Aircraft lightning indirect effect and HIRF conduction sensitivity test device and method

Abstract

The present invention relates to the technical field of aircraft lightning protection test, and discloses an aircraft lightning indirect effect and HIRF conduction sensitivity test device and method, the device includes a test equipment (EUT), accompanying test monitoring equipment, auxiliary equipment, HIRF injection probe, lightning injection probe, monitoring probe, lightning signal isolator, HIRF conduction test system, lightning indirect effect test system and digital oscilloscope. In view of the electromagnetic environmental safety hazards caused by separate certification and independent rectification of lightning and HIRF airworthiness of civil aircraft, the present invention can simultaneously carry out lightning indirect effect and HIRF conduction sensitivity tests on aircraft electronic and electrical systems, verify the lightning and HIRF comprehensive protection performance of aircraft electronic and electrical systems, and effectively reduce the safety hazards of the electromagnetic environment. The lightning indirect effect and HIRF conduction sensitivity test device is simple to construct and easy to implement in engineering, and can also be used for lightning and HIRF protection performance verification tests of other aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft lightning protection test, and more specifically, to an aircraft lightning indirect effect and HIRF conduction sensitivity test device and method. Background Art

[0002] On average, about 8 million lightning strikes occur on Earth every day, and the risk of lightning strikes seriously affects the safety of aircraft. The hazards of lightning to equipment are divided into direct effects and indirect effects. The direct effect of lightning refers to the breakdown, melting, structural deformation, etc. caused by lightning directly hitting the equipment. The indirect effect of lightning refers to the interaction between lightning and aircraft, which causes a transient electromagnetic environment inside the fuselage and affects or damages the electronic and electrical systems on the aircraft. With the widespread deployment of high-power electromagnetic radiation equipment such as communication base stations, satellite ground stations, radars, and broadcasts, and the extensive use of various electronic radiation equipment, the high-intensity radiation field (HIRF) environment has become extremely complex. In addition, on the one hand, a large proportion of aircraft fuselage structures use composite materials with poor electromagnetic shielding performance; on the other hand, a large number of electronic and electrical systems replace traditional mechanical control systems, making the HIRF sensitivity of aircraft electronic and electrical systems more prominent.

[0003] In the process of aircraft electronic and electrical system development, cable bundle lightning transient simulation and cable bundle sensitivity test are important indicators for the early development of the system and cable bundle, which are of great value for improving the system's lightning resistance and guiding the lightning resistance design of the cable bundle. The current lightning transient simulation technology at home and abroad is mainly based on the equivalent telegraph method. This method simulates the system lightning response as a reference circuit and compares the cable bundle with it to determine whether the cable bundle meets the requirements. However, the current lightning transient sensitivity test is difficult to reflect the overall lightning resistance performance of the cable bundle due to the limitations of system scale, test site and other objective factors; the high-intensity radiated field (HIRF) sensitivity test is a high-frequency compatibility test method currently widely used internationally, which mainly evaluates the sensitivity of aircraft electronic and electrical systems to high-frequency interference energy. This test can effectively discover the propagation path of electromagnetic interference inside the system, which is of great significance to the high-frequency anti-interference design of the system. At present, both domestic and foreign countries use the dual-conduction source independent test method to carry out HIRF sensitivity tests, which can effectively discover the internal conduction coupling path of the system.

[0004] The lightning and HIRF airworthiness of aircraft electronic and electrical systems are independently certified. The impact of lightning and HIRF effects on the cross-frequency band after rectification is unknown, and it is difficult to find problems through independent verification. However, the sensitivity research on lightning indirect effects and HIRF conduction effects at home and abroad is independent of each other, and comprehensive effect test verification research has not been carried out. The comprehensive protection performance of lightning and HIRF effects of aircraft electronic and electrical systems has not been tested, resulting in potential electromagnetic safety hazards. Summary of the invention

[0005] The present invention provides an aircraft lightning indirect effect and HIRF conduction sensitivity test device and method, and aims to solve the problem that in the existing test scheme, the lightning and HIRF airworthiness certification of the aircraft electronic and electrical system is carried out independently, and the impact of lightning and HIRF effects on the cross-frequency band after rectification is unknown, and it is difficult to find problems through independent verification. However, at present, the sensitivity research on lightning indirect effect and HIRF conduction effect at home and abroad is independent of each other, and no comprehensive effect test verification research has been carried out, and the comprehensive protection performance of lightning and HIRF effects of aircraft electronic and electrical systems has not been tested, resulting in potential electromagnetic safety hazards.

