Mobile aircraft full-scale lightning test device

Abstract

The present application relates to the technical field of aircraft testing, and discloses a mobile aircraft whole-machine lightning test device, which comprises a mobile high-voltage cabin, a mobile monitoring cabin, a charging system, a residual charge discharge unit and a lightning waveform generating system. The charging system performs energy injection on the high-voltage capacitor group of the lightning waveform generating system. After the energy injection is completed, the mobile monitoring cabin is controlled through the measurement and control end to inject a preset lightning waveform into the aircraft test piece. The residual charge discharge unit intelligently starts double-channel discharge based on real-time voltage monitoring, and simultaneously links the cabin door access lock to form a test closed loop. The present application can be freely moved without the need to transport the aircraft to a fixed test site, and is suitable for instant testing beside the production line or in the field. The closed lightning waveform generating cabin can accommodate the whole machine, avoiding the electromagnetic coupling distortion problem caused by traditional segmented testing. The double-channel redundant discharge design combined with real-time voltage monitoring completely eliminates the risk of residual charge.

Description

Technical Field

[0001] This invention relates to the field of aircraft testing, and more specifically, to a mobile aircraft full-aircraft lightning test apparatus. Background Technology

[0002] Aircraft lightning environment testing is a critical part of aircraft development. According to GJB 1389A and GJB 3567, the whole-aircraft lightning test should inject the direct lightning effect A wave, indirect lightning effect A wave, and indirect lightning effect H wave as specified in the standards. This injection method is to reproduce the lightning effect and study the aircraft's state under lightning environment. It is necessary to conduct whole-aircraft direct lightning effect and indirect lightning effect tests on the aircraft, measure the transient induced open-circuit voltage and short-circuit current of the aircraft's internal electronic and electrical equipment and systems, and verify whether the aircraft's electromagnetic protection design meets the standard requirements.

[0003] Currently, apart from building a full-size aircraft lightning test site to solve the problem of full-aircraft lightning testing, there is no better solution. However, this solution is not applicable to different aircraft models, and the full-size test site cannot be moved, occupies a large area, and is not conducive to testing in different scenarios. Summary of the Invention

[0004] This invention provides a mobile aircraft full-aircraft lightning test device, which solves the technical problems in related technologies where lightning test devices cannot be miniaturized and can be moved to be suitable for different testing environments.

[0005] This invention provides a mobile aircraft full-aircraft lightning testing device, comprising:

[0006] The mobile high-voltage cabin includes a cabin body, a mobile cabin, a mobile sliding rail, and a flip-over protective plate. The mobile sliding rail is installed on the top and bottom of the mobile cabin and is used for mutual sliding between the mobile cabin and the cabin body. The side panels of the cabin body are openable structures. The test specimen is sent into the cabin body from the side. A test platform is provided on the inner wall of the bottom end of the cabin body. The test specimen is tested on the test platform. When the mobile cabin is completely moved out of the cabin body, the flip-over protective plate is flipped and installed on the end face of the mobile cabin. The flip-over protective plate is used to seal the cavity inside the mobile cabin to form an independent lightning waveform generating chamber.

[0007] The mobile monitoring cabin includes a self-sufficient power supply and a measurement and control system, both of which are installed inside the cabin. The measurement and control system is used to record and transmit test data within the device, while the self-sufficient power supply is used to power the test system.

[0008] The charging system includes a voltage regulating control console, a step-up transformer, an AC power supply, and a charging switch. The AC power supply is connected in series with the voltage regulating control console, the charging control system, and the step-up transformer. This system is used to charge the lightning waveform generation system.

[0009] The remaining charge discharging unit comprises a pneumatic high-voltage switch and a discharge resistor, and the pneumatic high-voltage switch and the discharge resistor are connected in series to a remaining charge discharging end to form a main discharge loop.

[0010] The lightning waveform generating system comprises a detachable capacitor bank assembly and a bearing PCB board, the capacitor bank assembly comprises a first capacitor unit, a second capacitor unit and a third capacitor unit, the capacitor bank assembly is installed on the bearing PCB board, a diode, a variable resistor, an inductor, a remaining charge discharging end and a test piece connecting port are integrated on the bearing PCB board, the first capacitor unit, the second capacitor unit and the third capacitor unit are connected in parallel, the first capacitor unit, the second capacitor unit and the third capacitor unit are respectively provided with a first switch, a second switch and a third switch, the capacitor bank assembly is connected in parallel with a switch group, the variable resistor, the inductor and the test piece connecting port at two ends of the capacitor bank assembly, and the variable resistor, the inductor and the test piece connecting port are connected in series.

