Airplane waveguide switch detection device

Abstract

The utility model discloses an airplane waveguide switch detection device which comprises a power supply module and a detection mechanism. The cathode of the power supply module is used for being electrically connected with a cathode connector of an airplane waveguide switch. The detection mechanism comprises a left-right selection switch, the input end of the left-right selection switch is electrically connected with the positive electrode of the power module, the left output end of the left-right selection switch is used for being electrically connected with a left connector of an airplane waveguide switch, and the right output end of the left-right selection switch is used for being electrically connected with a right connector of the airplane waveguide switch. The beneficial effects of the utility model are that during assembly in a general assembly workshop, power is supplied through the power supply module, and the left joint or the right joint of the airplane waveguide switch is selectively connected through the left and right selection switches, so that the airplane waveguide switch can be directly driven to turn left or right, and whether the waveguide switch can turn left or right normally can be judged; the problem that the dismounting workload is increased due to the fact that the airplane waveguide switch is detected after the airplane is well assembled is avoided.

Description

Technical Field

[0001] The utility model relates to the technical field of waveguide switches, in particular to an aircraft waveguide switch detection device. Background Art

[0002] A certain type of aircraft is equipped with 3 waveguide switches, each of which is connected to the waveguide channel by 12 screws. During the assembly stage, there is no torque requirement. After the assembly is completed, when the reactance system is high-voltage to measure power radiation, faults occur frequently. After troubleshooting, it is found that many times the torque of the screws connecting the waveguide switch and the waveguide is too large, causing the waveguide switch to fail to rotate normally. Since there is no torque requirement, excessive installation torque will cause the waveguide channel to fail to rotate normally, and too small torque will cause the screws to fall off due to vibration during the flight of the aircraft, causing risks. At present, only when the aircraft is in good condition and through power-on debugging can it be detected whether the waveguide switch is installed well. Since the installation positions of the three waveguide switches are different, if the waveguide switch detects a problem, the waveguide switch needs to be disassembled and reinstalled. It is very difficult to disassemble and reinstall the waveguide switch when the aircraft is in good condition, which is time-consuming and labor-intensive. In addition, applying high voltage multiple times or for a long time will cause the transmitter to overheat, and there is a risk of damaging the machine parts. At the same time, when high voltage is applied to the reactance system, the radiation power can reach 100W. During radiation testing or troubleshooting, personnel are in danger of being radiated, which endangers the health of operators. Utility Model Content

[0003] In view of this, it is necessary to provide an aircraft waveguide switch detection device to solve the technical problems that electrical debugging and detection of waveguide switches on aircraft will increase the workload of disassembly and assembly, pose a risk of damaging parts, and put personnel at risk of radiation.

[0004] In order to achieve the above-mentioned purpose, the utility model provides an aircraft waveguide switch detection device, including a power module and a detection mechanism;

[0005] The negative electrode of the power module is used to be electrically connected to the negative electrode connector of the aircraft waveguide switch;

[0006] The detection mechanism includes a left-right selection switch, the input end of the left-right selection switch is electrically connected to the positive pole of the power module, the left output end of the left-right selection switch is used to be electrically connected to the left connector of the aircraft waveguide switch, and the right output end of the left-right selection switch is used to be electrically connected to the right connector of the aircraft waveguide switch.

[0007] In some embodiments, the detection mechanism also includes a left indicator light and a right indicator light, wherein two ends of the left indicator light are respectively electrically connected to the left output end of the left or right selection switch and the negative pole of the power module, and two ends of the right indicator light are respectively electrically connected to the right output end of the left or right selection switch and the negative pole of the power module.

