Aircraft large wing supporting device

Abstract

The utility model relates to the technical field of aircraft maintenance, in particular to an aircraft large wing supporting device which comprises a fixing frame, the fixing frame is an isosceles trapezoid support composed of a top plate, a bottom plate and two inclined plates, a supporting cross beam is arranged on the fixing frame, and a lifting assembly used for driving the supporting cross beam to ascend and descend is arranged on the fixing frame. One end of the supporting beam is provided with a first supporting structure used for supporting the wide end of the large wing of the airplane, and the other end of the supporting beam is provided with a second supporting structure used for supporting the narrow end of the large wing of the airplane. The large wing supporting device for aircraft maintenance has the advantages that the problems that supporting points of the large wing supporting device for aircraft maintenance are too many, and sight is blocked are solved, and the teaching display requirement can be met.

Description

Technical Field

[0001] This utility model relates to the field of aircraft maintenance technology, and in particular to an aircraft wing support device. Background Technology

[0002] With the rapid development of general aviation aircraft in my country, the daily maintenance and repair of general aviation aircraft is becoming increasingly important. For those who have just joined the maintenance work, systematic training is needed to improve their knowledge and skills of general aviation aircraft. This includes the repair of the wingtip lighting control components of the aircraft wing. However, during the training process, there is a lack of information about the overall support structure of the aircraft wing, making it difficult to disassemble the aircraft wing and to demonstrate the overall installation and wiring of the aircraft wing.

[0003] The existing Chinese patent, CN210790891U, discloses a maintenance workbench for aircraft wings and horizontal stabilizers, including a maintenance platform mechanism, a lifting drive mechanism, and a mobile support mechanism. The maintenance platform mechanism includes a maintenance operating platform, four side guardrails, and two release and positioning structures. The lifting drive mechanism adjusts the height of the maintenance operating platform, and the mobile support mechanism adjusts the horizontal position of the lifting drive mechanism and the maintenance operating platform. Although this maintenance workbench has lifting and moving functions, its platform design still has the problem of too many support points and obstruction of the view, making it difficult to meet the needs of teaching and demonstration. Utility Model Content

[0004] In order to improve the problem of excessive support points and obstructed vision in aircraft maintenance wing support equipment, and to make it able to meet the needs of teaching and demonstration, this application provides an aircraft wing support device.

[0005] The aircraft wing support device provided in this application adopts the following technical solution:

[0006] An aircraft wing support device includes a fixed frame, which is an isosceles trapezoidal support consisting of a top plate, a bottom plate, and two inclined plates. A support beam is provided on the fixed frame, and a lifting assembly for driving the support beam to rise and fall is provided on the fixed frame. One end of the support beam is provided with a first support structure for supporting the wide end of the aircraft wing, and the other end of the support beam is provided with a second support structure for supporting the narrow end of the aircraft wing.

[0007] Preferably, the lifting assembly includes a fixed bearing, a first threaded rod, a first threaded sleeve, a handle, and a limiting block. The fixed bearing is mounted on the base plate. One end of the first threaded rod is connected to the fixed bearing. The first threaded rod is arranged in a direction perpendicular to the base plate. The handle is fixedly connected to the first threaded rod. The first threaded sleeve is threaded onto the first threaded rod. The top plate has an installation hole for the first threaded sleeve to pass through. The end of the first threaded sleeve passing through the installation hole is connected to a support beam. The limiting block is fixedly connected to the installation hole. The first threaded sleeve has a slot for the limiting block to slide. The side wall of the limiting block slides against the inner wall of the slot.

[0008] Preferably, a linear bearing is connected inside the mounting hole, and the first threaded sleeve passes through the linear bearing.

[0009] Preferably, a rib is fixedly connected between the first threaded sleeve and the supporting crossbeam, and one rib is provided on each side of the first threaded sleeve.

[0010] Preferably, the first support structure includes a first fixing block, a first support plate, and a rubber pad. The first fixing block is fixedly connected to the support beam, the first support plate is fixedly connected to the first fixing block, the first support plate is an arc-shaped plate, the arc of the first support plate is adapted to the aircraft wing, and the rubber pad is adhered to the first support plate and is located on the surface of the first support plate facing the aircraft wing.