[0011] Further, a copper mesh shielding layer and a nanocrystalline magnetic coating are arranged in the mobile cabin and the cabin body.

[0012] Further, a grounding terminal is arranged at the bottom end of the mobile cabin, and the top end of the grounding terminal is connected to the main discharge loop.

[0013] Further, when the first switch is closed, the step-up transformer and the diode are connected to the first capacitor unit, and the system is switched to a direct effect A wave generating end; when the second switch is closed, the step-up transformer and the diode are connected to the second capacitor unit, and the system is switched to an indirect effect A wave generating end; and when the third switch is closed, the step-up transformer and the diode are connected to the third capacitor unit, and the system is switched to an indirect effect H wave generating end.

[0014] Further, the switch group comprises a fourth switch, a fifth switch and a sixth switch, and the fourth switch, the fifth switch and the sixth switch are respectively connected to the connection ends of the first capacitor unit, the second capacitor unit and the third capacitor unit.

[0015] Further, when the fourth switch is closed, the first capacitor unit is connected to the variable resistor, the inductor and the test piece; when the fifth switch is closed, the second capacitor unit is connected to the variable resistor, the inductor and the test piece; and when the sixth switch is closed, the third capacitor unit is connected to the variable resistor, the inductor and the test piece.

[0016] Further, the measurement and control system comprises a charging system monitoring unit, a lightning waveform generating system monitoring unit, a high-voltage switch control unit, a test piece current and voltage measurement unit, a logic control unit, a measurement and control parameter transmission unit and a shelter voltage monitoring unit.

[0017] The charging system monitoring unit is used for monitoring the charging system; the lightning waveform generating system monitoring unit is used for monitoring the lightning waveform generating system; the high-voltage switch control unit is used for monitoring the pneumatic high-voltage switch in the residual charge discharging unit; the test piece current and voltage measuring unit is used for measuring the monitoring parameters of the test piece; the shelter voltage monitoring unit is used for monitoring the voltage in the mobile high-voltage shelter; the logic control unit and the measurement and control parameter transmission unit are used for cooperating with other units to perform measurement and control operations, and part of the measurement and control parameter transmission unit is installed in the mobile high-voltage shelter, and the other part is installed in the mobile measurement and control shelter, and the two parts are connected through a cable.

[0018] Further, an external control box and a relay junction box are installed on the outer wall of the mobile cabin, and the bottom end of the external control box extends out of a wire for connecting the lightning waveform generating system.

[0019] Further, the voltage regulating console adjusts the charging voltage of the lightning waveform generating system, and the step-up transformer is used to increase the charging voltage, and the maximum charging voltage after being increased can meet the charging requirements of the direct effect A wave, the indirect effect A wave and the indirect effect H wave.

[0020] Further, the residual charge discharging unit further comprises a voltage sensor, and the voltage sensor monitors the voltage in the cabin body and the mobile cabin.

[0021] The beneficial effects of the present application are that:

[0022] The whole device of the present application can be freely moved, without the need to transport the aircraft to a fixed test site, and is especially suitable for instant testing beside the production line or in the field, the whole machine can be accommodated in the sealed lightning waveform generating cabin, the electromagnetic coupling distortion problem caused by traditional segmented testing is avoided, and the double-channel redundant discharge design is combined with real-time voltage monitoring to completely eliminate the residual charge risk, the shelter door is automatically locked during high-voltage discharge, the electromagnetic shielding cabin body formed by the overturning protection plate realizes the physical isolation of man and machine. BRIEF DESCRIPTION OF DRAWINGS

[0023] Figure 1 is a configuration schematic diagram of the mobile aircraft full-machine lightning test device of the present application;

[0024] Figure 2 is a test circuit principle diagram of the mobile aircraft full-machine lightning test device of the present application;

[0025] Figure 3 is a structure schematic diagram of the mobile high-voltage shelter of the mobile aircraft full-machine lightning test device of the present application;

[0026] Figure 4 is a side perspective view of the Figure 3 of the present application;

[0027] Figure 5 is a flowchart of system initialization of the mobile aircraft full-machine lightning test device of the present application.

