, and the wiring harness plug of the throttle lever assembly includes 118XPS plug and 119XPS plug; characterized in that, The test device comprises a box (100), wherein a master control circuit is arranged in the box (100), and a front compartment 118XSP socket (102) and a front compartment 119XSP socket (103) are arranged on the side of the box (100), wherein the master control circuit is connected to a 118XPS plug and a 119XPS plug of a throttle lever assembly via the front compartment 118XSP socket (102) and the front compartment 119XSP socket (103); the master control circuit comprises a plurality of parallel test sub-circuits and corresponding indication components, wherein the test sub-circuits are used to detect the state of the throttle lever assembly, and the indication component is used to display the state of the throttle lever assembly in real time; The test subcircuit includes: an avionics main mode switch test circuit, an electronic warfare switch test circuit, a speed brake control switch test circuit, a transmit / receive control switch test circuit, a target calibration control switch test circuit, a missile position marker control switch test circuit, a radar antenna pitch control switch test circuit and a front wheel turn control rate selection switch test circuit; The indication assembly comprises: an avionics main mode switch indication assembly (1), an electronic warfare switch indication assembly (2), a speed brake control switch indication assembly (3), a transmission / reception control switch indication assembly (4), a target calibration control switch indication assembly (5), a missile position marker control switch indication assembly (6), a radar antenna pitch control switch indication assembly (7) and a front wheel turning control rate selection switch indication assembly (8).

2. The aircraft throttle lever assembly electrical control system test equipment according to claim 1, characterized in that: Two adapter plates are also provided in the box body (100), and a rear cabin 450XSP socket (104) and a rear cabin 453XSP socket (105) are also provided on the side of the box body (100); the rear cabin 450XSP socket (104) and the front cabin 118XSP socket (102) are connected in parallel on one of the adapter plates, and the rear cabin 453XSP socket (105) and the front cabin 119XSP socket (103) are connected in parallel on the other adapter plate, and the adapter plate is connected to the master control circuit to realize the test of a single-seat throttle lever assembly or a double-seat throttle lever assembly.

3. The aircraft throttle lever assembly electrical control system test equipment according to claim 2, characterized in that: The 118XPS plug is provided with output pins A, B, E, F, G, J, L and M, and the front cabin 118XSP socket (102) 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 (102), the T3 speed brake control switch is connected to the speed brake control switch test circuit, and the T4 transmission / reception control switch is connected to the transmission / reception control switch test circuit.

4. The aircraft throttle lever assembly electrical control system test equipment according to claim 3, characterized in that: The T3 speed brake control switch is connected to the input pin A and the output pin B in the 118XSP socket (102) in the front cabin via the 118XPS plug. The T3 speed brake control switch is divided into on and off positions. When the T3 speed brake control switch is moved backward along the aircraft heading, the T3 speed brake control switch is turned on, and when it is released, the switch is turned off. The speed brake control switch indicator component (3) indicates the switch state with a "green" indicator light. When it is turned on, the green light is on, and when it is released, the green light is off. The T4 transmitting / receiving control switch is connected to the input pins E, F, G and J in the front cabin 118XSP socket (102) through a 118XPS plug. The T4 transmitting / receiving control switch is divided into three gears: front, middle and rear. When the T4 transmitting / receiving control switch is pushed forward along the aircraft heading, it is in the front gear. When the T4 transmitting / receiving control switch is placed in the middle position, it is in the middle gear. When the T4 transmitting / receiving control switch is pulled backward, it is in the rear gear. The transmitting / receiving control switch indicating component (4) uses "yellow", "red" and "green" three-color lights to indicate the switch position. When the T4 transmitting / receiving control switch is pushed forward, the yellow light is on. When the T4 transmitting / receiving control switch is placed in the middle position, the red light is on. When the T4 transmitting / receiving control switch is pulled backward, the green light is on.

5. The aircraft throttle lever assembly electrical control system test equipment according to claim 3, characterized in that: 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 front cabin 119XSP socket (103) 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 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 pitch control switch is connected to the radar antenna pitch control switch test circuit.

6. The aircraft throttle lever assembly electrical control system test equipment according to claim 5, characterized in that: The T1 avionics main mode switch is connected to the input pins H, J, K and L in the front cabin 119XSP socket (103) through the 119XPS plug. The T1 avionics main mode switch is divided into three gears: front, middle and rear. When the T1 avionics main mode switch is pushed forward along the aircraft heading, it is the front gear. When the T1 avionics main mode switch is placed in the middle position, it is the middle gear. When the T1 avionics main mode switch is pulled back, it is the rear gear. The avionics main mode switch indication component (1) uses "yellow", "red" and "green" three-color lights 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 placed 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 in the front cabin 119XSP socket (103) through the 119XPS plug. The T2 electronic warfare switch is divided into three gears: front, middle and rear. When the T2 electronic warfare switch is pushed forward along the aircraft heading, it is the front gear. When the T2 electronic warfare switch is placed in the middle position, it is the middle gear. When the T2 electronic warfare switch is pulled back, it is the rear gear. The electronic warfare switch indication component (2) uses "yellow", "red" and "green" three-color 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 placed 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 aircraft throttle lever assembly electrical control system test equipment 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 in the front compartment 119XSP socket (103) through the 119XPS plug. The T5 target calibration control switch is composed of a force sensitive sensor and an on-off switch. The target calibration control switch indicator component (5) uses a dual-channel voltmeter to display the detection V X and V Y Voltage, with "red" and "green" two-color lights to display the state of the T5 target calibration control switch along the center axis of the switch; when the T5 target calibration control switch is turned up and down, the X-axis voltage V X Since the U / 2 value changes, when the T5 target calibration control switch is turned upward, V X When you pull it down, V X When the T5 target calibration control switch is turned in the forward and backward direction, the Y-axis voltage V Y Since the U / 2 value changes, when the T5 target calibration control switch is moved forward, V Y When you pull it back, V Y becomes smaller; when the T5 target calibration control switch is not pressed down along the center axis, the red light is on and the green light is off; when the T5 target calibration control switch is pressed down along the center axis, the green light is on and the red light is off.

