Aircraft cable cutting arc test device

Abstract

The utility model relates to an aircraft cable cutting arc test device. The aircraft cable cutting arc test device comprises a test bench, an arc striking device, a cable group and a tested piece, wherein the arc striking device is installed on the test bench, the cable group is horizontally arranged on the test bench, and the tested piece is installed on the test bench through the support and faces one side of the cable group; wherein the arc striking device comprises a cutting blade, a bolt and a motor, the vertical position of the cutting blade is adjusted by screwing the bolt, so that the depth of the cutting blade cutting into the cable group is changed, the main plane of the cutting blade is perpendicular to the longitudinal axis of the cable group, and the cutting blade horizontally reciprocates through the motor so as to cut the cable group in a reciprocating manner.

Description

TECHNICAL FIELD

[0001] The utility model relates to an aircraft cable cutting electric arc test device belongs to the aircraft cable electric arc damage verification technical field. BACKGROUND

[0002] During the flight of the aircraft, the sharp edge of the metal structure can rub against the cable with accidental damage of the insulating skin, resulting in cutting of the cable, formation of a short circuit, and triggering of a fault arc. Therefore, a set of simulation device for the cutting electric arc of the aircraft cable needs to be designed to verify the safety and effectiveness of the electric arc isolation and protection design of the aircraft cable.

[0003] The prior art cannot effectively simulate the scenario in which the cable accidentally contacts the sharp edge of the metal structure under the vibration environment during the flight of the aircraft, resulting in cutting of the cable, generation of an electric arc fault, and electric arc damage to the surrounding environment. SUMMARY

[0004] One purpose of the utility model is to provide an aircraft cable cutting electric arc test device that can overcome at least some of the defects of the prior art, effectively simulate the occurrence of a cutting electric arc fault caused by the friction of the sharp edge of the metal structure against the cable, and effectively evaluate the electric arc damage of various aircraft components.

[0005] The above purpose of the utility model is achieved by an aircraft cable cutting electric arc test device, which comprises a test bench, an arc generation device, a cable group, and a test piece.

[0006] The arc generation device is installed on the test bench, the cable group is horizontally arranged on the test bench, and the test piece is installed on the test bench by a support and faces one side of the cable group.

[0007] The arc generation device comprises a cutting blade, a bolt, and a motor. The vertical position of the cutting blade is adjusted by screwing the bolt, thereby changing the depth of the cutting blade into the cable group. The main plane of the cutting blade is perpendicular to the longitudinal axis of the cable group. The cutting blade also moves horizontally and reciprocally by the motor, thereby reciprocally cutting the cable group.

[0008] According to the above technical solution, the aircraft cable cutting electric arc test device of the utility model can effectively simulate the occurrence of a cutting electric arc fault caused by the friction of the sharp edge of the metal structure against the cable, and effectively evaluate the electric arc damage of various aircraft components.

[0009] Preferably, the arc generation device further comprises a limiting nut, which is engaged with the bolt to limit the maximum depth of the cutting blade into the cable group.

[0010] Preferably, the aircraft cable cutting arc test device further comprises at least two clamps respectively arranged on two sides of the cutting blade to clamp the cable group.

[0011] Preferably, the test piece comprises a plate structure, a cable, or a pipeline.

[0012] Preferably, the test bench is provided with a sliding rail, and the support can slide along the sliding rail to adjust the isolation distance between the test piece and the arc starting point of the cable group.

[0013] Preferably, the test bench is further provided with a scale to indicate the isolation distance between the test piece and the arc starting point of the cable group.

[0014] Preferably, the isolation distance is 0.5-6.0 inches.

[0015] Preferably, the cable group comprises a first cable, a second cable and a third cable, the first cable and the second cable are arranged in parallel adjacent to each other in a first horizontal plane, the third cable is arranged between the first cable and the second cable in a second horizontal plane below the first horizontal plane, and the first cable, the second cable and the third cable are tangent to each other.

[0016] Preferably, the horizontal center axis of the test piece is coplanar with the first horizontal plane.