[0028] In the figure: 1, AC power supply; 2, charging control system; 3, step-up transformer; 4, discharge resistance; 5, pneumatic high-voltage switch; 6, diode; 7, first switch; 8, second switch; 9, third switch; 10, fourth switch; 11, first capacitor unit; 12, fifth switch; 13, second capacitor unit; 14, charging switch; 15, sixth switch; 16, third capacitor unit; 17, variable resistance; 18, inductor; 19, test piece; 100, cabin body; 110, side panel; 120, turnover protection plate; 130, test bench; 200, mobile cabin; 210, mobile slide rail; 300, external control box; 400, relay terminal box; 500, grounding terminal; 600, lightning waveform generation system. DETAILED DESCRIPTION

[0029] The subject matter described herein will now be discussed with reference to example implementations. It should be understood that the discussion of these implementations is merely meant to provide a better understanding of the subject matter described herein and can be changed in the function and arrangement of the elements discussed without departing from the scope of the content of this specification. Various processes or components can be omitted, substituted, or added according to need from various examples. In addition, features described with respect to some examples can also be combined in other examples.

[0030] As shown in Figures 1-5 , the mobile aircraft full-machine lightning test device comprises:

[0031] The mobile high-voltage square cabin comprises a cabin body 100, a mobile cabin 200, a square cabin door, a mobile slide rail 210, a turnover protection plate 120, an external control box 300, and a relay terminal box 400;

[0032] The charging system comprises a voltage regulation console, a step-up transformer 3, an AC power supply 1, and a charging switch, and the AC power supply 1 is connected in series with the voltage regulation console, the charging control system 2, and the step-up transformer 3;

[0033] The voltage regulation console adjusts the charging voltage to the lightning waveform generation system 600;

[0034] The step-up transformer 3 is used to boost the charging voltage, and the maximum charging voltage can meet the charging requirements of the three lightning waveform generators of the direct effect A wave, the indirect effect A wave, and the indirect effect H wave;

[0035] The charging control system 2 is used to control the adjustment of the charging voltage and ensure the constant charging current, and can control the charging of the three lightning waveform generators of the direct effect A wave, the indirect effect A wave, and the indirect effect H wave;

[0036] The lightning waveform generating system 600 comprises a generator capable of switching the direct effect A wave, the indirect effect A wave and the indirect effect H wave;

[0037] The measurement and control system comprises a charging system monitoring unit, a lightning waveform generating system monitoring unit, a high-voltage switch control unit, a test piece current and voltage measurement unit, a logic control unit, a measurement and control parameter transmission unit and a shelter voltage monitoring unit;

[0038] In an embodiment of the present application, the self-sustaining power supply and the measurement and control system are installed in the mobile monitoring shelter;

[0039] The residual charge discharge unit comprises a pneumatic high-voltage switch 5 and a discharge resistor 4, which are connected in series to the residual charge discharge end to form a main discharge circuit;

[0040] The test piece 19 is an aircraft to be tested, which is subjected to aircraft lightning environment tests through the test device;

[0041] In an embodiment of the present application, the mobile sliding rail 210 is installed at the top and bottom ends of the mobile cabin 200, and is used for mutual sliding between the mobile cabin 200 and the cabin body 100;

[0042] Handles are installed on the outer walls of the two ends of the mobile cabin 200, which can be used for manually pushing and pulling the mobile cabin 200;

[0043] The mobile cabin 200 and the cabin body 100 are provided with an electromagnetic isolation mechanism: a copper mesh shielding layer (0.3 mm thick) and a nanocrystalline magnetic coating are arranged in the mobile cabin 200, which are used for absorbing 99% electromagnetic interference, and at the same time, the measurement and control signals are transmitted through optical fibers (error rate <10 -9 );

[0044] The external control box 300 and the relay junction box 400 are both installed on the outer wall of the mobile cabin 200, and the bottom end of the external control box 300 extends out of a wire, which comprises a cable and an optical fiber;

[0045] A grounding terminal 500 is arranged at the bottom end of the mobile cabin 200, and the top end of the grounding terminal 500 is connected to the main discharge circuit;

[0046] The side panel 110 of the cabin body 100 is a openable structure, the test piece 19 is sent into the cabin body 100 from the side of the cabin body 100, and a test bench 130 is arranged on the inner wall of the bottom end of the cabin body 100;

[0047] The shelter door is arranged on the outer wall of the side of the cabin body 100 away from the mobile cabin 200;