[0008] In some embodiments, the detection mechanism also includes a left cable, a right cable and a negative cable, one end of the left cable is electrically connected to the left output end of the left or right selection switch, and the other end of the left cable is connected to a left plug, and the left plug is used to be electrically connected to the left connector of the aircraft waveguide switch; one end of the right cable is electrically connected to the right output end of the left or right selection switch, and the other end of the right cable is connected to a right plug, and the right plug is used to be electrically connected to the right connector of the aircraft waveguide switch; one end of the negative cable is electrically connected to the negative pole of the power module, and the other end of the negative cable is connected to a negative plug, and the negative plug is used to be electrically connected to the negative connector of the aircraft waveguide switch.

[0009] In some embodiments, the detection mechanism also includes a left resistor and a left diode, one end of the left resistor is electrically connected to the left cable, the other end of the left resistor is connected to the positive pole of the left diode, the negative pole of the left diode is electrically connected to one end of the left indicator light, and the other end of the left indicator light is electrically connected to the negative cable.

[0010] In some embodiments, the detection mechanism also includes a right resistor and a right diode, one end of the right resistor is electrically connected to the right cable, the other end of the right resistor is connected to the positive electrode of the right diode, the negative electrode of the right diode is electrically connected to one end of the right indicator light, and the other end of the right indicator light is electrically connected to the negative cable.

[0011] In some embodiments, the detection mechanism also includes a light detection switch, one end of the light detection switch is electrically connected to the input end of the left and right selection switch, and the other end of the light detection switch is electrically connected to the left output end and the right output end of the left and right selection switch.

[0012] In some embodiments, the detection mechanism also includes a voltage selection switch and a first voltmeter, the output end of the voltage selection switch is electrically connected to one end of the first voltmeter, the left input end of the voltage selection switch is electrically connected to the left cable, the right input end of the voltage selection switch is electrically connected to the right cable, and the other end of the first voltmeter is electrically connected to the negative cable.

[0013] In some embodiments, the power supply module includes a transformer, a rectifier and a power supply selection switch, the input end of the transformer is connected to the AC power, the input end of the rectifier is electrically connected to the output end of the transformer, the negative output end of the rectifier is electrically connected to the negative cable, the first input connector of the power supply selection switch is electrically connected to the positive output end of the rectifier, the second input connector of the power supply selection switch is used to be electrically connected to the DC power supply positive connector of the aircraft, and the output connector of the power supply selection switch is electrically connected to the input end of the left and right selection switches.

[0014] In some embodiments, the power supply module also includes a power supply resistor, a power supply diode and a power supply indicator light, one end of the power supply resistor is electrically connected to the output connector of the power supply selection switch, the other end of the power supply resistor is electrically connected to the positive electrode of the power supply diode, the negative electrode of the power supply diode is electrically connected to one end of the power supply indicator light, and the other end of the power supply indicator light is electrically connected to the negative electrode cable.

[0015] In some embodiments, the power module further includes a second voltmeter, one end of the second voltmeter is electrically connected to the output connector of the power supply selection switch, and the other end of the second voltmeter is electrically connected to the negative cable.

[0016] Compared with the prior art, the beneficial effect of the technical solution proposed by the utility model is that during assembly in the general assembly workshop, power is supplied by the power module, and the left connector or the right connector of the aircraft waveguide switch is selected by the left and right selection switches, so that the aircraft waveguide switch can be directly driven to turn left or right, so that it can be judged whether the waveguide switch can turn left and right normally, and then it can be judged whether the tightening torque of the connecting screws of the aircraft waveguide switch meets the rotation requirements, so that the fault can be moved forward, and whether the rotation function of the aircraft waveguide switch is normal can be detected during assembly in the general assembly workshop, avoiding the problem of increased disassembly and assembly workload caused by detecting the aircraft waveguide switch after the aircraft is fully assembled, saving a lot of manpower and material resources, shortening the production cycle, and since no power-on debugging is required, the risk of machine damage and radiation hazards to personnel can be reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the panel structure of an embodiment of the aircraft waveguide switch detection device provided by the utility model;

[0018] Figure 2 yes Figure 1 Circuit diagram of the aircraft waveguide switch detection device;

