Mobile thunder and lightning test device for whole aircraft

Abstract

The invention relates to the technical field of aircraft testing, and discloses a mobile aircraft whole-aircraft thunder and lightning testing device which comprises a mobile high-voltage square cabin, a mobile monitoring square cabin, a charging system, a residual charge discharging unit and a thunder and lightning waveform generating system. Through control of a measurement and control end of a mobile monitoring shelter, a preset lightning waveform is injected into an aircraft test piece, a residual charge discharge unit intelligently starts dual-channel discharge based on real-time voltage monitoring, and meanwhile, a shelter access control lock is linked to form a test closed loop. The device can move freely, an airplane does not need to be transported to a fixed test site, the device is suitable for real-time testing in an external field or beside a production line, the whole machine can be accommodated through the closed lightning waveform generation cabin, the problem of electromagnetic coupling distortion caused by a traditional segmented test is avoided, a dual-channel redundancy discharge design is combined with real-time voltage monitoring, and the reliability of the device is improved. And the residual charge risk is thoroughly eliminated.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft testing, more particularly, it relates to a mobile aircraft full machine lightning test device. BACKGROUND

[0002] The aircraft lightning environment test is a key link in the development of the aircraft, according to the requirements of GJB 1389A and GJB 3567, the aircraft full machine lightning test should inject the standard specified lightning direct effect A wave, lightning indirect effect A wave, lightning indirect effect H wave, the injection method is to reproduce the lightning effect, study the state of the aircraft in the lightning environment, the aircraft needs to be tested for lightning direct effect and lightning indirect effect, measure the open circuit voltage and short circuit current of the transient induction of the internal electronic and electrical equipment and system of the aircraft, and test whether the electromagnetic protection design of the aircraft meets the standard requirements.

[0003] At present, there is no better solution to solve the problem of aircraft full machine lightning test except to build a full-size aircraft lightning test site, but it cannot be applied to different aircraft models, and the full-size test site cannot be moved, and the land occupation is large, which is not conducive to testing in different scenes. SUMMARY

[0004] The present application provides a mobile aircraft full machine lightning test device, which solves the technical problems of lightning test device miniaturization and mobile application to different test environments in related technologies.

[0005] The present application provides a mobile aircraft full machine lightning test device, which includes: The mobile high-voltage cabin includes a cabin body, a mobile cabin, a mobile slide rail and a turnover protection plate, the mobile slide rail is installed at the top and bottom ends of the mobile cabin, the mobile slide rail is used for the mutual sliding between the mobile cabin and the cabin body, the side panel of the cabin body is a openable structure, the test piece is sent into the cabin body from the side of the cabin body, a test table is arranged on the inner wall of the bottom end of the cabin body, the test piece is tested on the test table, when the mobile cabin is completely moved out of the cabin body, the turnover protection plate is installed on the end face of the mobile cabin by turning over, and the turnover protection plate is used for sealing the cavity in the mobile cabin to form an independent lightning waveform generating cabin; The mobile monitoring cabin includes a self-sustaining power supply and a measurement and control system, both of which are arranged in the cabin, the measurement and control system is used for recording and transmitting the test data in the device, and the self-sustaining power supply is used for power supply of the test system; The charging system includes a voltage regulation console, a step-up transformer, an alternating current power supply and a charging switch, the alternating current power supply is connected in series with the voltage regulation console, the charging control system and the step-up transformer, and the system is used for charging the lightning waveform generating system; The residual charge discharge unit includes a pneumatic high-voltage switch and a discharge resistor, the pneumatic high-voltage switch and the discharge resistor are connected in series to a residual charge discharge end to form a main discharge loop; 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 residual charge discharge end and a test piece connection 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, a first switch, a second switch and a third switch are arranged at the connection ends of the first capacitor unit, the second capacitor unit and the third capacitor unit, the connection ends of the variable resistor, the inductor and the test piece connection port are connected in parallel at the two ends of the capacitor bank assembly, and the variable resistor, the inductor and the test piece connection port are connected in series.

[0006] Further, a copper mesh shielding layer and a nanocrystalline magnetic coating are arranged in the mobile cabin and the cabin body.

[0007] 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 circuit.

[0008] Further, when the first switch is closed, the step-up transformer and the diode are connected to the first capacitor unit, and the direct effect A wave generating end is switched; when the second switch is closed, the step-up transformer and the diode are connected to the second capacitor unit, and the indirect effect A wave generating end is switched; and when the third switch is closed, the step-up transformer and the diode are connected to the third capacitor unit, and the indirect effect H wave generating end is switched.

[0009] 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 connected to the connection ends of the first capacitor unit, the second capacitor unit and the third capacitor unit respectively.