[0006] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: an aircraft lightning indirect effect and HIRF conduction sensitivity test device, comprising a test device, a test monitoring device, a cable bundle, a HIRF injection probe, a lightning injection probe, a monitoring probe, a lightning signal isolator, a HIRF conduction test system, a lightning indirect effect test system and a digital oscilloscope, the test device and the auxiliary device are connected through the cable bundle, the lightning injection probe, the HIRF injection probe and the monitoring probe are sequentially arranged on the cable bundle in the direction from the test device to the auxiliary device, a lightning signal injection channel is arranged between the lightning indirect effect test system and the lightning injection probe, a HIRF signal injection channel is arranged between the HIRF conduction test system and the HIRF injection probe, and a monitoring signal transmission channel is arranged between the digital oscilloscope and the monitoring probe.

[0007] In a preferred embodiment, a lightning signal isolator is provided on the HIRF signal injection channel between the HIRF conduction test system and the HIRF injection probe.

[0008] In a preferred embodiment, the lightning signal output by the lightning indirect effect test system is coupled into the cable bundle through a lightning injection probe to achieve coupled injection of the lightning signal, and the HIRF test signal output by the HIRF conduction test system is coupled into the cable bundle through a HIRF injection probe to achieve conducted injection of the HIRF test signal.

[0009] In a preferred embodiment, the test device also includes a test operating table, and the lightning injection probe, the HIRF injection probe and the monitoring probe are all installed on the test operating table. The cable bundle passes through the monitoring probe, the HIRF injection probe and the lightning injection probe. A fixed frame assembly is also installed on the test operating table, and the fixed frame assembly includes a first fixed frame. The first fixed frame is provided with at least two groups, and the two groups of first fixed frames are respectively arranged at the two ends of the area where the cable bundle is located on the test operating table. The first fixed frame is a cylindrical structure, and the cable bundle passes through the first fixed frame. A cable clamping structure is provided on the first fixed frame, and the cable clamping structure is used to clamp and fix the cable bundle. A first mounting seat is provided at the bottom of the first fixed frame, and the first fixed frame is slidably connected to the first mounting seat through a slide rail. A screw rod structure is rotatably installed in the first mounting seat, and a slider structure threadedly matched with the screw rod structure is provided at the bottom of the first fixed frame.

[0010] In a preferred embodiment, the cable clamping structure includes a hoop, which is rotatably mounted on the first fixing frame, a rubber pad structure is arranged on the inner side of the hoop, and a locking member is arranged between the hoop and the first fixing frame.

[0011] In a preferred embodiment, the fixing frame assembly further includes a plurality of sets of second fixing frames, which are mounted on the test operating table via second mounting seats, are cylindrical structures, and are also provided with cable clamping structures.

[0012] In a preferred embodiment, the cable clamping structure includes a swivel and a slip ring, the swivel is rotatably mounted on one end of the second fixed frame, the slip ring is slidably mounted on the other end of the second fixed frame, a guide structure is arranged between the slip ring and the second fixed frame, a binding rope is arranged between the second fixed frame and the slip ring, and both ends of the binding rope are fixedly connected to the second fixed frame and the slip ring respectively.

[0013] In a preferred embodiment, a first worm gear is fixedly installed on the outside of the swivel, a first worm that cooperates with the first worm gear is rotatably installed on the second fixed frame, a slide groove that cooperates with the guide structure is provided on the second fixed frame, an elastic reset member is provided between the guide structure and the slide groove, and the elastic reset member is used to provide an elastic force to the sliding ring away from the swivel. The restraining rope is an elastic rope structure, and the external sliding sleeve of the restraining rope is connected with multiple sleeve structures.

[0014] In a preferred embodiment, a plurality of groups of mounting sockets are arrayed on the test operating table, and mounting pins are provided at the bottom of the first mounting seat, the second mounting seat, the lightning injection probe, the HIRF injection probe and the monitoring probe, and the mounting pins are used to be plugged into the mounting sockets. The second fixing frame is rotatably connected to the second mounting seat, a second worm gear is provided at the bottom of the second fixing frame, a second worm is rotatably installed in the second mounting seat, and the second worm and the second worm gear cooperate with each other.

[0015] The test method for aircraft lightning indirect effects and HIRF conducted sensitivity includes the following steps:

[0016] Step 1: Build the test platform according to the requirements of the test layout diagram;

[0017] Step 2: Determine the frequency bandwidth, level and other parameters for the HIRF conduction sensitivity test, and perform HIRF conduction sensitivity test calibration;

[0018] Step 3: Determine the parameters such as the lightning waveform, level and quantity for the lightning indirect effect test, and verify the performance of the transient signal generator;

[0019] Step 4: Select the working mode of the device under test;

[0020] Step 5: Select the cable bundle to be tested;

[0021] Step 6: Set the initial frequency of the HIRF conducted sensitivity test and conduct the test. During the dwell time at each HIRF test frequency point, conduct a lightning indirect effect test on the target cable bundle at the same time. Observe and record the conditions of the equipment under the combined effects of lightning and HIRF through the accompanying test monitoring equipment.

