Impulse current generation system for aircraft whole aircraft lightning indirect effects testing

Abstract

The utility model provides a shock current generating system for whole machine thunder and lightning indirect effect test of aircraft, including charging unit, capacitor module, waveform switching unit, waveform forming unit and control unit. The utility model provides a shock current generating system for whole machine thunder and lightning indirect effect test of aircraft, can output 50kA level thunder and lightning indirect effect A wave and D wave of meeting GJB8848 2016 standard requirement, through the setting of waveform forming unit, can accurate control waveform parameter, make the precision of output waveform higher, set up waveform switching unit, through the switching of the connection mode of each capacitor in capacitor module to waveform switching unit, realize the rapid switching of A wave and D wave, improve test efficiency, improved the load capacity of shock current generating system, can work stably under 15uH inductive load, satisfy the requirement of whole machine thunder and lightning indirect effect test of aircraft.

Description

Technical Field

[0001] This utility model relates to the field of aircraft lightning testing technology, and in particular to an impulse current generation system for testing the indirect effects of lightning on the entire aircraft. Background Technology

[0002] With the increasing use of composite materials and microelectronic systems in modern aircraft, the sensitivity of the entire aircraft to lightning strikes is becoming increasingly severe. Testing the indirect lightning effects on the entire aircraft is crucial for ensuring flight safety. However, current research and testing remain focused on the direct lightning effects on aircraft or the indirect lightning effects at the component level; no impulse current generator is currently available to meet the requirements for testing the indirect lightning effects on the entire aircraft.

[0003] Traditional impulse current generators require higher voltages to output currents sufficient for testing the indirect lightning effects of an entire aircraft. This results in a larger main inductance, higher voltage withstand requirements for the capacitors, and a larger overall size, significantly increasing the cost of the impulse current generator. Existing impulse current generators also cannot meet the accuracy requirements for testing the indirect lightning effects of an entire aircraft. Furthermore, existing impulse current generators struggle to achieve stable output under large inductive loads of 10-20μH. Utility Model Content

[0004] The purpose of this invention is to provide an impulse current generation system for testing the indirect effects of lightning on the entire aircraft, which can solve one or more of the problems mentioned above in the prior art.

[0005] According to one aspect of the present invention, an impulse current generation system for testing the indirect effects of lightning on an aircraft is provided, comprising a charging unit, a capacitor module, a waveform switching unit, a waveform forming unit, and a control unit. The charging unit is electrically connected to the capacitor module and can charge the capacitor module. The capacitor module is connected to the waveform switching unit and can switch the connection mode of each capacitor unit in the capacitor module. The capacitor module is electrically connected to the waveform forming unit and can output an impulse current. The control unit is electrically connected to both the waveform switching unit and the waveform forming unit and can control the waveform switching unit to switch the connection mode of each capacitor unit in the capacitor module. The control unit can also control the waveform forming unit to output an impulse current.

[0006] In some embodiments, the capacitor module includes capacitor unit C1, capacitor unit C2, capacitor unit C3 and capacitor unit C4, and capacitor unit C1, capacitor unit C2, capacitor unit C3 and capacitor unit C4 have the same parameters.

[0007] In some implementations, the waveform switching unit enables the capacitor module to switch between a series mode and a series-parallel mode. In the series mode, each capacitor unit in the capacitor module is connected in series sequentially, while in the series-parallel mode, each capacitor unit in the capacitor module is connected in parallel after being connected in pairs in series.

[0008] In some embodiments, the waveform switching unit includes an insulating rod and a driving device connected to the insulating rod. Metal connectors are respectively provided at both ends of the insulating rod. The insulating rod can drive the metal connectors to move between a first connection position and a second connection position under the drive of the driving device. When the metal connector is in the first connection position, the capacitor module is in series-parallel mode, and when the metal connector is in the second connection position, the capacitor module is in series mode.

[0009] In some implementations, the drive unit is a cylinder.

[0010] In some embodiments, the waveform forming unit includes a wavefront resistor R1, a first discharge gap G1, a second discharge gap G2, and a wave tail inductor L1. One end of the capacitor module is sequentially connected to the wavefront resistor R1, the first discharge gap G1, the wave tail inductor L1, and the load under test. The other end of the load under test is connected to the other end of the capacitor module. A second discharge gap G2 is connected in parallel between the first discharge gap G1 and the wave tail inductor L1. The other end of the second discharge gap G2 is connected to the other end of the capacitor module.