[0011] Preferably, the second support structure includes a second fixing block, a second support plate, a positioning plate, a mounting plate, a mounting bearing, a second threaded rod, a second threaded sleeve, a turntable, a guide rod, and a clamping plate. The second fixing block is fixedly connected to the support beam, the second support plate is fixedly connected to the second fixing block, and the second support plate is a straight plate. The positioning plate is fixedly connected to the second support plate and is arranged in a direction perpendicular to the second support plate. The mounting plate is fixedly connected to the second support plate and is arranged in a direction perpendicular to the second support plate and parallel to the positioning plate. The mounting bearing is connected to the mounting plate, the second threaded rod passes through the mounting bearing, the turntable is connected to the end of the second threaded rod facing away from the positioning plate, the second threaded sleeve is threaded onto the second threaded rod, and the second threaded sleeve is connected to the clamping plate. The clamping plate is adapted to the side of the aircraft wing and is inclined. The guide rod is fixedly connected to the clamping plate and is parallel to the second threaded sleeve. The mounting plate has a guide hole for the guide rod to pass through, and the guide rod has one on each side of the second threaded sleeve.

[0012] Preferably, the base plate is connected to casters, the casters have a built-in foot-operated locking structure, and one caster is provided at each of the four corners of the base plate.

[0013] In summary, this application includes the following beneficial technical effects:

[0014] This utility model provides an aircraft wing support device, which features a liftable support beam mounted on a fixed frame. The support beam has raised first and second support structures at both ends, supporting both ends of the aircraft wing. This design minimizes contact points and creates an open structure, avoiding obstruction of wiring on the wing surface and facilitating observation of internal component installation and cable routing by trainees. Furthermore, the fixed frame includes casters with built-in foot-operated locking mechanisms, allowing for easy movement of the structure to suitable positions. This design effectively addresses the problem of excessive support points and obstructed visibility in aircraft maintenance wing support equipment, thus meeting the needs of teaching and demonstration. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the structure of the aircraft wing support device in the embodiments of this application;

[0016] Figure 2 This is a schematic diagram illustrating the limiting block in an embodiment of this application;

[0017] Figure 3 yes Figure 1 Enlarged view of point A in the middle.

[0018] Explanation of reference numerals in the attached drawings: 100, fixed frame; 110, top plate; 111, linear bearing; 120, bottom plate; 121, caster wheel; 130, inclined plate; 200, support beam; 300, lifting assembly; 310, fixed bearing; 320, first threaded rod; 330, first threaded sleeve; 331, rib plate; 340, handle; 350, limiting block; 400, first support structure; 410, first fixing block; 420, first support plate; 430, rubber pad; 500, second support structure; 501, second fixing block; 502, second support plate; 503, positioning plate; 504, mounting plate; 505, mounting bearing; 506, second threaded rod; 507, second threaded sleeve; 508, turntable; 509, guide rod; 510, clamping plate. Detailed Implementation

[0019] To enable those skilled in the art to better understand the present invention, the solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of the present invention.

[0020] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation or specific orientation structure and operation, and therefore should not be construed as a limitation of this utility model; the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. In addition, unless otherwise explicitly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. For those skilled in the art, the specific meaning of the above terms in this utility model can be understood according to the specific circumstances.

[0021] This application discloses an aircraft wing support device. (Refer to...) Figure 1 , Figure 2 and Figure 3 The aircraft wing support device includes a fixed frame 100, which is an isosceles trapezoidal support consisting of a top plate 110, a bottom plate 120, and two inclined plates 130. A support beam 200 is provided on the fixed frame 100, and a lifting assembly 300 for driving the support beam 200 to rise and fall is provided on the fixed frame 100. One end of the support beam 200 is provided with a first support structure 400 for supporting the wide end of the aircraft wing, and the other end of the support beam 200 is provided with a second support structure 500 for supporting the narrow end of the aircraft wing.

