A device for measuring the explosive control force of a large aircraft suspension device

Abstract

The invention discloses a device for measuring the explosive control force of a large aircraft suspension device, comprising an aircraft suspension device, a large base, a small base, a positioning plate, a positioning bushing, a ring, a rotating wheel assembly, a handle assembly and a plurality of explosive control rings. The invention uses the large and small bases to support the aircraft suspension device, and uses the positioning plate, the positioning bushing and the ring to simulate the installation state of the aircraft suspension device on the aircraft to realize the positioning and fixing of the aircraft suspension device; uses the handle assembly to apply tension to the wire rope, so that the explosive control ring pulls the aircraft suspension device hook to unlock, and the sensor transmits the tension to the display device at this time; uses the geometric angle between the rotating wheel assembly and the aircraft suspension device hook as the angle required for measurement; uses the rotating wheel assembly to convert various force application angles into force in one direction; and reduces the difficulty of operation for workers by placing the aircraft suspension device horizontally on a pad to measure the explosive control force; and due to the improvement of the measurement angle accuracy, the measurement accuracy of the explosive control force value is also improved.

Description

Technical Field

[0001] The invention relates to the technical field of force measurement, and in particular to a device for measuring the explosive control force of a large aircraft suspension device. Background Art

[0002] An aircraft suspension device is a device that is suspended under the wing or belly of an aircraft and is used to suspend auxiliary fuel tanks, missiles or the next-level suspension device. For an aircraft suspension device, explosive control force is a very important technical indicator. Explosive control force refers to the minimum force required for the next-level suspension to forcibly detach from the suspension device at a specific angle. Therefore, whether the explosive control force value meets the requirements is an important parameter related to aircraft flight safety. General aircraft suspension devices use a vertical suspension method to measure explosive control force, that is, the aircraft suspension device is suspended on a mounting plate, and the explosive control force is measured by winding a wire rope around the turntable and handle installed below. For large aircraft suspension devices, this measurement method is not accurate enough in measuring the angle, and it is difficult for workers to operate. Therefore, a new measurement method is needed to measure the explosive control force of large aircraft suspension devices. Summary of the invention

[0003] The technical problem solved by the present invention is as follows: In view of the problems existing in the background technology, a device for measuring the explosive control force of a large aircraft suspension device is provided.

[0004] The technical solution of the present invention:

[0005] A device for measuring explosion control force of a large aircraft suspension device comprises an aircraft suspension device, a large base, a small base, a positioning plate, a positioning bushing, a ring, a rotating wheel assembly, a handle assembly and a plurality of explosion control rings, wherein the large base and the small base are arranged in parallel, and a plurality of movable pads are arranged on the large base and the small base, and the two ends of the aircraft suspension device are respectively arranged on the pads of the large base and the small base, and the explosion control ring is hung on the hook of the aircraft suspension device, and the positioning plate is arranged on the surface of the large base, and the positioning bushing is fixed on the positioning plate, and the ring is sleeved on the vertical shaft of the aircraft suspension device, and the vertical shaft of the aircraft suspension device is arranged in the positioning bushing, and the end face of the ring is connected to the end face of the positioning bushing. The large base is provided with a plurality of parallel arranged rotary wheel assembly groups, each rotary wheel assembly group includes four rotary wheel assemblies, two of which are parallel arranged close to the aircraft suspension device, and there is a distance between the two rotary wheel assemblies, and the other two rotary wheel assemblies are parallel arranged away from the aircraft suspension device, and the two rotary wheel assemblies are in contact with each other, and three groups of steel wire ropes are fixed on each explosion control ring, two of which are respectively bypassed around the outside of the two rotary wheel assemblies close to the aircraft suspension device, and pass through the contact points of the two rotary wheel assemblies away from the aircraft suspension device, and are connected to the handle assembly arranged on the edge of the large base, and the other group of steel wire ropes pass through the contact points of the two rotary wheel assemblies away from the aircraft suspension device, and are connected to the handle assembly.

[0006] The surface of the cushion block is provided with a hard rubber plate.

[0007] The positioning plate is fixed on the surface of the large base through cylindrical pins and screws.

[0008] The positioning bushing is provided with a positioning nut.

[0009] The rotating wheel assembly comprises a supporting shaft, a rotating wheel and a fixed bearing. The rotating wheel is fixed to the top of the supporting shaft through the fixed bearing. A fastening nut is arranged on the bottom end of the supporting shaft. A wire groove is arranged on the outer edge of the rotating wheel.

