A kind of aircraft landing gear fixture

Abstract

The present application provides an aircraft landing gear fixture, comprising a clamping device; the clamping device comprises a fixture mounting plate; a rotation positioning device is provided on one side of the fixture mounting plate; the rotation positioning device comprises a rotary reducer and a servo motor; a pressure distribution device and a traveling clamp mounting plate are coaxially provided on both sides of the rotary reducer; a pressure distribution component is fixedly connected in the rotary center hole of the rotary reducer; one end of the pressure distribution component is rotatably connected to the pressure distribution device; the traveling clamp mounting plate is fixedly installed on the rotary reducer, and a traveling clamp is fixedly installed on the side away from the rotary reducer; the pressure distribution device is connected to the traveling clamp through a pipeline to adjust the pressure of the traveling clamp so that the traveling clamp is clamped / separated from the fixture mounting plate. The aircraft landing gear fixture can clamp the aircraft landing gear and has a rotation positioning function, which is convenient for the outer surface processing during the assembly of the landing gear, and is easy to install and can be quickly disassembled.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft landing gear, and in particular to an aircraft landing gear tooling fixture. Background Art

[0002] The landing gear is an accessory device at the bottom of the aircraft that is used to support the aircraft during takeoff and landing or taxiing on the ground (water surface) and is used for ground (water surface) movement. When processing and assembling the landing gear struts, a tooling fixture is required. Most of the existing assembly tooling fixtures are fixed fixtures, which can only play a clamping role and cannot drive the landing gear to rotate. However, when assembling the aircraft landing gear, it is sometimes necessary to process its outer surface. For example, it is necessary to drill multiple holes at intervals on the circumference of the outer tube of the landing gear strut, which requires it to be rotated. Therefore, it is of great significance to study an aircraft landing gear tooling fixture that can not only clamp the landing gear, but also drive the landing gear to rotate. Summary of the invention

[0003] The purpose of this application is to provide an aircraft landing gear fixture to address the above problems.

[0004] The present application provides an aircraft landing gear fixture, the landing gear comprising a first support arm and a second support arm, the fixture comprising a clamping device for clamping the first support arm and the second support arm; the clamping device comprises a fixture mounting plate; a rotation positioning device is provided on one side of the fixture mounting plate; the rotation positioning device comprises a rotary reducer and a servo motor driving the rotary reducer to rotate; a pressure distribution device and a traveling clamp mounting plate are coaxially provided on both sides of the rotary reducer; a rotary center hole of the rotary reducer is fixed A pressure distribution component is connected; the axis of the rotary center hole of the rotary reducer is colinear with the center axis of the landing gear; the pressure distribution component is in the shape of a hollow cylinder, one end of which is rotatably connected to the pressure distribution device; the traveling clamp mounting plate is fixedly installed on the rotary reducer, and a traveling clamp is fixedly installed on the side away from the rotary reducer; the pressure distribution device is connected to the traveling clamp through a pipeline to adjust the pressure of the traveling clamp so that the traveling clamp is clamped / separated from the tooling mounting plate.

[0005] According to the technical solution provided in certain embodiments of the present application, a first tooling and a second tooling are fixedly installed on the side of the tooling mounting plate away from the rotation positioning device; a first through hole is provided on the first tooling for the first arm to be inserted; a second through hole is provided on the second tooling for the second arm to be inserted; the second through hole and the second arm are fixedly connected by a tightening bolt and a lock nut.

[0006] According to the technical solution provided in certain embodiments of the present application, the second tooling includes a support arm and a clamping arm; the support arm and the clamping arm are detachably connected; one end of the support arm is fixedly connected to the tooling mounting plate, and the other end is provided with a guide pin; the clamping arm includes an integrally formed connecting portion and a clamping portion; the connecting portion and the clamping portion are vertically arranged; a pin hole for inserting the guide pin is provided on the connecting portion; the second through hole is provided on the clamping portion; the tightening bolt is provided at the end of the second support arm; the clamping portion is also connected to a fixing portion; a connecting through hole for inserting the tightening bolt is provided on the fixing portion; the aperture of the connecting through hole is smaller than the aperture of the second through hole.