[0022] Step 7: Change the frequency of the HIRF conduction sensitivity test, and repeat step 6 until the end frequency of the HIRF conduction sensitivity test is reached;

[0023] Step 8. Replace the new test cable bundle and repeat steps 5, 6 and 7 to complete the test of all cable bundles;

[0024] Step 9. Select a new working mode for the device under test and repeat steps 4, 5, 6, 7 and 8 to complete the test of all working modes.

[0025] Step 10. Use the test monitoring equipment to observe and record the conditions of the equipment under the combined effects of lightning and HIRF, and complete the test verification of the comprehensive lightning and HIRF protection performance of the aircraft's electronic and electrical systems.

[0026] The beneficial effects of the present invention are as follows: compared with the scheme of verifying the protection of lightning or HIRF separately, the present invention can simultaneously verify the comprehensive protection performance of lightning and HIRF, improve the test efficiency, and effectively reduce the safety hazards of the electromagnetic environment; and the test device is simple to construct and easy to implement in engineering, meets the requirements of relevant test standards, verifies the comprehensive protection performance of lightning and HIRF of the aircraft electronic and electrical system, and can also be used for lightning and HIRF protection performance verification tests of other aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is a diagram of the test arrangement of the present invention.

[0028] Figure 2 The present invention is a flow chart of the test method.

[0029] Figure 3 It is a schematic diagram of the test platform of the present invention.

[0030] Figure 4 It is a schematic diagram of the overall structure of the first fixing frame of the present invention.

[0031] Figure 5 It is a schematic diagram of the overall structure of the second fixing frame of the present invention.

[0032] Figure 6 It is a schematic diagram of the supporting state of the cable bundle when the restraining rope is tightened after the swivel of the present invention rotates.

[0033] Figure 7 FIG. 4 is an external view of the second fixing bracket of the present invention.

[0034] Figure 8 This is a diagram of the combined use state of the second fixing bracket of the present invention.

[0035] Fig. 9 For the present invention Figure 5 A-section structure enlarged view.

[0036] Fig.10 It is a schematic diagram of the overall structure of the improved second fixing frame of the present invention.

[0037] Fig.11 It is a side view of the improved second fixing frame of the present invention.

[0038] Fig.12 It is a schematic diagram of the arrangement state of cables in other postures on the test platform of the present invention.

[0039] Fig.13 This is a schematic diagram of the structure after a sleeve structure is added to the restraining rope of the present invention.

[0040] Fig.14 This is a schematic diagram of the sleeve structure after the binding rope of the present invention is tightly pressed onto the cable bundle.

[0041] In the figure: 1. Test equipment; 11. Auxiliary equipment; 12. Cable bundle; 13. Accompanying test monitoring equipment; 2. Lightning indirect effect test system; 21. Lightning injection probe; 3. HIRF conduction test system; 31. HIRF injection probe; 32. Lightning signal isolator; 4. Digital oscilloscope; 41. Monitoring probe; 5. Test operation table; 51. Mounting socket; 6. Fixed frame assembly; 61. First fixed frame; 611. First mounting seat; 612. Screw structure; 62. Second fixed frame; 621. Second mounting seat; 622. Mounting column; 623. Second worm gear; 624. Second worm; 7. Cable clamping structure; 71. Hoop; 711. Locking member; 72. Swivel; 721. First worm gear; 722. First worm; 73. Slip ring; 731. Guide structure; 732. Elastic reset member; 74. Binding rope; 75. Casing structure. DETAILED DESCRIPTION

[0042] The subject matter described herein will now be discussed with reference to example embodiments. It should be understood that the discussion of these embodiments is only to enable those skilled in the art to better understand and implement the subject matter described herein, and the functions and arrangements of the elements discussed may be changed without departing from the scope of protection of the contents of this specification. Each example may omit, replace or add various processes or components as needed. In addition, the features described relative to some examples may also be combined in other examples.