[0019] In the figure: 1-power module, 11-power supply selection switch, 12-power supply resistor, 13-power supply diode, 14-power supply indicator light, 15-second voltmeter, 2-detection mechanism, 21-left and right selection switches, 22-left indicator light, 23-right indicator light, 24-left cable, 25-right cable, 26-negative cable, 27-left plug, 28-right plug, 29-negative plug, 210-left resistor, 211-left diode, 212-right resistor, 213-right diode, 214-light detection switch, 215-voltage selection switch, 216-first voltmeter. DETAILED DESCRIPTION

[0020] The preferred embodiments of the present invention are described in detail below in conjunction with the accompanying drawings, wherein the accompanying drawings constitute a part of the present application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not used to limit the scope of the present invention.

[0021] Please refer to Figure 1 and Figure 2 , the utility model provides an aircraft waveguide switch detection device, including a power module 1 and a detection mechanism 2;

[0022] The negative electrode of the power module 1 is used to be electrically connected to the negative electrode connector of the aircraft waveguide switch;

[0023] The detection mechanism 2 includes a left and right selection switch 21, a left indicator light 22 and a right indicator light 23. The input end of the left and right selection switch 21 is electrically connected to the positive pole of the power module 1, the left output end of the left and right selection switch 21 is used to be electrically connected to the left connector of the aircraft waveguide switch, and the right output end of the left and right selection switch 21 is used to be electrically connected to the right connector of the aircraft waveguide switch. The two ends of the left indicator light 22 are respectively electrically connected to the left output end of the left and right selection switch 21 and the negative pole of the power module 1, and the two ends of the right indicator light 23 are respectively electrically connected to the right output end of the left and right selection switch 21 and the negative pole of the power module 1.

[0024] It should be understood that the left-right selection switch 21 has an input terminal and three output terminals (left output terminal, right output terminal and neutral terminal). When the knob of the left-right selection switch 21 is rotated to a certain output terminal, the output terminal is electrically connected to the input terminal. Specifically, when the knob of the left-right selection switch 21 is rotated to the left position, the left output terminal is electrically connected to the input terminal, when the knob of the left-right selection switch 21 is rotated to the right position, the right output terminal is electrically connected to the input terminal, and when the knob of the left-right selection switch 21 is rotated to the neutral terminal, the neutral terminal is electrically connected to the input terminal. This switch is a knob-type three-selection switch, and its specific structure is the prior art, and the utility model will not repeat it.

[0025] During assembly in the aircraft assembly workshop, the rotation function of the aircraft waveguide switch is tested. Specifically, the negative pole of the power module 1 is electrically connected to the negative pole connector of the aircraft waveguide switch, the left output end of the left-right selection switch 21 is electrically connected to the left connector of the aircraft waveguide switch, and the right output end of the left-right selection switch 21 is electrically connected to the right connector of the aircraft waveguide switch. Then, the knob of the left-right selection switch 21 is manually turned to the left position. At this time, the power module 1 is electrically connected to the left connector of the aircraft waveguide switch, the aircraft waveguide switch is powered and rotated to the left, and whether the aircraft waveguide switch can turn left normally is observed. After the test is normal, the knob of the left-right selection switch 21 is manually turned to the right position. At this time, the power module 1 is electrically connected to the right connector of the aircraft waveguide switch, the aircraft waveguide switch is powered and rotated to the right, and whether the aircraft waveguide switch can turn right normally is observed. If both tests are normal, it indicates that the aircraft waveguide switch is well installed;