[0011] In some implementations, an input unit is also included, which is electrically connected to the control unit.

[0012] This invention provides an impulse current generation system for testing the indirect lightning effect on an aircraft. It can output 50kA-level A-wave and D-wave of the indirect lightning effect, conforming to the requirements of GJB8848-2016 standard. Through the waveform forming unit, waveform parameters can be precisely controlled, resulting in higher accuracy of the output waveform. A waveform switching unit allows for rapid switching between A-wave and D-wave by changing the connection method of each capacitor unit in the capacitor module, improving testing efficiency. The system also enhances its load-bearing capacity, enabling stable operation under a 15uH inductive load, thus meeting the requirements for testing the indirect lightning effect on an aircraft.

[0013] In addition, unless otherwise specified, all aspects of this utility model technical solution can be implemented by conventional means in the field. Attached Figure Description

[0014] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0015] Figure 1 This is a schematic diagram of the impulse current generation system for testing the indirect lightning effect on an aircraft, provided in one embodiment of the present invention.

[0016] Figure 2 The circuit diagram of the waveform forming unit in the impulse current generation system for testing the indirect lightning effect on an aircraft, as provided in an embodiment of this utility model.

[0017] Figure 3 This is a schematic diagram of a waveform switching unit located at the first connection position in an impulse current generation system for testing the indirect effects of lightning on an aircraft, provided as an embodiment of the present invention.

[0018] Figure 4 This is a schematic diagram of a waveform switching unit located at the second connection position in an impulse current generation system for testing the indirect effects of lightning on an aircraft, provided as an embodiment of the present invention. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0020] Example: In this embodiment, please refer to the appendix to the specification. Figure 1-4 It provides an impulse current generation system for testing the indirect effects of lightning on the entire aircraft, including a charging unit 1, a capacitor module 2, a waveform switching unit 3, a waveform forming unit 4, a control unit 5, and an input unit 6.

[0021] The charging unit 1 is electrically connected to the capacitor module 2, and the charging unit 1 can charge the capacitor module 2. Specifically, the charging unit 1 can be a power supply or a battery. When the charging unit 1 is a battery, it can be connected to a power supply for charging, or it can charge the capacitors in the capacitor module 2.

[0022] The capacitor module 2 is connected to the waveform switching unit 3. The waveform switching unit 3 can switch the connection mode of each capacitor in the capacitor module 2. The capacitor module 2 is electrically connected to the waveform forming unit 4.

[0023] Waveform forming unit 4 can output inrush current. Waveform forming unit 4 is used to connect to the load under test, which is the entire aircraft. Specifically, waveform forming unit 4 can generate lightning indirect effect A-wave and D-wave current waveforms. A-wave refers to a current waveform with a wavefront time Tf = 6.4μs and a half-peak time Tt = 69μs, and D-wave refers to a current waveform with a wavefront time Tf = 3.18μs and a half-peak time Tt = 34.5μs.

[0024] Control unit 5 is electrically connected to waveform switching unit 3 and waveform forming unit 4 respectively. Control unit 5 can control waveform switching unit 3 to switch the connection mode of each capacitor in capacitor module 2. Control unit 5 can control waveform forming unit 4 to output inrush current. Input unit 6 is electrically connected to control unit 5. Operators can input the current waveform required for testing through input unit 6.

[0025] Reference manual attached Figure 2 The diagram shows a circuit diagram of a waveform switching unit. The waveform forming unit 4 may include a wavefront resistor R1, a first discharge gap G1, a second discharge gap G2, and a wave tail inductor L1. One end of the capacitor module 2 is connected in sequence to the wavefront resistor R1, the first discharge gap G1, the wave tail inductor L1, and the load under test. The other end of the load under test is connected to the other end of the capacitor module 2. The second discharge gap G2 is connected in parallel between the first discharge gap G1 and the wave tail inductor L1. The other end of the second discharge gap G2 is connected to the other end of the capacitor module 2.