[0022] The lifting assembly 300 includes a fixed bearing 310, a first threaded rod 320, a first threaded sleeve 330, a handle 340, and a limiting block 350. The fixed bearing 310 is mounted on the base plate 120. One end of the first threaded rod 320 is connected to the fixed bearing 310. The first threaded rod 320 is arranged in a direction perpendicular to the base plate 120. The handle 340 is fixedly connected to the first threaded rod 320. The first threaded sleeve 330 is threaded onto the first threaded rod 320. The top plate 110 has an installation hole for the first threaded sleeve 330 to pass through. The end of the first threaded sleeve 330 passing through the installation hole is connected to the support beam 200. The limiting block 350 is fixedly connected to the installation hole. The first threaded sleeve 330 has a slot for the limiting block 350 to slide. The side wall of the limiting block 350 slides against the inner wall of the slot.

[0023] A linear bearing 111 is connected inside the mounting hole, and the first threaded sleeve 330 passes through the linear bearing 111. By setting the linear bearing 111, it is beneficial to improve the stability of the first threaded sleeve 330 when it is raised or lowered.

[0024] A rib plate 331 is fixedly connected between the first threaded sleeve 330 and the supporting beam 200. A rib plate 331 is provided on each side of the first threaded sleeve 330. By setting the rib plate 331, it is beneficial to improve the stability and strength of the structure between the first threaded sleeve 330 and the supporting beam 200.

[0025] The first support structure 400 includes a first fixing block 410, a first support plate 420, and a rubber pad 430. The first fixing block 410 is fixedly connected to the support beam 200, and the first support plate 420 is fixedly connected to the first fixing block 410. The first support plate 420 is an arc-shaped plate, and the curvature of the first support plate 420 is adapted to the aircraft wing. The rubber pad 430 is bonded to the first support plate 420 and is located on the surface of the first support plate 420 facing the aircraft wing.

[0026] The second support structure 500 includes a second fixing block 501, a second support plate 502, a positioning plate 503, a mounting plate 504, a mounting bearing 505, a second threaded rod 506, a second threaded sleeve 507, a turntable 508, a guide rod 509, and a clamping plate 510. The second fixing block 501 is fixedly connected to the support beam 200. The second support plate 502 is fixedly connected to the second fixing block 501 and is a straight plate. The positioning plate 503 is fixedly connected to the second support plate 502 and is arranged in a direction perpendicular to the second support plate 502. The mounting plate 504 is fixedly connected to the second support plate 502 and is arranged in a direction perpendicular to the second support plate 502. Parallel to the positioning plate 503, the mounting bearing 505 is connected to the mounting plate 504. The second threaded rod 506 passes through the mounting bearing 505. The turntable 508 is connected to the end of the second threaded rod 506 facing away from the positioning plate 503. The second threaded sleeve 507 is threaded onto the second threaded rod 506. The second threaded sleeve 507 is connected to the clamping plate 510. The clamping plate 510 is adapted to the side of the aircraft wing and is set at an angle. The guide rod 509 is fixedly connected to the clamping plate 510. The guide rod 509 and the second threaded sleeve 507 are set parallel to each other. The mounting plate 504 has a guide hole for the guide rod 509 to pass through. The guide rod 509 is provided on both sides of the second threaded sleeve 507.

[0027] The base plate 120 is connected to casters 121, which have a built-in foot-operated locking structure. There is one caster 121 at each of the four corners of the base plate 120. By setting the casters 121 with built-in foot-operated locking structures, the equipment can be moved and stopped stably.

[0028] The implementation principle of an aircraft wing support device according to an embodiment of this application is as follows: During operation, the support device is first moved to the underside of the aircraft wing, and then the caster wheel 121 is locked. Next, the handle 340 and the first threaded rod 320 are manually rotated. Under the guiding and limiting action of the limiting block 350, the first threaded sleeve 330 can move along the length direction of the first threaded rod 320, so that the support beam 200 rises, and the first support plate 420 and the second support plate 502 are both against the underside of the aircraft wing. Then, the turntable 508 and the second threaded rod 506 are rotated. Under the guiding and limiting action of the guide rod 509, the second threaded sleeve 507 can move along the length direction of the second threaded rod 506, so that the clamping plate 510 cooperates with the positioning plate 503 to clamp and fix the narrow end of the aircraft wing.

[0029] Finally, it should be noted that the above description is only a preferred embodiment of this utility model, and the protection scope of this utility model is not limited to the above embodiments. All technical solutions within the scope of this utility model's concept are within the protection scope of this utility model. It should be pointed out that for those skilled in the art, any improvements and modifications made without departing from the principle of this utility model should also be considered within the protection scope of this utility model.