[0010] 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.

[0011] 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. 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.

[0012] 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.

[0013] 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.

[0014] Further, the residual charge discharging unit further comprises a voltage sensor for monitoring the voltage in the cabin body and the mobile cabin.

[0015] The beneficial effects of the present application are as follows: The entire device of the present application can be freely moved, without the need to transport the aircraft to a fixed test site, and is particularly suitable for instant testing on the production line or beside the production line, the closed lightning waveform generating cabin can accommodate the entire machine, avoids the electromagnetic coupling distortion problem caused by traditional segmented testing, and adopts a double-channel redundant discharge design combined with real-time voltage monitoring to completely eliminate the residual charge risk, the shelter door is automatically locked during high-voltage discharge, and the electromagnetic shielding cabin body formed by the overturning protection plate realizes physical isolation between man and machine. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 is a configuration schematic diagram of the mobile aircraft full-machine lightning test device of the present application; Figure 2 is a test circuit principle diagram of the mobile aircraft full-machine lightning test device of the present application; 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; Figure 4 is a side perspective view of the mobile aircraft full-machine lightning test device of the present application; Figure 3 Figure 5 is a flowchart of system initialization of the mobile aircraft full-machine lightning test device of the present application. ​

[0017] In the figure: 1. AC power supply; 2. Charging control system; 3. Step-up transformer; 4. Discharge resistor; 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 resistor; 18. Inductor; 19. Test piece; 100. Cabin; 110. Side panel; 120. Flip protection plate; 130. Test bench; 200. Mobile cabin; 210. Mobile slide rail; 300. External control box; 400. Relay junction box; 500. Grounding terminal; 600. Lightning waveform generation system. DETAILED DESCRIPTION

[0018] The subject matter described herein will now be discussed with reference to exemplary embodiments. It should be understood that these embodiments are discussed solely to enable those skilled in the art to better understand and implement the subject matter described herein, and that the functions and arrangements of the elements discussed may be varied without departing from the scope of this specification. Various examples may omit, substitute, or add various processes or components as needed. In addition, features described with respect to some examples may also be combined in other examples.