[0026] Capacitor module 2, wavefront resistor R1, first discharge gap G1, wavetail inductor L1, and load constitute a wavefront forming circuit, while wavetail inductor L1, second discharge gap G2, and load constitute a wavetail forming circuit. Thus, by setting the first discharge gap G1 and the second discharge gap G2, the first discharge gap G1 conducts to form the wavefront, and the second discharge gap G2 conducts when the current reaches its peak value. After the second discharge gap G2 conducts, the circuit switches from the wavefront forming circuit to the wavetail forming circuit to form the wavetail, making the wavefront forming circuit and the wavetail forming circuit independent of each other.

[0027] The control unit 5 can control the conduction time of the first discharge gap G1 and the second discharge gap G2. Thus, by precisely controlling the conduction time of the first discharge gap G1 and the second discharge gap G2, a higher precision A-wave or D-wave waveform can be output.

[0028] The second discharge gap G2 can be a Crowbar switch.

[0029] In an optional embodiment, the capacitor module 2 includes capacitor unit C1, capacitor unit C2, capacitor unit C3 and capacitor unit C4, and the parameters of capacitor unit C1, capacitor unit C2, capacitor unit C3 and capacitor unit C4 are the same.

[0030] The specifications of each capacitor unit in capacitor module 2 can be 100kV / 2uF.

[0031] The waveform switching unit 3 enables the capacitor module 2 to switch between series mode and series-parallel mode.

[0032] In the series mode of capacitor module 2, each capacitor in capacitor module 2 is connected in series sequentially. In this case, waveform forming unit 4 outputs D wave. In the series-parallel mode of capacitor module 2, each capacitor in capacitor module 2 is connected in series in pairs and then in parallel. In this case, waveform forming unit 4 outputs A wave.

[0033] In optional embodiments, refer to the appendix to the specification. Figure 3 Included with instruction manual Figure 4 The diagram shows a schematic of the waveform switching unit 3. The capacitor module 2 includes four identical capacitor units. One end of capacitor unit C1 is electrically connected to the output terminal HV+ of capacitor module 2. Capacitor units C1, C2, C3, and C4 are connected sequentially. The end of capacitor unit C2 connected to capacitor unit C3 is closably electrically connected to the output terminal HV- of capacitor module 2. The end of capacitor unit C4 not connected to capacitor unit C3 is closably electrically connected to both the output terminals HV+ and HV- of capacitor module 2.

[0034] The waveform switching unit 3 includes an insulating rod 31 and a driving device connected to the insulating rod. Metal connectors 32 are respectively provided at both ends of the insulating rod 31. The insulating rod 31 can drive the metal connectors 32 to move between the first connection position and the second connection position under the drive of the driving device.

[0035] When the metal connector 32 is in the first connection position, the capacitor unit C4 is connected to the output terminal HV+ of the capacitor module 2, and the end of the capacitor unit C2 and capacitor unit C3 is connected to the output terminal HV- of the capacitor module 2. The capacitor module 2 is in series-parallel mode, that is, the capacitor unit C1 and capacitor unit C2 are connected in series and then connected in parallel with the series-connected capacitor unit C3 and capacitor unit C4. At this time, the waveform forming unit 4 outputs wave A.

[0036] When the metal connector 32 is in the second connection position, the capacitor unit C4 is connected to the output terminal HV- of the capacitor module 2. The capacitor module 2 is in series mode, that is, the capacitor units C1, C2, C3 and C4 are connected in series. At this time, the waveform forming unit 4 outputs the D wave.

[0037] Therefore, by controlling the waveform switching unit 3, the control of each capacitor unit in the capacitor module 2 is realized, thereby controlling the waveform forming unit 4 to output A wave or D wave to meet the test requirements.

[0038] When waveform forming unit 4 outputs wave A, the operating parameters of the impulse current generating system are: capacitor 1uF, inductor 15uH, resistor 0.5Ω, and charging voltage 200kV.

[0039] When waveform forming unit 4 outputs D wave, the system parameters of the impulse current generating system are: capacitor 0.25uF, inductor 15uH, resistor 1Ω, and charging voltage 400kV.

[0040] In an optional embodiment, a cylinder can be used as the driving device. This reduces the switching time between A-wave and D-wave to 5 seconds, eliminating the need for manual switching and improving testing efficiency and safety.