[0010] The handle assembly includes a base plate, a rolling bearing, a screw, a handle, a transfer nut, a transfer screw, a sensor and a hook. The base plate is fixed to the large base through pin holes and pins. The rolling bearing is installed in the mounting bearing hole of the base plate. The screw is installed in the rolling bearing. One end of the screw is connected to the handle and the other end is connected to the transfer nut. The transfer nut is connected to the transfer screw. The transfer screw is connected to the sensor. The sensor is connected to the hook. Bearing covers are fixed to both end surfaces of the rolling bearing by fixing screws.

[0011] The rotating wheel of the rotating wheel assembly is at the same height as the rolling bearing of the handle assembly.

[0012] The explosion control ring is made of 2.5-3mm steel wire wound on a specific steel structure plate.

[0013] The sensor is connected to an external display device.

[0014] The screw rod is provided with a key.

[0015] The beneficial effects of the present invention are as follows: the present invention utilizes large and small bases to support the aircraft suspension device, utilizes positioning plates, positioning bushings, and rings to simulate the installation state of the aircraft suspension device on the aircraft to realize the positioning and fixing of the aircraft suspension device; utilizes a handle assembly to apply tension to the wire rope, so that the explosion control ring pulls the aircraft suspension device hook to unlock, and at this time the sensor transmits the tension to the display device; utilizes the geometric angle between the rotating wheel assembly and the aircraft suspension device hook as the angle required for measurement; utilizes the rotating wheel assembly to convert various force application angles into force in one direction; the present invention reduces the difficulty of operation for workers by measuring the explosion control force by placing the aircraft suspension device horizontally on a pad; due to the improvement of the measurement angle accuracy, the measurement accuracy of the explosion control force value is also improved, and various difficulties encountered in the explosion control force measurement of large aircraft suspension devices are completely solved. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the structure of the present invention;

[0017] Figure 2is a schematic diagram of a runner assembly of the present invention;

[0018] Figure 3 is a schematic diagram of a handle assembly of the present invention;

[0019] Figure 4 is a schematic diagram of the explosion control ring of the present invention;

[0020] As shown in the figure: 1. Large base, 2. Small base, 3. Spacer, 4. Ring, 5. Positioning bushing, 6. Positioning nut, 7. Screw, 8. Cylindrical pin, 9. Wire rope, 10. Support shaft, 11. Turntable, 12. Fixed bearing, 13. Fastening nut, 14. Handle, 15. Bottom plate, 16. Fixing screw, 17. Bearing cover, 18. Screw, 19. Adapter nut, 20. Adapter screw, 21. Sensor, 22. Hook, 23. Key, 24. Rolling bearing, 25. Explosion control ring, 26. Aircraft suspension device, 27. Positioning plate, 28. Wire trough. DETAILED DESCRIPTION

[0021] The present invention will be further described below in conjunction with the accompanying drawings. Figure 1 As shown, a large aircraft suspension device explosion control force measuring device includes an aircraft suspension device 26, a large base 1, a small base 2, a positioning plate 27, a positioning bushing 5, a ring 4, a rotating wheel assembly, a handle assembly and a plurality of explosion control rings 25, wherein the large base 1 and the small base 2 are arranged in parallel, and a plurality of movable pads 3 are arranged on the large base 1 and the small base 2, and the two ends of the aircraft suspension device 26 are respectively arranged on the pads on the large base 1 and the small base 2, and the explosion control ring 25 is hung on the hook of the aircraft suspension device 26, and the positioning plate 27 is arranged on the surface of the large base 1, and the positioning bushing 5 is fixed on the positioning plate 27, and the ring 4 is sleeved on the vertical shaft of the aircraft suspension device 26, and the vertical shaft of the aircraft suspension device 26 is arranged in the positioning bushing 5. The end face of the ring 4 fits with the end face of the positioning bushing 5. The large base 1 is provided with a plurality of parallel arranged rotary wheel assembly groups, each rotary wheel assembly group includes four rotary wheel assemblies, two of which are arranged in parallel close to the aircraft suspension device 26, and there is a distance between the two rotary wheel assemblies, and the other two rotary wheel assemblies are arranged in parallel away from the aircraft suspension device 26, and the two rotary wheel assemblies are in contact with each other. Three groups of steel wire ropes 9 are fixed on each explosion control ring 25, two of which are respectively bypassed around the outside of the two rotary wheel assemblies close to the aircraft suspension device 26, and pass through the contact points of the two rotary wheel assemblies away from the aircraft suspension device 26, and are connected to the handle assembly arranged on the edge of the large base 1, and another group of steel wire ropes 9 pass through the contact points of the two rotary wheel assemblies away from the aircraft suspension device 26, and are connected to the handle assembly.