[0026] The utility model can also detect the power supply of the aircraft waveguide switch. The specific method is: manually turn the knob of the left and right selection switch 21 to the neutral end. At this time, the power module 1 is electrically disconnected from the aircraft waveguide switch. Then, the aircraft is powered on, and then the display control, electronic countermeasure and other related systems on the aircraft's avionics starter board are turned on in turn to power on the system. After the reactance system is powered on, the waveguide switch will also be powered on. Professionals control the position of the target simulator device relative to the aircraft. First, the target simulator device is located on the left side of the aircraft. At this time, theoretically, the left connector of the aircraft waveguide switch should be powered on, and observe whether the left indicator light 22 is normally lit. If it is normally lit, it indicates that the left connector of the aircraft waveguide switch is normally powered on. Then the target simulator device is located on the right side of the aircraft. At this time, theoretically, the right connector of the aircraft waveguide switch should be powered on, and observe whether the right indicator light 23 is normally lit. If it is normally lit, it indicates that the right connector of the aircraft waveguide switch is normally powered on.

[0027] During assembly in the final assembly workshop, power is supplied through the power module 1, and the left connector or the right connector of the aircraft waveguide switch is selected through the left and right selection switches 21, so that the aircraft waveguide switch can be directly driven to turn left or right, so that it can be judged whether the waveguide switch can turn left and right normally, and then it can be judged whether the tightening torque of the connecting screws of the aircraft waveguide switch meets the rotation requirement. The utility model can move the fault forward, and can detect whether the rotation function of the aircraft waveguide switch is normal during assembly in the final assembly workshop, avoiding the problem of increased disassembly and assembly workload caused by detecting the aircraft waveguide switch after the aircraft is fully assembled, saving a lot of manpower and material resources, shortening the production cycle, and since there is no need for power-on debugging, the risk of machine damage and the harm of radiation to personnel can be reduced.

[0028] To facilitate the connection of aircraft waveguide switches, please refer to Figure 1 and Figure 2In a preferred embodiment, the detection mechanism 2 further includes a left cable 24, a right cable 25 and a negative cable 26, one end of the left cable 24 is electrically connected to the left output end of the left / right selection switch 21, and the other end of the left cable 24 is connected to a left plug 27, and the left plug 27 is used to be electrically connected to the left connector of the aircraft waveguide switch; one end of the right cable 25 is electrically connected to the right output end of the left / right selection switch 21, and the other end of the right cable 25 is connected to a right plug 28, and the right plug 28 is used to be electrically connected to the right connector of the aircraft waveguide switch; one end of the negative cable 26 is electrically connected to the negative pole of the power module 1, and the other end of the negative cable 26 is connected to a negative plug 29, and the negative plug 29 is used to be electrically connected to the negative connector of the aircraft waveguide switch.

[0029] For the convenience of storage, the device is provided with a cable box, and the left cable 24, the right cable 25 and the negative cable 26 are all stored in the cable box.

[0030] To protect the left indicator light 22, please refer to Figure 1 and Figure 2 In a preferred embodiment, the detection mechanism 2 also includes a left resistor 210 and a left diode 211, one end of the left resistor 210 is electrically connected to the left cable 24, the other end of the left resistor 210 is connected to the positive electrode of the left diode 211, the negative electrode of the left diode 211 is electrically connected to one end of the left indicator light 22, and the other end of the left indicator light 22 is electrically connected to the negative cable 26.

[0031] To protect the right indicator light 23, please refer to Figure 1 and Figure 2 In a preferred embodiment, the detection mechanism 2 also includes a right resistor 212 and a right diode 213, one end of the right resistor 212 is electrically connected to the right cable 25, the other end of the right resistor 212 is connected to the positive electrode of the right diode 213, the negative electrode of the right diode 213 is electrically connected to one end of the right indicator light 23, and the other end of the right indicator light 23 is electrically connected to the negative cable 26.

[0032] In order to detect whether the left indicator light 22 and the right indicator light 23 are damaged, please refer to Figure 1 and Figure 2In a preferred embodiment, the detection mechanism 2 further includes a light detection switch 214, one end of which is electrically connected to the input end of the left / right selection switch 21, and the other end of which is electrically connected to both the left output end and the right output end of the left / right selection switch 21. When detecting whether the left indicator light 22 and the right indicator light 23 are damaged, the light detection switch 214 is closed to observe whether the left indicator light 22 and the right indicator light 23 are both lit, thereby determining whether the left indicator light 22 and the right indicator light 23 are damaged. After confirming that there is no damage, the light detection switch 214 is disconnected, and then other detections are performed.