[0041] The impulse current generation system provided by this utility model for testing the indirect effects of lightning on the entire aircraft allows the operator to input the desired waveform (A-wave or D-wave) through the input unit 6. The control unit 5 then controls the waveform switching unit 3 to switch the connection mode of each capacitor unit in the capacitor module 2 according to the operator's input, so that the connection mode corresponds to the target waveform. The charging unit 1 charges the capacitor module 2 to the set voltage, and the first discharge gap G1 is turned on to form the wavefront. When the current reaches the peak value, the second discharge gap G2 is turned on to form the wave tail, thus obtaining the target waveform.

[0042] This invention provides an impulse current generation system for testing the indirect lightning effect on an aircraft. It can output 50kA-level A-wave and D-wave of the indirect lightning effect, conforming to the requirements of GJB8848-2016 standard. Through the waveform forming unit, waveform parameters can be precisely controlled, resulting in higher accuracy of the output waveform. A waveform switching unit allows for rapid switching between A-wave and D-wave by changing the connection method of each capacitor in the capacitor module, improving testing efficiency. The system also enhances its load-bearing capacity, enabling stable operation under a 15uH inductive load, thus meeting the requirements for testing the indirect lightning effect on an aircraft.

[0043] The above description is only an optional embodiment of this utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this utility model, and these improvements and modifications should also be considered within the protection scope of this utility model.

Claims

1. An impulse current generation system for testing the indirect effects of lightning on an aircraft, characterized in that, It includes a charging unit (1), a capacitor module (2), a waveform switching unit (3), a waveform forming unit (4), and a control unit (5). The charging unit (1) is electrically connected to the capacitor module (2), and the charging unit (1) can charge the capacitor module (2). The capacitor module (2) is connected to the waveform switching unit (3), which can switch the connection mode of each capacitor in the capacitor module (2). The capacitor module (2) is electrically connected to the waveform forming unit (4). The waveform forming unit (4) is capable of outputting an impulse current. The control unit (5) is electrically connected to the waveform switching unit (3) and the waveform forming unit (4) respectively. The control unit (5) can control the waveform switching unit (3) to switch the connection mode of each capacitor unit in the capacitor module (2). The control unit (5) can control the waveform forming unit (4) to output the impulse current.

2. The impulse current generation system for testing the indirect effects of lightning on an aircraft as described in claim 1, characterized in that, The capacitor module (2) includes capacitor unit C1, capacitor unit C2, capacitor unit C3 and capacitor unit C4, and the parameters of capacitor unit C1, capacitor unit C2, capacitor unit C3 and capacitor unit C4 are the same.

3. The impulse current generation system for testing the indirect effects of lightning on an aircraft as described in claim 1, characterized in that, The waveform switching unit (3) enables the capacitor module (2) to switch between series mode and series-parallel mode. The capacitor module (2) is connected in series in that each capacitor unit in the capacitor module (2) is connected in series in sequence. The series-parallel connection mode of the capacitor module (2) is that each capacitor unit in the capacitor module (2) is connected in series and then in parallel.

4. The impulse current generation system for testing the indirect effects of lightning on an aircraft as described in claim 1, characterized in that, The waveform switching unit (3) includes an insulating rod (31) and a driving device connected to the insulating rod. Metal connectors (32) are respectively provided at both ends of the insulating rod (31). The insulating rod (31) can drive the metal connector (32) to move between the first connection position and the second connection position under the drive of the driving device. When the metal connector (32) is in the first connection position, the capacitor module (2) is in series-parallel connection mode. When the metal connector (32) is in the second connection position, the capacitor module (2) is in series mode.

5. The impulse current generation system for testing the indirect effects of lightning on an aircraft as described in claim 4, characterized in that, The driving device is a cylinder.

6. The impulse current generation system for testing the indirect effects of lightning on an aircraft as described in claim 1, characterized in that, The waveform forming unit (4) includes a wavefront resistor R1, a first discharge gap G1, a second discharge gap G2, and a wave tail inductor L1. One end of the capacitor module (2) is connected in sequence to the wavefront resistor R1, the first discharge gap G1, the wave tail inductor L1, and the load under test. The other end of the load under test is connected to the other end of the capacitor module (2). A second discharge gap G2 is connected in parallel between the first discharge gap G1 and the wave tail inductor L1, and the other end of the second discharge gap G2 is connected to the other end of the capacitor module (2).

7. The impulse current generation system for testing the indirect effects of lightning on an aircraft as described in claim 1, characterized in that, It also includes an input unit (6), which is electrically connected to the control unit (5).

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