[0022] The surface of the cushion block 3 is provided with a hard rubber plate to prevent the cushion block 3 from scratching the surface of the aircraft suspension device 26 .

[0023] A plurality of positioning pin holes are provided on the large base 1 , and cylindrical pins 8 and screws 7 pass through the positioning pin holes to fix the positioning plate 27 on the surface of the large base 1 .

[0024] The positioning bushing 5 is provided with a positioning nut 6. The aircraft suspension device 26 is positioned by the ring 4 and the positioning bushing 5 and is tightened with the positioning nut 6 to prevent the aircraft suspension device 26 from being displaced when subjected to force.

[0025] like Figure 2 As shown, the wheel assembly includes a support shaft 10, a wheel 11, and a fixed bearing 12. The wheel 11 is fixed to the top of the support shaft 10 through the fixed bearing 12. A fastening nut 13 is provided on the bottom end of the support shaft 10. A wire groove 28 is provided on the outer edge of the wheel 11. The wire rope 9 is arranged along the wire groove 28. The wheel assembly is positioned through the wheel mounting screw hole on the large bottom 1, and then the wheel assembly is locked by the fastening nut 13.

[0026] like Figure 3 As shown, the handle assembly includes a base plate 15, a rolling bearing 24, a screw 18, a handle 14, a transfer nut 19, a transfer screw 20, a sensor 21 and a hook 22. The base plate 15 is fixed to the large base 1 through pin holes and pins. The rolling bearing 24 is installed in the mounting bearing hole of the base plate 15. The screw 18 is installed in the rolling bearing 24. One end of the screw 18 is connected to the handle 14, and the other end is connected to the transfer nut 19. The transfer nut 19 is connected to the transfer screw 20. The transfer screw 20 is connected to the sensor 21, and the sensor 21 is connected to the hook 22. The two end surfaces of the rolling bearing 24 are fixed with bearing covers 17 by fixing screws 16 to prevent foreign matter from entering the rolling bearing 24.

[0027] The rotating wheel 11 of the rotating wheel assembly is at the same height as the rolling bearing 24 of the handle assembly.

[0028] like Figure 4 As shown, the explosion control ring 25 is made of 2.5-3 mm steel wire wound on a specific steel structure plate, and can bear sufficient explosion control force.

[0029] The sensor 21 is connected to an external display device.

[0030] The screw rod 18 is provided with a key 23 to prevent the screw rod 18 from being dragged out of the rolling bearing 24 .

[0031] Specific implementation process: first, place the aircraft suspension device 26 horizontally on the large base 1 and the small base 2, and pad a number of pads 3 under the aircraft suspension device 26 according to the force conditions, then put the ring 4 on the vertical shaft of the aircraft suspension device 26 and fix it with screws 7, then put the vertical shaft of the aircraft suspension device 26 into the positioning bushing 5, so that the end face of the ring 4 fits with the end face of the positioning bushing 5, and finally tighten the aircraft suspension device 26 with the positioning nut 6 to prevent the aircraft suspension device 26 from being displaced when subjected to force. At this time, the aircraft suspension device 26 is fixed; measure the aircraft suspension When the explosive control force in a certain direction of one point of the hanging device 26 is measured, the explosive control ring 25 is hung on the hook at the corresponding position of the aircraft hanging device 26, and then the wire rope 9 is passed around the wire groove 28 of the rotating wheel 11 on the corresponding rotating wheel assembly, and then the wire rope 9 is hung on the hook 22, and the handle 14 is turned to gradually force the wire rope 9 until the hook of the aircraft hanging device 26 is unlocked. At this time, the external display device will record the force value. When measuring the explosive control force at another point or another angle, the explosive control ring 25 needs to be hung at another hook position and in the wire groove 28 of another corresponding rotating wheel 11.

[0032] The present invention utilizes a large base 1 and a small base 2 to support an aircraft suspension device 26, utilizes a positioning plate 27, a positioning bushing 5, and a ring 4 to simulate the installation state of the aircraft suspension device 26 on an aircraft to realize the positioning and fixing of the aircraft suspension device 26; utilizes a handle assembly to apply tension to a steel wire rope 9, so that the explosion control ring 25 pulls the hook of the aircraft suspension device 26 to unlock, and at this time the sensor 21 transmits the tension to a display device; utilizes a geometric angle between a rotating wheel assembly and the hook of the aircraft suspension device 26 as the angle required for measurement; utilizes a rotating wheel assembly to convert various force application angles into force in one direction; the present invention reduces the difficulty of operation for workers by measuring the explosion control force by placing the aircraft suspension device 26 horizontally on a pad 3; due to the improvement of the measurement angle accuracy, the measurement accuracy of the explosion control force value is also improved, and various difficulties encountered in the explosion control force measurement of a large aircraft suspension device 26 are completely solved.