[0033] In order to check whether the voltage of the left and right connectors of the aircraft waveguide switch is normal, please refer to Figure 1 and Figure 2 In a preferred embodiment, the detection mechanism 2 also includes a voltage selection switch 215 and a first voltmeter 216, the output end of the voltage selection switch 215 is electrically connected to one end of the first voltmeter 216, the left input end of the voltage selection switch 215 is electrically connected to the left cable 24, the right input end of the voltage selection switch 215 is electrically connected to the right cable 25, and the other end of the first voltmeter 216 is electrically connected to the negative cable 26.

[0034] To implement the functions of power module 1, please refer to Figure 1 and Figure 2 In a preferred embodiment, the power supply module 1 includes a transformer, a rectifier and a power supply selection switch 11, the input end of the transformer is connected to the mains, the input end of the rectifier is electrically connected to the output end of the transformer, the negative output end of the rectifier is electrically connected to the negative cable 26, the first input connector of the power supply selection switch 11 is electrically connected to the positive output end of the rectifier, the second input connector of the power supply selection switch 11 is used to be electrically connected to the DC power supply positive connector of the aircraft, and the output connector of the power supply selection switch 11 is electrically connected to the input end of the left and right selection switch 21.

[0035] When in use, the device can select two power supply modes. The first mode is to switch the power supply selection switch 11 to the first input connector. At this time, the first input connector of the power supply selection switch 11 is electrically connected to its output connector. The 220V AC mains power is converted into 28V AC power through a transformer, and the 28V AC power is converted into 28V DC power through a rectifier for use by the device. The second mode is to switch the power supply selection switch 11 to the second input connector. At this time, the second input connector of the power supply selection switch 11 is electrically connected to its output connector, and the second input connector of the power supply selection switch 11 is electrically connected to the DC power supply positive connector of the aircraft, and the negative cable is grounded, so that the 28V DC power of the aircraft can be used for power supply.

[0036] To check whether the power module 1 is supplying power normally, please refer to Figure 1 and Figure 2 In a preferred embodiment, the power module 1 further includes a power supply resistor 12, a power supply diode 13 and a power supply indicator light 14, one end of the power supply resistor 12 is electrically connected to the output connector of the power supply selection switch 11, the other end of the power supply resistor 12 is electrically connected to the positive electrode of the power supply diode 13, the negative electrode of the power supply diode 13 is electrically connected to one end of the power supply indicator light 14, and the other end of the power supply indicator light 14 is electrically connected to the negative electrode cable 26. When the device is powered normally (regardless of the power supply mode), the power supply indicator light 14 will be lit.

[0037] To facilitate the detection of the supply voltage of power module 1, please refer to Figure 1 and Figure 2 In a preferred embodiment, the power module 1 further comprises a second voltmeter 15, one end of the second voltmeter 15 is electrically connected to the output connector of the power supply selection switch 11, and the other end of the second voltmeter 15 is electrically connected to the negative cable 26. When the device is powered normally (regardless of the power supply mode), the second voltmeter 15 can display the magnitude of the power supply voltage.