[0017] Preferably, the aircraft cable cutting arc test device is placed in a test cabinet, and the test cabinet comprises an environment setting device and a data acquisition device. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 is a general schematic view of an aircraft cable cutting arc test device according to an embodiment of the present application.

[0019] Figure 2 is a schematic view of an arc starting device of an aircraft cable cutting arc test device according to an embodiment of the present application.

[0020] Figure 3 is a schematic view of a blade cutting cable of an aircraft cable cutting arc test device according to an embodiment of the present application.

[0021] Figure 4A is a schematic view of an aircraft cable cutting arc test device according to an embodiment of the present application before adjusting the position of the blade, Figure 4B is a schematic view of an aircraft cable cutting arc test device according to an embodiment of the present application after adjusting the position of the blade.

[0022] Figure 5AIs the knife of the aircraft cable cutting arc test device of an embodiment of the utility model correct cutting schematic view, Figure 5B Is the knife of the aircraft cable cutting arc test device of an embodiment of the utility model overcut schematic view.

[0023] Figure 6A Is the knife of the aircraft cable cutting arc test device of an embodiment of the utility model before cutting schematic view, Figure 6B Is the knife of the aircraft cable cutting arc test device of an embodiment of the utility model during cutting schematic view.

[0024] Figure 7A Is the "wire-plate" test configuration schematic view of the aircraft cable cutting arc test device of an embodiment of the utility model, Figure 7B Is the "wire-wire" test configuration schematic view of the aircraft cable cutting arc test device of an embodiment of the utility model, Figure 7C Is the "wire-tube" test configuration schematic view of the aircraft cable cutting arc test device of an embodiment of the utility model.

[0025] Figure 8 Is the isolation distance schematic view of the aircraft cable cutting arc test device of an embodiment of the utility model.

[0026] Figure 9 Is the slide rail and scale schematic view of the aircraft cable cutting arc test device of an embodiment of the utility model.

[0027] Figure 10 Is the schematic view of the aircraft cable cutting arc test device of an embodiment of the utility model placed in the test cabinet.

[0028] Figure 11 Is the electrical connection schematic view of the aircraft cable cutting arc test device of an embodiment of the utility model.

[0029] List of reference signs

[0030] 1: test table;

[0031] 2: arc striking device;

[0032] 3: cable group;

[0033] 4: test piece;

[0034] 5: support;

[0035] 6: clamp;

[0036] 10: aircraft cable cutting arc test device;

[0037] 11: slide rail;

[0038] 12: scale;

[0039] 21: cutting blade;

[0040] 22: bolt;

[0041] 23: motor;

[0042] 24: limiting nut;

[0043] 31: first cable;

[0044] 32: second cable;

[0045] 33: third cable;

[0046] 50: test cabinet;

[0047] 51: explosion-proof glass panel;

[0048] 52: operation panel;

[0049] V: vertical movement direction of the cutting blade;

[0050] H: horizontal movement direction of the cutting blade;

[0051] S: isolation distance. DETAILED DESCRIPTION

[0052] The specific embodiments of the present application will be described hereinafter, it should be noted that, in the specific description of these embodiments, in order to be brief and concise, the present specification can not be detailed description of all the features of the actual embodiment. It should be understood that, in the actual implementation process of any one embodiment, as in the process of any engineering project or design project, in order to achieve the specific goal of the developer, in order to meet the system related or business related restrictions, often make a variety of specific decisions, and this will also change from one embodiment to another. In addition, it can also be understood that, although the effort made in this development process may be complex and lengthy, however, for those skilled in the art related to the content disclosed in the present application, some design, manufacture or production changes based on the technical content disclosed in the present disclosure are only conventional technical means, and should not be understood as the content of the present disclosure is not sufficient.