Claims

1. A large aircraft suspension device explosion control force measurement device, characterized in that: The invention comprises an aircraft suspension device (26), a large base (1), a small base (2), a positioning plate (27), a positioning bushing (5), a ring (4), a rotating wheel assembly, a handle assembly and a plurality of explosion control rings (25). The large base (1) and the small base (2) are arranged in parallel. The large base (1) and the small base (2) are both provided with a plurality of movable cushion blocks (3). The two ends of the aircraft suspension device (26) are respectively provided on the cushion blocks (3) on the large base (1) and the small base (2). The explosion control ring (25) is hung on the hook of the aircraft suspension device (26). The positioning plate (27) is provided on the surface of the large base (1). The positioning bushing (5) is fixed on the positioning plate (27). The ring (4) is sleeved on the vertical shaft of the aircraft suspension device (26). The vertical shaft of the aircraft suspension device (26) is provided on the positioning bushing (5). ), the end face of the ring (4) is fitted with the end face of the positioning bushing (5), the large base (1) is provided with a plurality of parallel arranged rotary wheel assembly groups, each rotary wheel assembly group includes four rotary wheel assemblies, two of which are arranged in parallel close to the aircraft suspension device (26), and the two rotary wheel assemblies are spaced apart, the other two rotary wheel assemblies are arranged in parallel away from the aircraft suspension device (26), and the two rotary wheel assemblies are in contact with each other, and three groups of steel wire ropes (9) are fixed on each explosion control ring (25), two of which are respectively passed around the outer sides of the two rotary wheel assemblies close to the aircraft suspension device (26), and pass through the contact points of the two rotary wheel assemblies away from the aircraft suspension device (26), and are connected to the handle assembly arranged on the edge of the large base (1), and the other group of steel wire ropes (9) pass through the contact points of the two rotary wheel assemblies away from the aircraft suspension device (26), and are connected to the handle assembly; The rotating wheel assembly comprises a support shaft (10), a rotating wheel (11), and a fixed bearing (12); the rotating wheel (11) is fixed to the top of the support shaft (10) through the fixed bearing (12); a fastening nut (13) is arranged on the bottom end of the support shaft (10); and a wire groove (28) is arranged on the outer edge of the rotating wheel (11); The handle assembly comprises a base plate (15), a rolling bearing (24), a screw (18), a handle (14), a transfer nut (19), a transfer screw (20), a sensor (21) and a hook (22). The base plate (15) is fixed to the large base (1) through a pin hole and a pin. The rolling bearing (24) is installed in the mounting bearing hole of the base plate (15). The screw (18) is installed in the rolling bearing (24). One end of the screw (18) is connected to the handle (14) and the other end is connected to the transfer nut (19). The transfer nut (19) is connected to the transfer screw (20). The transfer screw (20) is connected to the sensor (21). The sensor (21) is connected to the hook (22). The two end surfaces of the rolling bearing (24) are fixed with bearing covers (17) through fixing screws (16).

2. The explosion control force measuring device for a large aircraft suspension device according to claim 1, characterized in that: The surface of the cushion block (3) is provided with a hard rubber plate.

3. The explosion control force measuring device for a large aircraft suspension device according to claim 1, characterized in that: The positioning plate (27) is fixed on the surface of the large base (1) by means of cylindrical pins (8) and screws (7).

4. The explosion control force measuring device for a large aircraft suspension device according to claim 1, characterized in that: A positioning nut (6) is provided on the positioning bushing (5).

5. The explosion control force measuring device for a large aircraft suspension device according to claim 1, characterized in that: The rotating wheel (11) of the rotating wheel assembly is at the same height as the rolling bearing (24) of the handle assembly.

6. The explosion control force measuring device for a large aircraft suspension device according to claim 1, characterized in that: The explosion control ring (25) is made of 2.5-3 mm steel wire wound on a steel structure plate.

7. The explosion control force measuring device for a large aircraft suspension device according to claim 1, characterized in that: The sensor (21) is connected to an external display device.

8. The explosion control force measuring device for a large aircraft suspension device according to claim 1, characterized in that: The screw rod (18) is provided with a key (23).

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