[0043] Refer to the instruction manual Figures 1 to 14 The aircraft lightning indirect effect and HIRF conduction sensitivity test device includes a test equipment 1 (i.e., EUT, the EUT mentioned in this article refers to the test equipment), a test monitoring device 13, a cable bundle 12, a HIRF injection probe 31, a lightning injection probe 21, a monitoring probe 41, a lightning signal isolator 32, a HIRF conduction test system 3, a lightning indirect effect test system 2 and a digital oscilloscope 4; the test equipment 1 and the auxiliary equipment 11 are connected through the cable bundle 12, the lightning injection probe 21, the HIRF injection probe 31 and the monitoring probe 41 are sequentially arranged on the cable bundle 12 along the direction from the test equipment 1 to the auxiliary equipment 11, a lightning signal injection channel is arranged between the lightning indirect effect test system 2 and the lightning injection probe 21, a HIRF signal injection channel is arranged between the HIRF conduction test system 3 and the HIRF injection probe 31, a monitoring signal transmission channel is arranged between the digital oscilloscope 4 and the monitoring probe 41, and the test monitoring device 13 is used to observe and record the situation of the test equipment 1 under the combined action of lightning and HIRF.

[0044] In order to prevent the lightning signal from impacting and damaging the HIRF conduction test system 3, a lightning signal isolator 32 is provided on the HIRF signal injection channel for protection.

[0045] In the present invention, the lightning signal output by the lightning indirect effect test system 2 is coupled to the cable bundle 12 through the lightning injection probe 21, so as to realize the coupling injection of the lightning signal; the HIRF test signal output by the HIRF conduction test system 3 is coupled to the cable bundle 12 through the lightning signal isolator 32 and the HIRF injection probe 31, so as to realize the conduction injection of the HIRF test signal. Among them, the frequency bandwidth, dynamic range and power capacity of the monitoring probe meet the requirements of the lightning indirect effect test and the HIRF conduction test at the same time.

[0046] In this embodiment, a thinner and smaller cable bundle 12 can be tested. During the test, the distance between each device is relatively small. For example, the monitoring probe 41 can be 5 cm away from the test device 1, the HIRF injection probe 31 and the monitoring probe 41 can be 5 cm apart, and the lightning injection probe 21 and the HIRF injection probe 31 can be 5-10 cm apart.

[0047] Based on the above implementation mode, during the specific test, the test equipment 1, the accompanying test monitoring equipment 13, the auxiliary equipment 11, the HIRF injection probe 31, the lightning injection probe 21, the monitoring probe 41, the lightning signal isolator 32, the HIRF conduction test system 3, the lightning indirect effect test system 2 and the digital oscilloscope 4 and other required test devices are arranged according to the instructions. Figure 1 Arrange as shown.

[0048] In addition, a lightning signal isolator 32 is connected between the HIRF injection probe 31 and the HIRF conduction test system 3 to protect the HIRF conduction test system 3. At the same time, the current injection cable of the lightning indirect effect test should be well grounded, shielded and other protections, and a unidirectional circuit device should be set on the circuit. Secondly, determine the test frequency band (10kHz∼400MHz) and select a suitable monitoring probe 41. The test equipment 1 should be arranged on a grounding plate (set on the test operating table 5), and the rest of the configuration should follow the general test requirements.

[0049] The present invention can not only independently carry out a lightning indirect effect test and a HIRF conduction sensitivity test on the cable bundle 12 of the aircraft electronic and electrical system, but also carry out a comprehensive lightning indirect effect and HIRF conduction sensitivity test on the cable bundle 12 of the aircraft electronic and electrical system as a whole.

[0050] In the above embodiment, the test is performed with a relatively thin and small cable bundle 12. However, in reality, there are a large number of cable bundles 12 composed of multiple wire bundles inside the aircraft. The cable bundle 12 finally formed is relatively thick and long. At this time, the distance between the devices is also increased accordingly. Among them, some probes are annular structures, such as the lightning injection probe 21 (refer to the large current injection probe or large current injection clamp) and the monitoring probe 41 (such as a clamp, a ring, etc. structure, which needs to surround the cable and achieve corresponding detection and operation by means of coil coupling). For the relatively thin and small cable bundle 12, the cable bundle 12 spans a small span during the test. , it is light in weight and not easy to sag, and can be relatively suspended in the circular structure. The device has good working effect and little impact during actual operation. However, for the longer and thicker cable bundle 12, its cross span is large. When it passes through the above-mentioned circular device, it is easy to sag, deviate from the center of the circular structure, and stick to the inner wall of the circular structure. In actual use, the coupling effect is relatively poor, and accidents are prone to occur during the test process, especially when the lightning injection probe 21 is working, the relative current is large, and the impact is large. The close contact between the cable bundle 12 and the lightning injection probe 21 can easily cause damage to the cable bundle 12.