[0053] Unless otherwise defined, technical terms or scientific terms used in the claims and the specification shall have the meaning commonly understood by one of ordinary skill in the art to which this practical new type belongs. The terms "first", "second", and similar terms used in the specification and claims of the practical new type patent application do not denote any order, quantity, or importance, but are used to distinguish different components. The terms "one" or "a" or similar terms do not denote a quantity limitation, but mean that at least one exists. The terms "include" or "contain" or similar terms mean that the elements or objects appearing before the "include" or "contain" are encompassed, and the elements or objects listed after the "include" or "contain" and their equivalent elements are not excluded. The terms "connect" or "connected" or similar terms are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0054] In the following description, in order to clearly show the structure and working mode of the practical new type, many directional words will be used for description, but the words "front", "back", "left", "right", "outer", "inner", "outward", "inward", "up", "down" and the like should be understood as convenient language, and should not be understood as limiting words.

[0055] Figure 1 is a schematic diagram of an aircraft cable cutting arc test device according to an embodiment of the practical new type. As shown in Figure 1 , according to an embodiment of the practical new type, the aircraft cable cutting arc test device 10 includes a test bench 1, an arc striking device 2, a cable group 3, and a test piece 4. The "test piece" referred to in this document refers to a component used for testing to evaluate arc damage.

[0056] The arc striking device 2 is installed on the test bench 1, the cable group 3 is horizontally arranged on the test bench 1, and the test piece 4 is installed on the test bench 1 through a support 5 and faces one side of the cable group 3.

[0057] Figure 2 is a schematic diagram of an arc striking device of an aircraft cable cutting arc test device according to an embodiment of the practical new type. Figure 3 is a schematic diagram of a blade cutting cable of an aircraft cable cutting arc test device according to an embodiment of the practical new type. As shown in Figure 2 to Figure 3 , the arc striking device 2 includes a cutting blade 21, a bolt 22, and a motor 23 (such as a servo motor), the cutting blade 21 adjusts its vertical position by screwing the bolt 22, thereby changing the depth of the cutting blade 21 cutting into the cable group 3, the main plane (also called the cutting cross section) of the cutting blade 21 is perpendicular to the longitudinal axis of the cable group 3, and the cutting blade 21 also reciprocates horizontally by the motor 23, thereby reciprocating the cutting of the cable group 3.

[0058] According to the technical scheme, the aircraft cable cutting arc test device can effectively simulate the occurrence of the cutting arc fault caused by the sharp edge of the metal structure rubbing the cable, and effectively evaluate the arc damage of various aircraft parts.

[0059] Specifically, the test simulation scene is that the sharp edge of the metal structure rubs the cable to cause the cable to be cut, the basic principle is to control the depth of the cutting blade into the cable through the bolt, and to control the cutting blade to reciprocate horizontally at a certain frequency through the motor, to cut the cable to trigger the fault arc, and to evaluate the damage of the arc to the surrounding affected objects (i.e. the test piece).

[0060] Preferably, the arc striking device 2 and the test piece 4 are installed on opposite sides of the cable group 3. Preferably, the cutting blade 21 is arranged above the cable group 3, the bolt 22 is connected to the cutting blade 21 through the tool fixing device and arranged above the cutting blade 21, so as to facilitate the cutting blade 21 to cut into the cable group 3 from above. Preferably, the cutting blade 21 is connected to the output part of the motor 23 through the tool fixing device, so as to realize horizontal reciprocating motion to reciprocate the cable group 3. Preferably, the material of the cutting blade 21 should be consistent with the material of the sharp edge of the metal structure on the aircraft, and the blade angle should be less than or equal to the blade angle of the sharp edge of the metal structure on the aircraft.

[0061] In some embodiments, as shown in Figure 2 to Figure 3 , the arc striking device 2 further comprises a limiting nut 24, the limiting nut 24 is engaged with the bolt 22 to limit the maximum depth of the cutting blade 21 into the cable group 3.