[0048] A reversible protection plate 120 is arranged on the inner wall of the top of the cabin 100, and when the mobile cabin 200 is completely moved out of the cabin 100, the reversible protection plate 120 is reversibly arranged on the end surface of the mobile cabin 200, used for sealing the cavity in the mobile cabin 200, forming an independent lightning wave shaping cabin;

[0049] The lightning wave shaping system 600 comprises a detachable capacitor group assembly and a bearing PCB board, the capacitor group assembly comprises a first capacitor unit 11, a second capacitor unit 13 and a third capacitor unit 16, and the capacitor group assembly is arranged on the bearing PCB board, and a diode 6, a variable resistor 17, an inductor 18, a residual charge discharge end and a test piece 19 connecting port are integrated on the bearing PCB board;

[0050] The first capacitor unit 11, the second capacitor unit 13 and the third capacitor unit 16 are connected in parallel, and the first switch 7, the second switch 8 and the third switch 9 are arranged at the front ends of the first capacitor unit 11, the second capacitor unit 13 and the third capacitor unit 16 respectively;

[0051] When the first switch 7 is closed, the step-up transformer 3 and the diode 6 are connected to the first capacitor unit 11, and the direct effect A wave shaping end is switched;

[0052] When the second switch 8 is closed, the step-up transformer 3 and the diode 6 are connected to the second capacitor unit 13, and the indirect effect A wave shaping end is switched;

[0053] When the third switch 9 is closed, the step-up transformer 3 and the diode 6 are connected to the third capacitor unit 16, and the indirect effect H wave shaping end is switched;

[0054] In an embodiment of the present application, other wave shape switching can also be realized by replacing the first capacitor unit 11, the second capacitor unit 13 and the third capacitor unit 16;

[0055] The switch group, the variable resistor 17, the inductor 18 and the test piece 19 connecting port are connected in parallel at the two ends of the capacitor group assembly, and the variable resistor 17, the inductor 18 and the test piece 19 connecting port are connected in series;

[0056] The connection switch 14 is further arranged at the port of the capacitor group assembly, and the connection switch 14 is used for controlling the connection and disconnection of the passage;

[0057] The switch group comprises a fourth switch 10, a fifth switch 12 and a sixth switch 15, and the fourth switch 10, the fifth switch 12 and the sixth switch 15 are connected to the connecting ends of the first capacitor unit 11, the second capacitor unit 13 and the third capacitor unit 16 respectively;

[0058] When the capacitor group assembly is discharged, the first switch 7, the second switch 8 and the third switch 9 are all in the open state;

[0059] Closing the fourth switch 10, the first capacitor unit 11 is connected to the variable resistor 17, the inductor 18 and the test piece 19;

[0060] Closing the fifth switch 12, the second capacitor unit 13 is connected to the variable resistor 17, the inductor 18 and the test piece 19;

[0061] Closing the sixth switch 15, the third capacitor unit 16 is connected to the variable resistor 17, the inductor 18 and the test piece 19;

[0062] The test piece 19 is connected to the test end of the test piece 19 through the cable;

[0063] The measurement and control system comprises a charging system monitoring unit, a lightning waveform generating system monitoring unit, a high-voltage switch control unit, a test piece current and voltage measurement unit, a logic control unit, a measurement and control parameter transmission unit, a shelter voltage monitoring unit and a self-sustaining power supply;

[0064] The self-sustaining power supply is used for supplying power to the measurement and control system;

[0065] The charging system monitoring unit is used for monitoring the charging system;

[0066] The lightning waveform generating system monitoring unit is used for monitoring the lightning waveform generating system 600;

[0067] The high-voltage switch control unit is used for monitoring the pneumatic high-voltage switch 5 in the residual charge discharge unit;

[0068] The test piece current and voltage measurement unit is used for measuring the monitoring parameters of the test piece 19;

[0069] The shelter voltage monitoring unit is used for monitoring the voltage in the mobile high-voltage shelter;

[0070] The logic control unit and the measurement and control parameter transmission unit are used for cooperating with other units to perform measurement and control operations, part of the measurement and control parameter transmission unit is installed in the mobile high-voltage shelter, and the other part is installed in the mobile measurement and control shelter, and the two parts are connected through the cable;

[0071] The pneumatic high-voltage switch 5 comprises a pneumatic driving member and a high-voltage discharge switch, the driving end of the pneumatic driving member is connected to the control end of the high-voltage discharge switch, after the test is completed, the pneumatic driving high-voltage discharge switch is closed to release the residual charge of the test piece 19 and the capacitor in the capacitor group assembly, the residual charge discharge unit adopts a double-channel redundant design, and the failure probability of discharge is reduced to 10 -7 ;