8. The aircraft throttle lever assembly electrical control system test equipment according to claim 5, characterized in that: The T6 missile position marker control switch is connected to the input pins H and M in the front compartment 119XSP socket (103) through the 119XPS plug. The T6 missile position marker control switch is divided into two states: on and off. When the T6 missile position marker control switch is pressed, the switch is on. When the T6 missile position marker control switch is released, the switch is off. The missile position marker control switch indicator component (6) indicates the switch state with a "green" light. When the T6 missile position marker control switch is pressed, the green light is on. When the T6 missile position marker control switch is released, the green light is off.

9. The aircraft throttle lever assembly electrical control system test equipment according to claim 5, characterized in that: The T7 radar antenna pitch control switch is connected to the input pins E, F and G in the front cabin 119XSP socket (103) through the 119XPS plug. The T7 radar antenna pitch control switch is a sliding rheostat switch. The radar antenna pitch control switch indicator component (7) uses a voltmeter to display the detection V Y Voltage, when the T7 radar antenna pitch control switch is pushed forward along the heading, the voltage is expressed in V Y When the T7 radar antenna pitch control switch is moved backward, the voltage is displayed as V. Y Get bigger.

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

11. A test method for the aircraft throttle lever assembly electrical control system test equipment according to any one of claims 1 to 10, characterized in that: The following steps are involved: Step S1, connecting the 118XPS plug and the 119XPS plug of the throttle lever to the front compartment 118XSP socket (102) and the front compartment 119XSP socket (103) of the test equipment respectively; Step S2, turning on the main switch (10) on the box (100) to the "on" position, and the power supply voltage display screen (9) displays "UV"; Step S3, T1 avionics main mode switch test: When the T1 avionics main mode switch is pushed forward along the aircraft heading, the yellow light in the avionics main mode switch indicator assembly (1) is on; when the T1 avionics main mode switch is placed in the middle position, the red light in the avionics main mode switch indicator assembly (1) is on; when the T1 avionics main mode switch is pulled backward, the green light in the avionics main mode switch indicator assembly (1) is on; Step S4, T2 electronic warfare switch test: When the T2 electronic warfare switch is pushed forward along the aircraft heading, the yellow light of the electronic warfare switch indicator component (2) is on; when the T2 electronic warfare switch is placed in the middle position, the red light of the electronic warfare switch indicator component (2) is on; when the T2 electronic warfare switch is pulled backward, the green light of the electronic warfare switch indicator component (2) is on; Step S5, T3 speed brake control switch test: for a single-seat aircraft, the T3 speed brake control switch is pulled backward along the aircraft heading, and the green light of the speed brake control switch indicator assembly (3) is on; when the T3 speed brake control switch is released, the green light of the speed brake control switch indicator assembly (3) is off; for the front cabin of a two-seat aircraft, when the T3 speed brake control switch is pulled backward along the aircraft heading, the green light of the speed brake control switch indicator assembly (3) is on, and the red light is off; when the T3 speed brake control switch is pushed forward, the green light of the speed brake control switch indicator assembly (3) is off, and the red light is on; 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 assembly (4) is on; when the T4 transmit / receive control switch is in the middle position, the red light of the transmit / receive control switch indicator assembly (4) is on; when the T4 transmit / receive control switch is pulled backward, the green light of the transmit / receive control switch indicator assembly (4) is on; Step S7, T5 target calibration control switch test: when the device switch is turned on, the voltage V X and V Y Both display (U / 2)V; when the T5 target calibration control switch is turned up and down, the X-axis voltage V X The value of (U / 2)V changes. When you turn it upward, V X It gradually increases from (U / 2)V. When it is pulled downward, V X It gradually decreases from (U / 2)V; when the T5 target calibration control switch is turned in the forward and backward direction, the Y-axis voltage V Y The value of (U / 2)V changes. When you push it forward, V Y It gradually increases from (U / 2)V. When it is pulled back, V Y The value gradually decreases from (U / 2)V; when the target calibration control switch T5 is not pressed downward along the central axis, the red light of the target calibration control switch indicating component (5) is on and the green light is off; when the target calibration control switch T5 is pressed downward along the central axis, the green light of the target calibration control switch indicating component (5) is on and the red light is off; Step S8, T6 missile position marker control switch test: After the T6 missile position marker control switch is pressed, the green light of the missile position marker control switch indicator component (6) turns on, and when it is released, the green light turns off; Step S9, T7 radar antenna pitch control switch test: When the device switch is turned on, the voltage V X Display (U / 2)V; when the T7 radar antenna pitch control switch is pushed forward along the heading, the voltage of the radar antenna pitch control switch indicating component (7) is displayed as V Y The voltage of the radar antenna pitch control switch indicator component (7) is indicated by (U / 2)V, which gradually decreases. When the T7 radar antenna pitch control switch is moved backward, the voltage of the radar antenna pitch control switch indicator component (7) is indicated by V. Y It gradually increases from (U / 2)V; Step S10, T8 front wheel turning control rate selection switch test: after the T8 front wheel turning control rate selection switch is pressed, the green light of the front wheel turning control rate selection switch indicator component (8) turns on and the red light turns off; when the T8 front wheel turning control rate selection switch is released, the green light of the front wheel turning control rate selection switch indicator component (8) turns off and the red light turns on.

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