[0062] Figure 4A is a schematic view of the blade position adjustment of the aircraft cable cutting arc test device of an embodiment of the utility model, Figure 4B is a schematic view of the blade position adjustment of the aircraft cable cutting arc test device of an embodiment of the utility model. Figure 5A is a schematic view of the correct cutting of the blade of the aircraft cable cutting arc test device of an embodiment of the utility model, Figure 5B is a schematic view of the excessive cutting of the blade of the aircraft cable cutting arc test device of an embodiment of the utility model. As Figure 4A to Figure 5B shown, the bolt 22 and the limiting nut 24 are used to control the stroke of the cutting blade 21. Specifically, at the beginning of the test, the vertical position of the cutting blade 21 is adjusted by turning the bolt 22, that is, turning the bolt 22 clockwise or counterclockwise can change the depth of the cutting blade 21 into the cable, for details Figure 4A and Figure 4B; while ensuring that the main plane of the cutting blade 21 is perpendicular to the longitudinal axis of the cable. The limiting nut 24 plays a limiting role, when the cutting blade 21 is controlled to move downward along the vertical movement direction V by the bolt 22, there is a terminal position corresponding to the maximum cutting depth, which ensures that the cutting blade 21 cannot cut the parts below the first cable 31 (also referred to as cable A) and the second cable 32 (also referred to as cable B), which will be described in detail below Figure 5A and Figure 5B .

[0063] Figure 6A is a schematic view of the cutting blade before cutting of the aircraft cable cutting electric arc test device according to an embodiment of the present application, Figure 6B is a schematic view of the cutting blade during cutting of the aircraft cable cutting electric arc test device according to an embodiment of the present application. As shown in Figure 6A and Figure 6B , the cutting blade 21 can be controlled by the motor 23 to reciprocatingly cut the cable along the horizontal movement direction H at a certain frequency.

[0064] In some embodiments, as shown in Figure 1 , the aircraft cable cutting electric arc test device 10 further comprises at least two clamps 6 located on both sides of the cutting blade 21 to clamp the cable group 3, thus ensuring the triggering of the cutting electric arc. Preferably, the cable A and the cable B are subjected to ring cutting or flat cutting treatment before the test, so as to expose the metal wire core, but cannot damage the wire core.

[0065] The EWIS (electrical wiring interconnection system) electric arc can ignite flammable liquids, gases, or break through the surrounding structural members such as pipelines. In some small space areas of the aircraft, the EWIS or the EWIS and other aircraft system components cannot fully meet the isolation requirements due to space limitations.

[0066] Figure 7A is a schematic view of a "wire-plate" test configuration of the aircraft cable cutting electric arc test device according to an embodiment of the present application, Figure 7B is a schematic view of a "wire-wire" test configuration of the aircraft cable cutting electric arc test device according to an embodiment of the present application, Figure 7C is a schematic view of a "wire-pipe" test configuration of the aircraft cable cutting electric arc test device according to an embodiment of the present application. In some embodiments, as shown in Figure 7A to Figure 7C , the test piece 4 comprises a plate-shaped structural member, a cable, or a pipeline. Therefore, the aircraft cable cutting electric arc test device of the present application can evaluate the electric arc damage effect of various aircraft components. The aircraft cable cutting electric arc test device has good versatility, and the plate-shaped structural member, the cable, and the pipeline can be installed on the test device as the object of the EWIS electric arc damage evaluation, which is suitable for evaluating the electric arc damage effect in the typical scene of the aircraft EWIS isolation, and ensures that the safety of the EWIS design is met.

[0067] Figure 8 is an isolation distance schematic diagram of the aircraft cable cutting arc test device of an embodiment of the utility model. Figure 9 is a slide rail and scale schematic diagram of the aircraft cable cutting arc test device of an embodiment of the utility model. In some embodiments, as shown in Figure 8 and Figure 9 , the test table 1 is provided with a slide rail 11, and the support 5 can slide along the slide rail 11 to adjust the isolation distance S between the test piece 4 and the arc starting point of the cable group 3. It should be noted that the "arc starting point" described herein refers to the midpoint of the line connecting the center of the first cable and the center of the second cable in the cutting cross section of the cutting blade. Alternatively, the isolation distance S can be the distance between the test piece 4 and the vertical longitudinal bisector (i.e., the vertical plane that vertically bisects the first cable and the second cable) of the cable group 3.