[0072] The residual charge discharge unit further comprises a voltage sensor which monitors the voltage inside the cabin 100 and the mobile cabin 200, when 50v < voltage < 500v, the standby thyristor discharge is activated, which is reduced to a safe voltage within 10ms, the mechanical locking of the cabin door of the mobile high-voltage cabin is closed; when the voltage > 500v, the main discharge circuit is started, the circuit of the pneumatic high-voltage switch 5 and the discharge resistor 4 is started.

[0073] In an embodiment of the present application, the specific steps of the mobile aircraft full machine lightning test device in the test process are as follows:

[0074] Step 1, test preparation: open the side of the cabin 100, put the aircraft to be tested into the cabin 100, connect the test piece 19 to the port of the aircraft test end through the cable, manually push and pull the mobile cabin 200 handle along the mobile slide rail 210, and push the mobile cabin 200 into the cabin 100, and turn the protection plate 120 to automatically close and form a sealed lightning waveform generating cabin with the end face of the mobile cabin 200;

[0075] Step 2, system initialization: as shown in Figure 5 The ground terminal 500 is connected to the main discharge circuit (ground resistance < 0.5Ω), and the operator selects the waveform type (direct A wave / indirect A wave / indirect H wave) through the external control box 300;

[0076] Step 3, capacitor charging:

[0077] Charging circuit activation:

[0078] AC power supply 1→voltage control console→step-up transformer 3→charging switch closed;

[0079] Waveform capacitor selection:

[0080] Direct effect A wave: close the first switch 7 (connect the first capacitor unit 11);

[0081] Indirect effect A wave: close the second switch 8 (connect the second capacitor unit 13);

[0082] Indirect effect H wave: close the third switch 9 (connect the third capacitor unit 16);

[0083] Diode 6 prevents reverse current, and step-up transformer 3 outputs 200kV high voltage;

[0084] Step 4, lightning waveform generation: disconnect the first / second / third switch (cut off the charging circuit), and close the corresponding discharge switch according to the selected waveform:

[0085] Fourth switch 10 (first capacitor unit 11 discharge);

[0086] Fifth switch 12 (second capacitor unit 13 discharge);

[0087] Sixth switch 15 (third capacitor unit 16 discharge);

[0088] When the switch group is connected, the connection switch 14 is closed, and the capacitor discharges to the test piece;

[0089] Waveform generation: capacitor energy → variable resistor 17 → inductor 18 → test piece 19 connection port → test piece 19;

[0090] The variable resistor 17 adjusts the current rise rate, and the inductor 18 shapes the waveform attenuation characteristics, and the measurement and control system records the aircraft current / voltage response in real time;

[0091] Step 5, residual charge discharge: when the main discharge loop fails, the thyristor standby loop automatically takes over, and the shelter door is forcibly locked when the voltage is greater than 50V;

[0092] Step 6, data recovery and reset: the test piece current and voltage measurement unit derives data, the logic control unit generates a test report, opens the flip guard 120, moves the cabin 200 out of the cabin body 100, disconnects the test piece 19 connection port, removes the aircraft, and all switches return to the open state.

[0093] Through the use of the device, it takes about 45 minutes (including 10 minutes of safety check) from the aircraft loading to the data recovery completion, which is 5 times more efficient than the traditional fixed test device.

[0094] The embodiments of the application are described above, but the application is not limited to the specific embodiments described above, and the specific embodiments described above are only illustrative and not limiting, and those skilled in the art can make many forms under the inspiration of the application, which all belong to the protection of the application.