[0051] For this purpose, refer to the instructions for Figure 3 and Figure 4 , this embodiment also provides the following technical solutions, specifically, the test device also includes a test operation table 5, the test operation table 5 is provided with a grounding plate, the lightning injection probe 21, the HIRF injection probe 31 and the monitoring probe 41 are all installed on the test operation table 5, the cable bundle 12 passes through the monitoring probe 41, the HIRF injection probe 31 and the lightning injection probe 21 (other equipment required for the test can be set inside the test operation table 5, and can also be set at other positions), the test operation table 5 is also installed with a fixing frame assembly 6, the fixing frame assembly 6 includes a first fixing frame 61, the first fixing frame 61 is provided with at least two groups, the two groups of first fixing frames 61 are respectively arranged at both ends of the area where the cable bundle 12 is located on the test operation table 5, the first fixing frame 61 is a cylindrical structure, the cable bundle 12 passes through the first fixing frame 61, the first fixing frame 61 is provided with a cable clamping structure 7, and the cable clamping structure 7 is used to clamp and fix the cable bundle 12;

[0052] A first mounting seat 611 is provided at the bottom of the first fixing frame 61. The first fixing frame 61 is slidably connected to the first mounting seat 611 through a slide rail. A screw rod structure 612 is rotatably installed in the first mounting seat 611. A slider structure threadably matched with the screw rod structure 612 is provided at the bottom of the first fixing frame 61.

[0053] During actual use, the first mounting seat 611 is installed on the test operating table 5. After assembling the cable bundle 12 and other equipment, the cable bundle 12 is clamped and fixed by the cable clamping structure 7. After fixation, the screw structure 612 is rotated to stretch the cable bundle 12, thereby tightening the cable bundle 12 as a whole, so that the cable bundle 12 is in a suspended state at the center position of the circular structure, thereby improving the coupling effect and improving the safety of the test.

[0054] For further information, please refer to the attached manual. Figure 4 The cable clamping structure 7 includes a hoop 71, which is rotatably mounted on the first fixing frame 61. A rubber pad structure is provided on the inner side of the hoop 71, and a locking member 711 is provided between the hoop 71 and the first fixing frame 61. When in use, the hoop 71 is turned over to press the cable bundle 12 tightly, and the locking member 711 is used to lock the hoop 71 to achieve the fastening of the cable bundle 12.

[0055] Refer to the instruction manual Figure 8 Although providing first fixing frames 61 at both ends of the cable bundle 12 to straighten the cable bundle 12 can improve the straightening effect of the cable bundle 12, when the first fixing frame 61 is far away from the detection equipment, or the adjacent probes are far apart, the cable bundle 12 still has a relatively serious sagging phenomenon. For this reason, the present invention also arranges multiple groups of second fixing frames 62 on the test operating table 5, and the second fixing frames 62 are installed on the test operating table 5 through second mounting seats 621. The second fixing frames 62 are cylindrical structures, and a cable clamping structure 7 is arranged in the second fixing frames 62. The cable clamping structure 7 is used to clamp and fix the cable bundle 12. In actual use, the second fixing frames 62 can be arranged at appropriate positions, that is, on both sides of the corresponding probes, and the cable bundle 12 is auxiliary supported by the second fixing frames 62 to reduce the sagging phenomenon of the cable bundle 12.

[0056] Further, in the above embodiment, if the cable bundle 12 is fixed by the hoop 71, a large shielding will be formed on the surface of the cable bundle 12, thereby affecting the distribution of the electric field on the surface of the cable bundle 12, which is not conducive to the cable bundle 12 being in a suspended state. For this reason, the present embodiment also provides another cable clamping structure 7, specifically, refer to the attached specification. Figure 5 The cable clamping structure 7 includes a swivel 72 and a slip ring 73. The swivel 72 is rotatably mounted on one end of the second fixed frame 62, and the slip ring 73 is slidably mounted on the other end of the second fixed frame 62. A guide structure 731 is provided between the slip ring 73 and the second fixed frame 62 for guiding the sliding of the slip ring 73 to prevent the slip ring 73 from rotating. A binding rope 74 is provided between the second fixed frame 62 and the slip ring 73. Both ends of the binding rope 74 are fixedly connected to the second fixed frame 62 and the slip ring 73 respectively. Multiple groups of binding ropes 74 can be provided and evenly spaced along the circumferential direction.

[0057] In actual use, the cable bundle 12 is passed through the second fixing frame 62, and then the swivel 72 is rotated. At this time, the rotation of the swivel 72 will cause the various binding ropes 74 to twist. During the twisting process, the binding ropes 74 will be close to the outer wall of the cable bundle 12 and form a tangled shape. The center of twisting of each binding rope 74 is on the central axis of the second fixing frame 62. Therefore, the binding ropes 74 twisted and wound around the cable bundle 12 can support the cable bundle 12 to form a suspended state, and the binding ropes 74 themselves have less coverage of the cable bundle 12, have less shielding effect on the cable bundle 12, and are not easy to cause pressure damage to the cable bundle 12.