[0007] According to the technical solution provided in certain embodiments of the present application, the first tool is fixedly mounted on the tool mounting plate by means of positioning pins and bolts.

[0008] According to the technical solution provided in certain embodiments of the present application, the pressure distribution device is an oil pressure distributor or a gas pressure distributor.

[0009] Compared with the prior art, the present application has the following beneficial effects: the aircraft landing gear fixture clamps and positions the first arm and the second arm of the aircraft landing gear through the clamping device, thereby achieving clamping of the aircraft landing gear; by arranging a servo motor, a rotary reducer, a pressure distribution device, a pressure distribution assembly, a traveling clamp mounting plate and a traveling clamp, when the aircraft landing gear needs to be rotated, the servo motor drives the rotary reducer to rotate, thereby driving the traveling clamp mounting plate to rotate, and then the aircraft landing gear fixed on the fixture mounting plate rotates together, and at the same time, the pressure distribution device and the pressure distribution assembly ensure the pressure supply to the traveling clamp, so that the traveling clamp and the fixture mounting plate are kept clamped; the rotation angle of the aircraft landing gear can be controlled by controlling the rotation angle of the servo motor, thereby achieving accurate rotation positioning of the aircraft landing gear; by arranging the traveling clamp, the fixture mounting plate of the clamping device and the rotation positioning device can be quickly disassembled and assembled. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 A schematic diagram of the three-dimensional structure of an aircraft landing gear fixture provided in an embodiment of the present application;

[0011] Figure 2 A schematic diagram of the structure of an aircraft landing gear fixture provided in an embodiment of the present application;

[0012] Figure 3 A schematic structural diagram of a rotation positioning device for an aircraft landing gear fixture provided in an embodiment of the present application;

[0013] Figure 4 A structural schematic diagram of a first fixture of an aircraft landing gear fixture provided in an embodiment of the present application;

[0014] Figure 5 A schematic structural diagram of a second tooling of an aircraft landing gear tooling fixture provided in an embodiment of the present application.

[0015] The text annotations in the figure represent:

[0016] 1. First support arm; 2. Second support arm; 3. Fixture mounting plate; 4. Rotary reducer; 5. Servo motor; 6. Pressure distribution device; 7. Travel clamp mounting plate; 8. Pressure distribution assembly; 9. Travel clamp; 10. First fixture; 11. First through hole; 12. Second through hole; 13. Jack bolt; 14. Lock nut; 15. Support arm; 16. Clamping arm; 17. Guide pin; 18. Fixing part; 19. Lock nut. DETAILED DESCRIPTION

[0017] In order to enable those skilled in the art to better understand the technical solution of the present application, the present application is described in detail below in conjunction with the accompanying drawings. The description in this section is only exemplary and explanatory and should not have any limiting effect on the scope of protection of the present application.

[0018] Please refer to Figures 1 to 3 The present embodiment provides a tooling fixture for an aircraft landing gear, the landing gear comprising a first arm 1 and a second arm 2, the tooling fixture comprising a clamping device for clamping the first arm 1 and the second arm 2; the clamping device comprises a tooling mounting plate 3; a rotation positioning device is provided on one side of the tooling mounting plate 3; the rotation positioning device comprises a rotary reducer 4 and a servo motor 5 for driving the rotary reducer 4 to rotate; a pressure distribution device 6 and a traveling clamp mounting plate 7 are coaxially provided on both sides of the rotary reducer 4; a pressure distribution assembly 8 is fixedly connected in the rotary center hole of the rotary reducer 4; the axis of the rotary center hole of the rotary reducer 4 is aligned with the axis of the aircraft landing gear The central axes of the landing frame are collinear; the pressure distribution assembly 8 is hollow cylindrical, one end of which is rotatably connected to the pressure distribution device 6; the accompanying clamp mounting plate 7 is fixedly installed on the rotary reducer 4 through a straight mouth and screws, and a accompanying clamp 9 is fixedly installed on the side away from the rotary reducer 4; the pressure distribution device 6 and the accompanying clamp 9 are connected by a pipeline to adjust the pressure of the accompanying clamp 9 so that the accompanying clamp 9 is clamped / separated from the tooling mounting plate 3, and the pipeline passes through the rotary center hole of the rotary reducer 4 and the through hole on the accompanying clamp mounting plate 7, one end of which is connected to the pressure distribution device 6, and the other end is connected to the accompanying clamp 9.