[0068] In some embodiments, as shown in Figure 8 and Figure 9 , the test table 1 is also provided with a scale 12 to indicate the isolation distance S between the test piece 4 and the arc starting point of the cable group 3. In some embodiments, as shown in Figure 8 and Figure 9 , the isolation distance S is 0.5-6.0 inches. Preferably, the minimum adjustment precision of the isolation distance S is 0.5 inches.

[0069] Therefore, the aircraft cable cutting arc test device of the utility model can conveniently adjust the isolation distance. The isolation distance between the plate-shaped structural member, the cable, or the pipeline and the arc starting point can be adjusted, which is suitable for tests of different EWIS isolation distance requirements, and further verifies the effectiveness of the EWIS isolation design and protection design.

[0070] In some embodiments, as shown in Figure 5A and Figure 5B , the cable group 3 includes a first cable 31, a second cable 32, and a third cable 33, the first cable 31 and the second cable 32 are located in a first horizontal plane and are arranged in parallel adjacent to each other, the third cable 33 is located in a second horizontal plane below the first horizontal plane and is located between the first cable 31 and the second cable 32, and the first cable 31, the second cable 32, and the third cable 33 are tangent.

[0071] In some embodiments, as shown in Figure 7A to Figure 7C , the horizontal center axis of the test piece 4 is coplanar with the first horizontal plane. Preferably, the horizontal center axis of the test piece 4 and the horizontal longitudinal center axis of the first cable 31 or the horizontal longitudinal center axis of the second cable 32 are located in the same horizontal plane (the first horizontal plane) and are parallel to each other.

[0072] Figure 10is a schematic view of the aircraft cable cutting arc test device of one embodiment of the present application placed in a test cabinet. In some embodiments, as shown in Figure 10 the aircraft cable cutting arc test device 10 is placed in a test cabinet 50, which includes an environment setting device and a data acquisition device to realize the functions of simulating the on-board environment and recording test data (such as current-voltage waveform diagram). Preferably, the test cabinet 50 can also include an openable and closable explosion-proof glass panel 51 and a ventilation pipeline to prevent the molten metal liquid splashed during the arc from causing harm to the test personnel and the surrounding environment, and to timely discharge the smoke generated when the arc is triggered through the pipeline. Preferably, the test cabinet 50 can also include an operation panel 52 to operate the aircraft cable cutting arc test device 10, the environment setting device, the data acquisition device, etc.

[0073] Before the test, the test cable needs to be prepared. First, cut several cable segments of appropriate length and clean the above-mentioned cut cable with cloth soaked in ethanol or isopropanol; second, remove the insulation layer at both ends of each cable to facilitate electrical connection; and finally, perform ring cutting or flat cutting on the midpoint of cable A and cable B to expose the metal wire core.

[0074] The material and thickness of the test piece used in the test should be consistent with the aircraft configuration, or the test configuration should be shown to be more severe through analysis. The plate-shaped structural member material includes metal material or composite material; the cable material includes single-core wire, shielded wire or twisted wire; and the pipeline material includes aluminum alloy, stainless steel or titanium alloy.

[0075] In addition to the aircraft cable cutting arc test device of the present application, the equipment used in the test generally includes power supply, temperature measurement device, load and circuit protection device, etc. Figure 11 is an electrical connection schematic diagram of the aircraft cable cutting arc test device of one embodiment of the present application.

[0076] The test steps can be specifically as follows:

[0077] a. Install the test piece (with temperature measurement device) and the test cable expected to trigger the cutting arc. Perpendicularly clamp the test cable to the cutting blade through the clamp, and ignore the slack of the tightened cable; set the arcing point and the isolation distance of the test piece through the slide rail and the translation scale to ensure that cable A, cable B and the test piece are parallel at the same height. Connect the circuit according to the electrical connection schematic diagram as shown in Figure 11 , and set the resistance value of the current regulating resistor Rf to match the required fault current;

[0078] b. Turn the bolt to adjust the depth at which the blade can cut the test cable, and use the limiting nut to prevent the blade from cutting below cable A and cable B;