[0058] Among them, refer to the instructions attached Figure 6 Since the torsion of the binding rope 74 in space will drive the binding rope 74 to move forward, when the second fixing frame 62 is used, the swivel 72 can be set away from the probe, especially when the two groups of second fixing frames 62 are set in pairs, the swivels 72 of the two groups of second fixing frames 62 are set away from each other. Therefore, when the position of the swivel 72 cannot be changed, the binding rope 74 twists and wraps around the cable bundle 12, while also providing a certain pulling force to the cable bundle 12, thereby making the cable bundle 12 passing through the corresponding probe straighter, and since the clamping and fixing of the binding rope 74 can make the cable bundle 12 relatively suspended in the second fixing frame 62, the second fixing frame 62 has less influence on the cable bundle 12 and can be set closer to the probe to provide more stable support.

[0059] In the above embodiment, after rotating the rotating ring 72, the rotating ring 72 needs to be fixed. Therefore, the rotating ring 72 can be fixed by using a corresponding screw structure (insulated type), or other methods can be used. For example, refer to the attached manual. Fig.10 The first worm gear 721 is fixedly installed on the outside of the swivel 72, and the first worm 722 cooperating with the first worm gear 721 is rotatably installed on the second fixing frame 62. Then, the swivel 72 can be controlled to rotate by rotating the first worm 722, and self-locking is formed, thereby ensuring the stability of the device, and the rotation of the swivel 72 is more labor-saving, thereby providing greater pulling force to the cable bundle 12. In order to facilitate the subsequent use of the device, refer to the attached manual Fig. 9 A slide groove cooperating with the guide structure 731 is provided on the second fixed frame 62, and an elastic reset member 732 is provided between the guide structure 731 and the slide groove. The elastic reset member 732 is used to provide an elastic force to the slip ring 73 away from the swivel 72, such as an elastic rope. When the use is finished and the swivel 72 is rotated in the reverse direction, the slip ring 73 can be automatically reset for the next use.

[0060] Furthermore, since the binding rope 74 is twisted and wrapped around the outside of the cable bundle 12, relative slippage will occur. If the slippage is large, it is easy to scratch the wrapping structure outside the cable bundle 12. For this reason, refer to the attached manual. Fig.13 and 14 The binding rope 74 is a high-strength elastic rope structure, and the outer sliding sleeve of the binding rope 74 is connected with multiple sleeve structures 75. In actual use, after the binding rope 74 is twisted to fit the cable bundle 12, the tightening of the binding rope 74 can slide relative to the sleeve structure 75, and the sleeve structure 75 is close to the outside of the cable bundle 12, thereby reducing the relative sliding damage between the binding rope 74 and the cable bundle 12, and the sleeve structure 75 forms a relative protrusion on the binding rope 74, especially after the binding rope 74 is wound and tilted, it is arranged on the outside of the cable bundle 12 close to the vertical direction of the length of the cable bundle 12. During the tightening of the binding rope 74, a more stable pulling force is provided to the cable bundle 12, which improves the safety of the device and the use effect of the device. After use, after the slip ring 73 is reset, the binding rope 74 bends vertically, and the sleeve structure 75 can automatically reset to the middle area of ​​the binding rope 74 for the next use.

[0061] In addition, in some test requirements, it is also necessary to simulate a certain bending posture of the cable bundle 12 for testing to be close to the actual use state. Therefore, the present invention also makes the following improvements, referring to the attached manual Figures 10 to 12 A plurality of mounting sockets 51 are arrayed on the test operating table 5, and mounting posts 622 are provided at the bottom of the first mounting seat 611, the second mounting seat 621, the lightning injection probe 21, the HIRF injection probe 31 and the monitoring probe 41. The mounting posts 622 are used to be plugged into the mounting sockets 51, wherein the second fixing frame 62 is rotationally connected to the second mounting seat 621, a second worm gear 623 is provided at the bottom of the second fixing frame 62, a second worm 624 is rotationally installed in the second mounting seat 621, the second worm 624 cooperates with the second worm gear 623, and then the rotation direction of the second fixing frame 62 can be adjusted by rotating the second worm 624, thereby facilitating the second fixing frame 62 to support the cable bundle 12 in multiple postures on the test operating table 5, so as to improve more test scenarios.

[0062] It should be noted that in the above-mentioned embodiment, the first fixing frame 61, the first mounting seat 611, the screw structure 612, the second fixing frame 62, the cable clamping structure 7 and other structures all adopt insulating structures, such as plastic parts, rubber parts, etc. Other key structures also use insulating structures to avoid affecting the test of the cable bundle 12.