[0019] like Figures 1-5 As shown in the figure, the mobile aircraft lightning test device includes: The mobile high-pressure cabin includes a cabin body 100, a mobile cabin 200, a cabin door, a movable slide rail 210, a flip protection plate 120, an external control box 300 and a relay junction box 400; The charging system includes a voltage regulating console, a step-up transformer 3, an AC power supply 1, and a charging switch. The AC power supply 1 is connected in series with the voltage regulating console, the charging control system 2, and the step-up transformer 3. The voltage regulating console adjusts the charging voltage of the lightning waveform generating system 600; The step-up transformer 3 is used to increase the charging voltage. The maximum charging voltage can meet the charging requirements of three lightning waveform generators: direct effect A wave, indirect effect A wave, and indirect effect H wave. The charging control system 2 is used to control the adjustment of the charging voltage to ensure a constant charging current. It can control the charging of three lightning waveform generators: direct effect A wave, indirect effect A wave, and indirect effect H wave. A lightning waveform generation system 600 includes a generator capable of switching between direct effect A-wave, indirect effect A-wave, and indirect effect H-wave; 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 measuring unit, a logic control unit, a measurement and control parameter transmitting unit and a shelter voltage monitoring unit. In one embodiment of the present application, the self-sustaining power supply and the measurement and control system are installed in the mobile monitoring shelter. The residual charge discharging unit comprises a pneumatic high-voltage switch 5 and a discharge resistor 4, which are connected in series to the residual charge discharging end to form a main discharge circuit. The test piece 19 is an aircraft to be tested, which is subjected to the aircraft lightning environment test through the test device. In one embodiment of the present application, the mobile slide rail 210 is installed at the top and bottom ends of the mobile cabin 200, and is used for the mutual sliding of the mobile cabin 200 and the shelter body 100. 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. The mobile cabin 200 and the shelter 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 ); 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. 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. The side panel 110 of the shelter body 100 is a openable structure, the test piece 19 is sent into the shelter body 100 from the side of the shelter body 100, and a test bench 130 is arranged on the inner wall of the bottom end of the shelter body 100. The shelter door is arranged on the outer wall of the side of the shelter body 100 away from the mobile cabin 200. A reversible protection plate 120 is arranged on the top inner wall of the shelter body 100, when the mobile cabin 200 is completely moved out of the shelter body 100, the reversible protection plate 120 is reversibly arranged on the end surface of the mobile cabin 200, which is used for sealing the cavity in the mobile cabin 200, and forms a separate lightning waveform generating cabin. The lightning waveform generating 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 installed on the bearing PCB board, and a diode 6, a variable resistor 17, an inductor 18, a residual charge discharging end and a test piece 19 connecting port are also integrated on the bearing PCB board. The first, second and third capacitor units 11, 13 and 16 are connected in parallel, and the first, second and third switches 7, 8 and 9 are respectively arranged at the front ends of the first, second and third capacitor units 11, 13 and 16; When the first switch 7 is closed, the voltage-boosting transformer 3 and the diode 6 are connected to the first capacitor unit 11, and the A-wave generating end is switched to the direct effect; When the second switch 8 is closed, the voltage-boosting transformer 3 and the diode 6 are connected to the second capacitor unit 13, and the A-wave generating end is switched to the indirect effect; When the third switch 9 is closed, the voltage-boosting transformer 3 and the diode 6 are connected to the third capacitor unit 16, and the H-wave generating end is switched to the indirect effect; In an embodiment of the present application, other wave shape change switching can also be realized by replacing the first, second and third capacitor units 11, 13 and 16; The switch group, the variable resistor 17, the inductor 18 and the test piece 19 are connected in series at the connection ports of the capacitor group assembly; 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; The switch group includes the fourth, fifth and sixth switches 10, 12 and 15, and the fourth, fifth and sixth switches 10, 12 and 15 are respectively connected to the connection ends of the first, second and third capacitor units 11, 13 and 16; When the capacitor group assembly is discharged, the first, second and third switches 7, 8 and 9 are all in the open state; When the fourth switch 10 is closed, the first capacitor unit 11 is connected to the variable resistor 17, the inductor 18 and the test piece 19; When the fifth switch 12 is closed, the second capacitor unit 13 is connected to the variable resistor 17, the inductor 18 and the test piece 19; When the sixth switch 15 is closed, the third capacitor unit 16 is connected to the variable resistor 17, the inductor 18 and the test piece 19; The connection port of the test piece 19 is connected to the test end of the test piece 19 through a cable; The measurement and control system includes a charging system monitoring unit, a lightning wave shape 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; The self-sustaining power supply is used for supplying power to the measurement and control system; The charging system monitoring unit is used for monitoring the charging system; The lightning wave shape generating system monitoring unit is used for monitoring the lightning wave shape generating system 600; The high-voltage switch control unit is used for monitoring the pneumatic high-voltage switch 5 in the residual charge discharge unit; The test piece current-voltage measurement unit is used for measuring the monitoring parameters of the test piece 19; 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, one 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; 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 capacitors in the capacitor group assembly, the residual charge discharge unit adopts a double-channel redundant design, and the discharge failure probability is reduced to 10 -7 ; The residual charge discharge unit further comprises a voltage sensor, the voltage sensor monitors the voltage in the cabin body 100 and the mobile cabin 200, when 50v < voltage < 500v, the standby thyristor discharge is activated, the voltage is reduced to a safe voltage within 10ms, and the shelter door of the mobile high-voltage shelter is mechanically locked; when the voltage > 500v, the main discharge loop is started, and the loop of the pneumatic high-voltage switch 5 and the discharge resistor 4 is started.

[0020] In one embodiment of the present application, the specific steps of the mobile aircraft full-machine lightning test device in the test process are as follows: Step 1, test preparation: open the side openable structure of the cabin body 100, put the aircraft to be tested into the cabin body 100, connect the test piece 19 connection port to the aircraft test end through the cable, manually push and pull the mobile cabin 200 handle, push the mobile cabin 200 into the cabin body 100 along the mobile slide rail 210, and automatically close the protection plate 120 to form a sealed lightning wave shape generating cabin with the end surface of the mobile cabin 200; Step 2, system initialization: as shown in Figure 5 The ground terminal 500 is connected to the main discharge loop (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; Step 3, capacitor charging: Charging loop activation: AC power supply 1→voltage control console→voltage increasing transformer 3→charging switch closed; Waveform capacitor selection: Direct effect A wave: close the first switch 7 (connect the first capacitor unit 11); Indirect effect A wave: close the second switch 8 (connect the second capacitor unit 13); Indirect effect H wave: close the third switch 9 (connect the third capacitor unit 16); Diode 6 prevents current backflow, and the boost transformer 3 outputs 200kV high voltage; Step 4, lightning waveform generation: open the first / second / third switch (cut off the charging circuit), and close the corresponding discharge switch according to the selected waveform: Fourth switch 10 (first capacitor unit 11 discharge); Fifth switch 12 (second capacitor unit 13 discharge); Sixth switch 15 (third capacitor unit 16 discharge); When the switch group is connected, the connecting switch 14 is closed, and the discharge is carried out to the test piece through the capacitor; Waveform generation: capacitor energy → variable resistor 17 → inductor 18 → test piece 19 connection port → test piece 19; The variable resistor 17 adjusts the current rise rate, the inductor 18 shapes the waveform decay characteristics, and the measurement and control system records the aircraft current / voltage response in real time; Step 5, residual charge discharge: when the main discharge circuit fails, the thyristor standby circuit automatically takes over, and the shelter door is forcibly locked when the voltage is greater than 50V; 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 plate 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.