Claims

1. A mobile aircraft-wide lightning test device, characterized in that, include: The mobile high-voltage cabin includes a cabin body, a mobile cabin, a mobile sliding rail, and a flip-over protective plate. The mobile sliding rail is installed on the top and bottom of the mobile cabin and is used for mutual sliding between the mobile cabin and the cabin body. The side panels of the cabin body are openable structures. The test specimen is sent into the cabin body from the side. A control table is provided on the inner wall of the bottom end of the cabin body. The test specimen is tested on the control table. When the mobile cabin is completely moved out of the cabin body, the flip-over protective plate is flipped and installed on the end face of the mobile cabin. The flip-over protective plate is used to seal the cavity inside the mobile cabin to form an independent lightning waveform generating chamber. Both the mobile cabin and the cabin body are equipped with copper mesh shielding layers; The mobile monitoring cabin includes a self-sufficient power supply and a measurement and control system, both of which are installed inside the cabin. The measurement and control system is used to record and transmit test data within the device, while the self-sufficient power supply is used to power the test system. The measurement and control system includes a charging system monitoring unit, a lightning waveform generation system monitoring unit, a high-voltage switch control unit, a test piece current and voltage measurement unit, a logic control unit, a measurement and control parameter transmission unit, and a cabin voltage monitoring unit. The charging system monitoring unit is used to monitor the charging system; the lightning waveform generation system monitoring unit is used to monitor the lightning waveform generation system; the high-voltage switch control unit is used to monitor the pneumatic high-voltage switch in the residual charge discharge unit; the test piece current and voltage measurement unit is used to measure the monitoring parameters of the test piece; the cabin voltage monitoring unit is used to monitor the voltage inside the mobile high-voltage cabin; the logic control unit and the measurement and control parameter transmission unit are used to cooperate with other units to perform measurement and control operations. One part of the measurement and control parameter transmission unit is installed inside the mobile high-voltage cabin, and the other part is installed inside the mobile measurement and control cabin. The two parts are connected by a cable. The charging system includes a voltage regulating control console, a step-up transformer, an AC power supply, and a charging switch. The AC power supply is connected in series with the voltage regulating control console, the charging control system, and the step-up transformer. This system is used to charge the lightning waveform generation system. The residual charge discharge unit includes a pneumatic high-voltage switch and a discharge resistor, which are connected in series to the residual charge discharge terminal to form the main discharge circuit; the residual charge discharge unit also includes a voltage sensor, which monitors the voltage inside the cabin and the mobile cabin; A lightning waveform generating system includes a detachable capacitor bank assembly and a carrier PCB board. The capacitor bank assembly includes a first capacitor unit, a second capacitor unit, and a third capacitor unit. The capacitor bank assembly is mounted on the carrier PCB board, which also integrates a diode, a variable resistor, an inductor, a residual charge discharge terminal, and a test piece connection port. The first, second, and third capacitor units are connected in parallel. A first switch, a second switch, and a third switch are respectively provided at the connection terminals of the first, second, and third capacitor units. The two ends of the capacitor bank assembly are connected in parallel to the switch group, the variable resistor, the inductor, and the test piece connection port. The variable resistor, the inductor, and the test piece connection port are connected in series.

2. The mobile aircraft full-aircraft lightning test device according to claim 1, characterized in that, A grounding terminal is located at the bottom of the mobile cabin, and the top of the grounding terminal is connected to the main venting circuit.

3. The mobile aircraft full-aircraft lightning test device according to claim 2, characterized in that, When the first switch is closed, the step-up transformer and diode are connected to the first capacitor unit, switching to the direct-effect A-wave generation terminal; when the second switch is closed, the step-up transformer and diode are connected to the second capacitor unit, switching to the indirect-effect A-wave generation terminal; when the third switch is closed, the step-up transformer and diode are connected to the third capacitor unit, switching to the indirect-effect H-wave generation terminal.

4. The mobile aircraft whole-aircraft lightning test device according to claim 3, characterized in that, The switch group includes a fourth switch, a fifth switch, and a sixth switch, which are respectively connected to the connection terminals of the first capacitor unit, the second capacitor unit, and the third capacitor unit.

5. The mobile aircraft full-aircraft lightning test device according to claim 4, characterized in that, When the fourth switch is closed, the first capacitor unit is connected to the variable resistor, inductor, and test piece; when the fifth switch is closed, the second capacitor unit is connected to the variable resistor, inductor, and test piece; when the sixth switch is closed, the third capacitor unit is connected to the variable resistor, inductor, and test piece.

6. The mobile aircraft whole-aircraft lightning test device according to claim 5, characterized in that, An external control box and a relay junction box are installed on the outer wall of the mobile cabin, with cables extending from the bottom of the external control box.

7. The mobile aircraft whole-aircraft lightning test device according to claim 6, characterized in that, The voltage regulating control console adjusts the charging voltage of the lightning waveform generation system, and the step-up transformer is used to increase the charging voltage. The maximum charging voltage after the increase can meet the charging requirements of the direct effect A wave, the indirect effect A wave, and the indirect effect H wave.

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