Claims

1. A support device for an aircraft wing, characterized in that: The device includes a fixed frame (100), which is an isosceles trapezoidal support consisting of a top plate (110), a bottom plate (120), and two inclined plates (130). A support beam (200) is provided on the fixed frame (100), and a lifting assembly (300) for driving the support beam (200) to rise and fall is provided on the fixed frame (100). One end of the support beam (200) is provided with a first support structure (400) for supporting the wide end of the aircraft wing, and the other end of the support beam (200) is provided with a second support structure (500) for supporting the narrow end of the aircraft wing.

2. The aircraft wing support device according to claim 1, characterized in that: The lifting assembly (300) includes a fixed bearing (310), a first threaded rod (320), a first threaded sleeve (330), a handle (340), and a limiting block (350). The fixed bearing (310) is mounted on the base plate (120). One end of the first threaded rod (320) is connected to the fixed bearing (310). The first threaded rod (320) is arranged in a direction perpendicular to the base plate (120). The handle (340) is fixedly connected to the first threaded rod (320). The first threaded sleeve (330) is threaded onto the first threaded rod (320). The top plate (110) has an installation hole through which the first threaded sleeve (330) passes. The end of the first threaded sleeve (330) passing through the installation hole is connected to the support beam (200). The limiting block (350) is fixedly connected to the installation hole. The first threaded sleeve (330) has a slot for the limiting block (350) to slide. The side wall of the limiting block (350) slides against the inner wall of the slot.

3. The aircraft wing support device according to claim 2, characterized in that: A linear bearing (111) is connected inside the mounting hole, and the first threaded sleeve (330) passes through the linear bearing (111).

4. The aircraft wing support device according to claim 2, characterized in that: A rib (331) is fixedly connected between the first threaded sleeve (330) and the supporting crossbeam (200), and the rib (331) is provided on both sides of the first threaded sleeve (330).

5. The aircraft wing support device according to claim 1, characterized in that: The first support structure (400) includes a first fixing block (410), a first support plate (420), and a rubber pad (430). The first fixing block (410) is fixedly connected to the support beam (200), and the first support plate (420) is fixedly connected to the first fixing block (410). The first support plate (420) is an arc-shaped plate, and the curvature of the first support plate (420) is adapted to the large wing of the aircraft. The rubber pad (430) is bonded to the first support plate (420) and is located on the surface of the first support plate (420) facing the large wing of the aircraft.

6. The aircraft wing support device according to claim 1, characterized in that: The second support structure (500) includes a second fixing block (501), a second support plate (502), a positioning plate (503), a mounting plate (504), a mounting bearing (505), a second threaded rod (506), a second threaded sleeve (507), a turntable (508), a guide rod (509), and a clamping plate (510). The second fixing block (501) is fixedly connected to the support beam (200), and the second support plate (502) is fixedly connected to the second fixing block (501). The second support plate (502) is a straight plate. The positioning plate (503) is fixedly connected to the second support plate (502) and is arranged in a direction perpendicular to the second support plate (502). The mounting plate (504) is fixedly connected to the second support plate (502) and is arranged in a direction perpendicular to the second support plate (502). The mounting bearing (505) is connected to the mounting plate (504) and parallel to the positioning plate (503). The second threaded rod (506) passes through the mounting bearing (505). The turntable (508) is connected to the end of the second threaded rod (506) facing away from the positioning plate (503). The second threaded sleeve (507) is threaded onto the second threaded rod (506). The second threaded sleeve (507) is connected to the clamping plate (510). The clamping plate (510) is adapted to the side of the aircraft wing and is inclined. The guide rod (509) is fixedly connected to the clamping plate (510). The guide rod (509) and the second threaded sleeve (507) are parallel to each other. The mounting plate (504) has a guide hole for the guide rod (509) to pass through. The guide rod (509) is provided on both sides of the second threaded sleeve (507).

7. The aircraft wing support device according to claim 1, characterized in that: The base plate (120) is connected to a caster wheel (121), which has a foot-operated locking structure. The caster wheel (121) is located at one of the four corners of the base plate (120).

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