[0019] When in use, the first arm 1 and the second arm 2 of the aircraft landing gear are clamped and positioned by the clamping device, and the servo motor 5 drives the rotary reducer 4 to rotate, thereby driving the accompanying clamp mounting plate 7 to rotate, and then the aircraft landing gear fixed on the tooling mounting plate 3 rotates together. At the same time, the pressure distribution device 6 and the pressure distribution assembly 8 ensure the pressure supply to the accompanying clamp 9, so that the accompanying clamp 9 and the tooling mounting plate 3 are kept clamped, wherein the pressure distribution device 6 is kept stationary, and the pressure distribution assembly 8 and the accompanying clamp 9 move synchronously; the rotation angle of the aircraft landing gear can be controlled by controlling the rotation angle of the servo motor 5, thereby realizing accurate rotation positioning of the aircraft landing gear; by setting the accompanying clamp 9, the tooling mounting plate 3 of the clamping device and the rotation positioning device can be quickly disassembled and assembled, and the specific method is that the pressure distribution device 6 supplies pressure / relieves pressure to the accompanying clamp 9 through a pipeline, so that the accompanying clamp 9 and the tooling mounting plate 3 are clamped / separated.

[0020] Please refer to further Figure 4 and Figure 5 Preferably, a first tool 10 and a second tool are fixedly installed on one side of the tool mounting plate 3 away from the rotation positioning device; the first tool 10 and the second tool jointly realize the clamping and positioning of the aircraft landing gear; the first tool 10 is provided with a first through hole 11 for the first support arm 1 to be inserted; the second tool is provided with a second through hole 12 for the second support arm 2 to be inserted; the second through hole 12 and the second support arm 2 are fixedly connected by a tightening bolt 13 and a lock nut 14.

[0021] Preferably, the second tooling includes a support arm 15 and a clamping arm 16; the support arm 15 is used to compensate for the insufficient spatial length of the clamping arm 16; the support arm 15 and the clamping arm 16 are detachably connected; one end of the support arm 15 is fixedly connected to the tooling mounting plate 3, and the other end is provided with a guide pin 17; the clamping arm 16 includes an integrally formed connecting portion and a clamping portion; the connecting portion and the clamping portion are vertically arranged; a pin hole for inserting the guide pin 17 is provided on the connecting portion, and when in use, the clamping arm 16 is fixedly connected to the support arm 15 by cooperating with the guide pin 17 through a locking nut 19; the clamping portion is provided with the second through hole 12; the end of the second support arm 2 is provided with the tightening bolt 13; the clamping portion is also connected to a fixing portion 18; the fixing portion 18 is provided with a connecting through hole for inserting the tightening bolt 13; the aperture of the connecting through hole is smaller than the aperture of the second through hole 12.

[0022] The specific method and steps for clamping and fixing the aircraft landing gear with a clamping device are as follows:

[0023] S1, inserting the first arm 1 of the aircraft landing gear into the first through hole 11 of the first tool 10, completing the clamping of the first tool 10;

[0024] S2, insert the second arm 2 of the aircraft landing gear into the second through hole 12 on the second fixture clamping arm 16, and pass the jacking bolt 13 on the second arm 2 through the connecting through hole on the fixing part. At this time, the second arm 2 and the clamping arm 16 are not fixed tightly.

[0025] S3, tighten the locking nut 19 to fix the support arm 15 and the clamping arm 16;

[0026] S4, tighten the anti-loosening nut 14, thereby fixing the second support arm and the clamping arm 16, and completing the clamping and fixing of the aircraft landing gear.

[0027] Preferably, the first tool 10 is fixedly mounted on the tool mounting plate 3 by means of positioning pins and bolts.