[0063] Refer to the instruction manual Figure 1 and Figure 2 The present invention also provides a test method for aircraft lightning indirect effects and HIRF conduction sensitivity, which specifically includes the following steps:

[0064] Step 1: Build the test platform according to the requirements of the test layout diagram;

[0065] Step 2: Determine the frequency bandwidth, level and other parameters for the HIRF conduction sensitivity test, and perform HIRF conduction sensitivity test calibration;

[0066] Step 3: Determine the parameters such as the lightning waveform, level and quantity for the lightning indirect effect test, and verify the performance of the transient signal generator of the lightning indirect effect test system 2;

[0067] Step 4: Select the working mode of the test equipment 1;

[0068] Step 5, selecting the cable bundle 12 to be tested;

[0069] Step 6: Set the initial frequency of the HIRF conducted sensitivity test and conduct the test. During the dwell time of each HIRF test frequency point, conduct a lightning indirect effect test on the target cable bundle 12 at the same time, and observe and record the conditions of the test equipment 1 under the combined effects of lightning and HIRF through the accompanying test monitoring equipment 13;

[0070] Step 7: Change the frequency of the HIRF conduction sensitivity test, and repeat step 6 until the end frequency of the HIRF conduction sensitivity test is reached;

[0071] Step 8, replace a new test cable bundle 12, repeat steps 5, 6 and 7, and complete the test of all cable bundles 12;

[0072] Step 9: Select a new working mode of the test equipment 1, and repeat steps 4, 5, 6, 7 and 8 to complete the test of all working modes;

[0073] Step 10: Observe and record the conditions of the equipment under test 1 under the combined effects of lightning and HIRF through the accompanying test monitoring equipment 13, and complete the test verification of the comprehensive lightning and HIRF protection performance of the aircraft electronic and electrical system.

[0074] The above describes an embodiment of the present embodiment, but the present embodiment is not limited to the above-mentioned specific implementation methods. The above-mentioned specific implementation methods are merely illustrative and not restrictive. Under the guidance of the present embodiment, ordinary technicians in this field can also make many forms, all of which are within the protection of the present embodiment.

Claims

1. Aircraft lightning indirect effect and HIRF conduction sensitivity test device, characterized by: It includes a test device (1), a test monitoring device (13), a cable bundle (12), a HIRF injection probe (31), a lightning injection probe (21), a monitoring probe (41), a lightning signal isolator (32), a HIRF conduction test system (3), a lightning indirect effect test system (2), and a digital oscilloscope (4); The device under test (1) and the auxiliary device (11) are connected via a cable bundle (12); the lightning injection probe (21), the HIRF injection probe (31) and the monitoring probe (41) are sequentially arranged on the cable bundle (12) in a direction from the device under test (1) to the auxiliary device (11); a lightning signal injection channel is arranged between the lightning indirect effect test system (2) and the lightning injection probe (21); a HIRF signal injection channel is arranged between the HIRF conduction test system (3) and the HIRF injection probe (31); and a monitoring signal transmission channel is arranged between the digital oscilloscope (4) and the monitoring probe (41); The test method of the aircraft lightning indirect effect and HIRF conduction sensitivity test device comprises the following steps: Step 1: Build the test platform according to the requirements of the test layout diagram; Step 2: Determine the frequency bandwidth and level parameters for conducting the HIRF conduction sensitivity test, and perform the HIRF conduction sensitivity test calibration; Step 3: Determine the lightning waveform, level and quantity parameters for the lightning indirect effect test, and verify the performance of the transient signal generator; Step 4: Select the working mode of the device under test (1); Step 5: Select the cable bundle to be tested (12); Step 6: Set the initial frequency of the HIRF conducted sensitivity test and conduct the test. During the dwell time at each HIRF test frequency point, conduct a lightning indirect effect test on the target cable bundle (12). Observe and record the conditions of the equipment under test (1) under the combined effects of lightning and HIRF through the accompanying test monitoring equipment (13); Step 7: Change the frequency of the HIRF conduction sensitivity test, and repeat step 6 until the end frequency of the HIRF conduction sensitivity test is reached; Step 8, replace a new test cable bundle (12), and repeat steps 5, 6 and 7 to complete the test of all cable bundles (12); Step 9. Select the new working mode of the equipment under test (1) and repeat steps 4, 5, 6, 7 and 8 to complete the test of all working modes. Step 10: Observe and record the conditions of the equipment under test (1) under the combined effects of lightning and HIRF through the accompanying test monitoring equipment (13), and complete the test verification of the comprehensive lightning and HIRF protection performance of the aircraft electronic and electrical system.