[0038] In order to better understand the present invention, the following Figure 1 and Figure 2 The working process of the aircraft waveguide switch detection device provided by the utility model is described in detail: during the assembly in the aircraft assembly workshop, the rotation function of the aircraft waveguide switch is detected. Specifically, the negative pole of the power module 1 is electrically connected to the negative pole connector of the aircraft waveguide switch, the left output end of the left-right selection switch 21 is electrically connected to the left connector of the aircraft waveguide switch, the right output end of the left-right selection switch 21 is electrically connected to the right connector of the aircraft waveguide switch, and then the knob of the left-right selection switch 21 is manually turned to the left position. At this time, the power module 1 is electrically connected to the left connector of the aircraft waveguide switch, the aircraft waveguide switch is powered and rotated to the left, and the aircraft waveguide switch is observed to see whether it can turn left normally. After the test is normal, the knob of the left-right selection switch 21 is manually turned to the right position. At this time, the power module 1 is electrically connected to the right connector of the aircraft waveguide switch, the aircraft waveguide switch is powered and rotated to the right, and the aircraft waveguide switch is observed to see whether it can turn right normally. If both tests are normal, it indicates that the aircraft waveguide switch is well installed.

[0039] The utility model can also detect the power supply of the aircraft waveguide switch. The specific method is: manually turn the knob of the left and right selection switch 21 to the neutral end. At this time, the power module 1 is electrically disconnected from the aircraft waveguide switch. Then, the aircraft is powered on, and then the display control, electronic countermeasure and other related systems on the aircraft's avionics starter board are turned on in sequence to power on the system. After the reactance system is powered on, the waveguide switch will also be powered on. Professionals control the position of the target simulator device relative to the aircraft. First, the target simulator device is located on the left side of the aircraft. At this time, theoretically, the left connector of the aircraft waveguide switch should be powered on. Observe the left indicator light 22. Check whether the right indicator light 23 lights up normally. If it lights up normally, it indicates that the left connector of the aircraft waveguide switch is powered normally. Then switch the voltage selection switch 215 to the left input end, detect the voltage of the left connector of the aircraft waveguide switch. If the voltage is normal, the left connector is powered normally. Then place the target simulator device on the right side of the aircraft. At this time, theoretically, the right connector of the aircraft waveguide switch should be powered. Observe whether the right indicator light 23 lights up normally. If it lights up normally, it indicates that the right connector of the aircraft waveguide switch is powered normally. Then switch the voltage selection switch 215 to the right input end, detect the voltage of the right connector of the aircraft waveguide switch. If the voltage is normal, the right connector is powered normally.

[0040] During assembly in the final assembly workshop, power is supplied through the power module 1, and the left connector or the right connector of the aircraft waveguide switch is selected through the left and right selection switches 21, so that the aircraft waveguide switch can be directly driven to turn left or right, so that it can be judged whether the waveguide switch can turn left and right normally, and then it can be judged whether the tightening torque of the connecting screws of the aircraft waveguide switch meets the rotation requirement. The utility model can move the fault forward, and can detect whether the rotation function of the aircraft waveguide switch is normal during assembly in the final assembly workshop, avoiding the problem of increased disassembly and assembly workload caused by detecting the aircraft waveguide switch after the aircraft is fully assembled, saving a lot of manpower and material resources, shortening the production cycle, and since there is no need for power-on debugging, the risk of machine damage and the harm of radiation to personnel can be reduced.

[0041] Taking the waveguide switch in the equipment compartment as an example, when the waveguide switch is tested when the aircraft is in good condition, if the waveguide switch detects a fault, it will take 3-4 people 2 days to disassemble and assemble the waveguide switch. The utility model uses the equipment to test the waveguide switch after final assembly, so as to judge in advance whether the waveguide switch has a fault. During the final assembly, it only takes one person 2 hours to disassemble and assemble the waveguide switch, which greatly shortens the production cycle and can also reduce the number and time of high-voltage troubleshooting tests, thereby reducing the risk of machine damage and radiation hazards to personnel. Therefore, the equipment actually solves the production needs in the maintenance process.