[0028] Preferably, the pressure distribution device 6 is an oil pressure distributor or a gas pressure distributor. In the present embodiment, the pressure distribution device 6 used is an oil pressure distributor, and the oil pressure distributor supplies oil for the rotation of the pallet clamp.

[0029] The aircraft landing gear fixture provided in the embodiment of the present application can not only clamp the aircraft landing gear, but also has a rotation positioning function, which is convenient for the outer surface processing during the assembly of the aircraft landing gear; at the same time, it is easy to install and can achieve rapid disassembly and assembly.

[0030] This article uses specific examples to illustrate the principles and implementation methods of this application. The description of the above embodiments is only used to help understand the method and its core ideas of this application. The above is only the preferred implementation method of this application. It should be pointed out that due to the limitations of textual expression and the objective existence of infinite specific structures, ordinary technicians in this technical field can make several improvements, modifications or changes without departing from the principles of the present invention, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, should be regarded as the scope of protection of this application.

Claims

1. A fixture for an aircraft landing gear, the landing gear comprising a first arm (1) and a second arm (2), characterized in that: The fixture comprises a clamping device for clamping the first support arm (1) and the second support arm (2); the clamping device comprises a fixture mounting plate (3); a rotation positioning device is provided on one side of the fixture mounting plate (3); the rotation positioning device comprises a rotary reducer (4) and a servo motor (5) for driving the rotary reducer (4) to rotate; a pressure distribution device (6) and a traveling clamp mounting plate (7) are coaxially provided on both sides of the rotary reducer (4); a pressure distribution component (8) is fixedly connected to the rotary center hole of the rotary reducer (4); the rotary reducer (4) is provided with a pressure distribution component (8); The axis of the slewing center hole of the (4) is colinear with the center axis of the landing gear; the pressure distribution assembly (8) is in the shape of a hollow cylinder, one end of which is rotatably connected to the pressure distribution device (6); the accompanying clamp mounting plate (7) is fixedly mounted on the slewing reducer (4), and a accompanying clamp (9) is fixedly mounted on the side of the accompanying clamp (7) away from the slewing reducer (4); the pressure distribution device (6) and the accompanying clamp (9) are connected by a pipeline to adjust the pressure of the accompanying clamp (9) so that the accompanying clamp (9) and the tooling mounting plate (3) are clamped / separated; The pipeline passes through the rotary center hole of the rotary reducer (4) and the through hole on the portable clamp mounting plate (7), one end of which is connected to the pressure distribution device (6) and the other end of which is connected to the portable clamp (9); A first tool (10) and a second tool are fixedly mounted on a side of the tool mounting plate (3) away from the rotation positioning device; the first tool (10) is provided with a first through hole (11) for the first support arm (1) to be inserted; the second tool is provided with a second through hole (12) for the second support arm (2) to be inserted; the second through hole (12) and the second support arm (2) are fixedly connected via a tightening bolt (13) and a locking nut (14).

2. The aircraft landing gear fixture according to claim 1, characterized in that: The second tooling comprises a support arm (15) and a clamping arm (16); the support arm (15) and the clamping arm (16) are detachably connected; one end of the support arm (15) is fixedly connected to the tooling mounting plate (3), and the other end is provided with a guide pin (17); the clamping arm (16) comprises an integrally formed connecting portion and a clamping portion; the connecting portion and the clamping portion are vertically arranged; the connecting portion is provided with a pin hole for inserting the guide pin (17); the clamping portion is provided with the second through hole (12); the end of the second support arm (2) is provided with the tightening bolt (13); the clamping portion is also connected to a fixing portion (18); the fixing portion (18) is provided with a connecting through hole for inserting the tightening bolt (13); the hole diameter of the connecting through hole is smaller than the hole diameter of the second through hole (12).

3. The aircraft landing gear fixture according to claim 1, characterized in that: The first tool (10) is fixedly mounted on the tool mounting plate (3) by means of positioning pins and bolts.

4. The aircraft landing gear fixture according to claim 1, characterized in that: The pressure distribution device (6) is an oil pressure distributor or a gas pressure distributor.

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