2. The aircraft lightning indirect effect and HIRF conduction sensitivity test device according to claim 1, characterized in that: A lightning signal isolator (32) is provided on the HIRF signal injection channel between the HIRF conduction test system (3) and the HIRF injection probe (31).

3. The aircraft lightning indirect effect and HIRF conduction sensitivity test device according to claim 2, characterized in that: The lightning signal output by the lightning indirect effect test system (2) is coupled into the cable bundle (12) via a lightning injection probe (21), thereby achieving coupled injection of the lightning signal. The HIRF test signal output by the HIRF conduction test system (3) is coupled into the cable bundle (12) via a HIRF injection probe (31), thereby achieving conducted injection of the HIRF test signal.

4. The aircraft lightning indirect effect and HIRF conduction sensitivity test device according to claim 3, characterized in that: The test device further comprises a test operation table (5), the lightning injection probe (21), the HIRF injection probe (31) and the monitoring probe (41) are all mounted on the test operation table (5), the cable bundle (12) passes through the monitoring probe (41), the HIRF injection probe (31) and the lightning injection probe (21), and a fixing frame assembly (6) is also mounted on the test operation table (5), the fixing frame assembly (6) comprises a first fixing frame (61), at least two groups of the first fixing frames (61) are provided, the two groups of the first fixing frames (61) are respectively arranged at two ends of an area where the cable bundle (12) is located on the test operation table (5), the first fixing frame (61) is a cylindrical structure, the cable bundle (12) passes through the first fixing frame (61), and a cable clamping structure (7) is arranged on the first fixing frame (61), and the cable clamping structure (7) is used to clamp and fix the cable bundle (12); A first mounting seat (611) is provided at the bottom of the first fixing frame (61); the first fixing frame (61) is slidably connected to the first mounting seat (611) via a slide rail; a screw rod structure (612) is rotatably mounted in the first mounting seat (611); and a slider structure threadably matched with the screw rod structure (612) is provided at the bottom of the first fixing frame (61).

5. The aircraft lightning indirect effect and HIRF conduction sensitivity test device according to claim 4, characterized in that: The cable clamping structure (7) comprises a hoop (71), the hoop (71) being rotatably mounted on a first fixing frame (61), a rubber pad structure being provided on the inner side of the hoop (71), and a locking member (711) being provided between the hoop (71) and the first fixing frame (61).

6. The aircraft lightning indirect effect and HIRF conduction sensitivity test device according to claim 4, characterized in that: The fixing frame assembly (6) further comprises a plurality of sets of second fixing frames (62), wherein the second fixing frames (62) are mounted on the test operation table (5) via second mounting seats (621), the second fixing frames (62) are cylindrical structures, and the second fixing frames (62) are also provided with a cable clamping structure (7).

7. The aircraft lightning indirect effect and HIRF conduction sensitivity test device according to claim 6, characterized in that: The cable clamping structure (7) comprises a swivel (72) and a slip ring (73); the swivel (72) is rotatably mounted on one end of the second fixing frame (62); the slip ring (73) is slidably mounted on the other end of the second fixing frame (62); a guide structure (731) is provided between the slip ring (73) and the second fixing frame (62); a binding rope (74) is provided between the second fixing frame (62) and the slip ring (73); and two ends of the binding rope (74) are fixedly connected to the second fixing frame (62) and the slip ring (73), respectively.

8. The aircraft lightning indirect effect and HIRF conduction sensitivity test device according to claim 7, characterized in that: A first worm gear (721) is fixedly mounted on the outside of the rotating ring (72); a first worm (722) cooperating with the first worm gear (721) is rotatably mounted on the second fixed frame (62); a slide groove cooperating with the guide structure (731) is provided on the second fixed frame (62); an elastic reset member (732) is provided between the guide structure (731) and the slide groove; the elastic reset member (732) is used to provide an elastic force to the sliding ring (73) in a direction away from the rotating ring (72); the binding rope (74) is an elastic rope structure; and a plurality of sleeve structures (75) are slidably sleeved on the outside of the binding rope (74).

9. The aircraft lightning indirect effect and HIRF conduction sensitivity test device according to claim 8, characterized in that: The test operation table (5) is provided with a plurality of groups of mounting sockets (51) in an array. The bottoms of the first mounting seat (611), the second mounting seat (621), the lightning injection probe (21), the HIRF injection probe (31) and the monitoring probe (41) are all provided with mounting posts (622). The mounting posts (622) are used to be plugged into the mounting sockets (51). The second fixing frame (62) is rotatably connected to the second mounting seat (621). A second worm gear (623) is provided at the bottom of the second fixing frame (62). A second worm (624) is rotatably mounted in the second mounting seat (621). The second worm gear (624) and the second worm gear (623) cooperate with each other.

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