[0021] After using the device, it takes about 45 minutes (including 10 minutes of safety check) from loading the aircraft to completing data recovery, which is 5 times more efficient than traditional fixed test devices.

[0022] 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 are all within the protection of the application.

Claims

1. Mobile aircraft lightning test device, characterized by: include: The mobile high-voltage cabin includes a cabin body, a mobile cabin, mobile slides, and a flip protection plate. The mobile slides are installed on the top and bottom of the mobile cabin and are used for sliding between the mobile cabin and the cabin body. The side panels of the cabin body are openable structures. The test piece is fed into the cabin body from the side. A test bench is provided on the inner wall of the bottom end of the cabin body. The test piece is tested on the test bench. When the mobile cabin is completely moved out of the cabin body, the flip protection plate is flipped and installed on the end face of the mobile cabin. The flip protection plate is used to seal the cavity in the mobile cabin to form an independent lightning waveform generating chamber. The mobile monitoring cabin includes a self-sustaining 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 in the device, and the self-sustaining power supply is used to power the test system; A charging system, comprising a voltage regulating console, a step-up transformer, an AC power supply and a charging switch, wherein the AC power supply is connected in series with the voltage regulating console, the charging control system and the step-up transformer, and the system is used to charge the lightning waveform generating 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 end to form a main discharge circuit; A lightning waveform generating system includes a detachable capacitor group assembly and a carrier PCB board. The capacitor group assembly includes a first capacitor unit, a second capacitor unit, and a third capacitor unit. The capacitor group assembly is mounted on the carrier PCB board. A diode, a variable resistor, an inductor, a residual charge discharge terminal, and a test piece connection port are also integrated on the carrier PCB board. The first capacitor unit, the second capacitor unit, and the third capacitor unit are connected in parallel. A first switch, a second switch, and a third switch are respectively provided at the connection ends of the first capacitor unit, the second capacitor unit, and the third capacitor unit. A switch group, a variable resistor, an inductor, and a test piece connection port are connected in parallel at both ends of the capacitor group assembly. The variable resistor, the inductor, and the test piece connection port are connected in series.

2. The mobile aircraft full-machine lightning test device according to claim 1, characterized in that: A copper mesh shielding layer is provided in the mobile cabin and the cabin body.

3. The mobile aircraft lightning test device according to claim 2, characterized in that: A grounding terminal is provided at the bottom end of the mobile cabin, and the top end of the grounding terminal is connected to the main discharge circuit.

4. The mobile aircraft lightning test device according to claim 3, characterized in that: When the first switch is closed, the boost transformer and the diode are connected to the first capacitor unit, switching to the direct effect A wave generating end; when the second switch is closed, the boost transformer and the diode are connected to the second capacitor unit, switching to the indirect effect A wave generating end; when the third switch is closed, the boost transformer and the diode are connected to the third capacitor unit, switching to the indirect effect H wave generating end.

5. The mobile aircraft lightning test device according to claim 4, characterized in that: The switch group includes 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.

6. The mobile aircraft lightning test device according to claim 5, 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.

7. The mobile aircraft lightning test device according to claim 6, characterized in that: 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 shelter voltage monitoring unit; The charging system monitoring unit is used to monitor the charging system; the lightning waveform generating system monitoring unit is used to monitor the lightning waveform generating 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 measuring 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. Part of the measurement and control parameter transmission unit is installed in the mobile high-voltage cabin, and the other part is installed in the mobile measurement and control cabin. The two parts are connected by cables.

8. The mobile aircraft lightning test device according to claim 7, characterized in that: An external control box and a relay junction box are installed on the outer wall of the mobile cabin. Wires extend from the bottom of the external control box for connecting to the lightning waveform generation system.

9. The mobile aircraft lightning test device according to claim 8, characterized in that: The voltage regulating console adjusts the charging voltage of the lightning waveform generating system. The step-up transformer is used to increase the charging voltage. The maximum charging voltage after the increase can meet the charging requirements of direct effect A wave, indirect effect A wave, and indirect effect H wave.

10. The mobile aircraft lightning test device according to claim 9, characterized in that: The residual charge discharge unit further includes a voltage sensor, which monitors the voltage in the cabin body and the moving cabin.

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