[0042] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed in the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft waveguide switch detection device, characterized in that: Including power module and detection mechanism; The negative electrode of the power module is used to be electrically connected to the negative electrode connector of the aircraft waveguide switch; The detection mechanism includes a left-right selection switch, the input end of the left-right selection switch is electrically connected to the positive electrode of the power module, the left output end of the left-right selection switch is used to be electrically connected to the left connector of the aircraft waveguide switch, and the right output end of the left-right selection switch is used to be electrically connected to the right connector of the aircraft waveguide switch; The detection mechanism also includes a left indicator light and a right indicator light, wherein two ends of the left indicator light are respectively electrically connected to the left output end of the left and right selection switches and the negative pole of the power module, and two ends of the right indicator light are respectively electrically connected to the right output end of the left and right selection switches and the negative pole of the power module; The detection mechanism also includes a left cable, a right cable and a negative cable, one end of the left cable is electrically connected to the left output end of the left / right selection switch, the other end of the left cable is connected to a left plug, and the left plug is used to be electrically connected to the left connector of the aircraft waveguide switch; one end of the right cable is electrically connected to the right output end of the left / right selection switch, the other end of the right cable is connected to a right plug, and the right plug is used to be electrically connected to the right connector of the aircraft waveguide switch; one end of the negative cable is electrically connected to the negative pole of the power module, the other end of the negative cable is connected to a negative plug, and the negative plug is used to be electrically connected to the negative connector of the aircraft waveguide switch.

2. The aircraft waveguide switch detection device according to claim 1, characterized in that: The detection mechanism also includes a left resistor and a left diode, one end of the left resistor is electrically connected to the left cable, the other end of the left resistor is connected to the positive electrode of the left diode, the negative electrode of the left diode is electrically connected to one end of the left indicator light, and the other end of the left indicator light is electrically connected to the negative electrode cable.

3. The aircraft waveguide switch detection device according to claim 2, characterized in that: The detection mechanism also includes a right resistor and a right diode, one end of the right resistor is electrically connected to the right cable, the other end of the right resistor is connected to the positive electrode of the right diode, the negative electrode of the right diode is electrically connected to one end of the right indicator light, and the other end of the right indicator light is electrically connected to the negative cable.

4. The aircraft waveguide switch detection device according to claim 3, characterized in that: The detection mechanism also includes a light detection switch, one end of which is electrically connected to the input end of the left and right selection switch, and the other end of which is electrically connected to both the left output end and the right output end of the left and right selection switch.

5. The aircraft waveguide switch detection device according to claim 1, characterized in that: The detection mechanism also includes a voltage selection switch and a first voltmeter, the output end of the voltage selection switch is electrically connected to one end of the first voltmeter, the left input end of the voltage selection switch is electrically connected to the left cable, the right input end of the voltage selection switch is electrically connected to the right cable, and the other end of the first voltmeter is electrically connected to the negative cable.

6. The aircraft waveguide switch detection device according to claim 1, characterized in that: The power supply module includes a transformer, a rectifier and a power supply selection switch, the input end of the transformer is connected to the mains, the input end of the rectifier is electrically connected to the output end of the transformer, the negative output end of the rectifier is electrically connected to the negative cable, the first input connector of the power supply selection switch is electrically connected to the positive output end of the rectifier, the second input connector of the power supply selection switch is used to be electrically connected to the DC power supply positive connector of the aircraft, and the output connector of the power supply selection switch is electrically connected to the input end of the left and right selection switches.

7. The aircraft waveguide switch detection device according to claim 6, characterized in that: The power supply module also includes a power supply resistor, a power supply diode and a power supply indicator light. One end of the power supply resistor is electrically connected to the output connector of the power supply selection switch, the other end of the power supply resistor is electrically connected to the positive electrode of the power supply diode, the negative electrode of the power supply diode is electrically connected to one end of the power supply indicator light, and the other end of the power supply indicator light is electrically connected to the negative electrode cable.

8. The aircraft waveguide switch detection device according to claim 6, characterized in that: The power supply module further includes a second voltmeter, one end of the second voltmeter is electrically connected to the output connector of the power supply selection switch, and the other end of the second voltmeter is electrically connected to the negative cable.

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