[0079] c. Set the power output parameters, start the power supply device to power on the circuit;

[0080] d. Start the cutting device, make the blade reciprocate cutting the cable with a stroke and frequency, trigger the fault arc;

[0081] e. Stop the test when any of the following conditions occurs:

[0082] 1) If the blade penetrates the cable A and the cable B during the test, but the breaker of the A phase or the B phase does not trip, stop the blade cutting movement and disconnect the power supply. Record;

[0083] 2) If any circuit protection device of the A phase or the B phase trips during the test, stop the blade cutting movement and disconnect the power supply, determine whether the cable is disconnected. If both cables are disconnected, stop the test; if the cable is not disconnected, separate the cutting blade from the cable, wait for a period of time, re-close the circuit protection device and start the power supply. Then start the cutting device again, make the blade reciprocate cutting the cable with the same stroke and frequency, trigger the arc again until the circuit protection device trips for the second time or the test cable breaks after the test stops;

[0084] f. Record the damage of the test piece (damage area and damage depth, etc.), and the temperature change and the highest temperature of the inner wall of the test piece during the test;

[0085] g. Repeat the test at least three times to ensure the confidence of the test results.

[0086] In summary, the utility model simulates the arc damage to the aircraft components caused by the friction between the metal structure on the aircraft and the EWIS wire harness during the flight of the aircraft, thereby verifying the effectiveness of the isolation and protection design of the aircraft cable, and ensuring the safety of the aircraft.

[0087] The specific embodiments of the utility model have been described above, but those skilled in the art will understand that the above specific embodiments do not constitute a limitation on the utility model, and various modifications can be made on the basis of the above disclosure without exceeding the scope of the utility model.

Claims

1. An aircraft cable cut arc test apparatus, characterized by, The aircraft cable cutting arc test device comprises a test table, an arc striking device, a cable group and a test piece. The arc striking device is installed on the test table, the cable group is horizontally arranged on the test table, and the test piece is installed on the test table by a support and faces one side of the cable group. The arc striking device comprises a cutting blade, a bolt and a motor.

2. The aircraft wire cut arc test apparatus of claim 1, wherein, The cutting blade is adjusted in vertical position by screwing the bolt, so as to change the depth of the cutting blade cutting into the cable group.

3. The aircraft wire cut arc test apparatus of claim 1, wherein, The main plane of the cutting blade is perpendicular to the longitudinal axis of the cable group.

4. The aircraft wire cut arc test apparatus of claim 1, wherein, The cutting blade is also horizontally reciprocated by the motor, so as to reciprocally cut the cable group.

5. The aircraft wire cut arc test apparatus of claim 1, wherein, The arc striking device further comprises a limiting nut engaged with the bolt, so as to limit the maximum depth of the cutting blade cutting into the cable group.

6. The aircraft wire cut arc test apparatus of claim 5, wherein, The aircraft cable cutting arc test device further comprises at least two clamps respectively located on both sides of the cutting blade, so as to clamp the cable group.

7. The aircraft wire cut arc test apparatus of claim 5, wherein, The test piece comprises a plate structure, a cable or a pipeline.

8. The aircraft wire cut arc test apparatus of claim 1, wherein, The test table is provided with a slide rail, and the support can slide along the slide rail, so as to adjust the isolation distance between the test piece and the arc striking point of the cable group.

9. The aircraft wire cut arc test apparatus of claim 8, wherein, The test table is further provided with a scale, so as to indicate the isolation distance between the test piece and the arc striking point of the cable group.

10. The aircraft wire cut arc test apparatus of claim 1, wherein, The isolation distance is 0.5-6.0 inches. The cable group comprises a first cable, a second cable and a third cable. The first cable and the second cable are horizontally and adjacently arranged in parallel in a first horizontal plane. The third cable is located between the first cable and the second cable in a second horizontal plane below the first horizontal plane. The horizontal central axis of the test piece is coplanar with the first horizontal plane. The aircraft cable cutting arc test device is placed in a test cabinet, and the test cabinet comprises an environment setting device and a data acquisition device.

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