Heavy-load bracket for aircraft maintenance and aircraft component consignment device

Abstract

The utility model provides a heavy-load bracket for aircraft maintenance and an aircraft component consignment device. The heavy-load bracket for aircraft maintenance comprises a bottom supporting plate, a main bearing frame body, an auxiliary supporting rod and a plurality of adaptive limiting structures. The main bearing frame body is fixedly arranged on the bottom supporting plate, an undercarriage horizontal table is arranged on the main bearing frame body, and a main support of the undercarriage is placed through the undercarriage horizontal table; the plurality of adaptive limiting structures are fixedly arranged on the main bearing frame body and are dispersedly arranged on the peripheral side of the undercarriage horizontal table; the auxiliary supporting rod is vertically arranged on the main bearing frame body and located in the swinging direction of a side auxiliary support of the undercarriage. The auxiliary supporting rod is fixedly connected to the main bearing frame body, and the auxiliary supporting rod supports and locks the side auxiliary support connected with the undercarriage, so that the main support and the side auxiliary support are kept relatively static, and finally the situation that the side auxiliary support swings relative to the main support to injure workers accidentally is reduced.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the technical field of aircraft maintenance equipment, in particular to a heavy load bracket for aircraft maintenance and an aircraft component carrying device. BACKGROUND

[0002] The landing gear is a support component when the aircraft takes off or lands. Please refer to Figure 1 In order to enhance the load-bearing capacity of the landing gear, the landing gear usually includes a main support 10 and a side support 20 connected by rotation, and a triangular structure is formed by rotating and unfolding between the main support 10 and the side support 20, so that the aircraft can be stably supported. Among them, as the main load-bearing component, it is also more likely to be damaged in use. In order to improve the maintenance efficiency of the landing gear, some manufacturers will use a landing gear storage vehicle such as disclosed in Chinese patent document CN216883894U, but due to the structure limitation of the main support 10 and the side support 20 in the landing gear Figure 1 , the landing gear is difficult to be placed stably on the vehicle plate, and the side support 20 is easy to swing relative to the main support 10 and injure the staff. CONTENT OF THE UTILITY MODEL

[0003] The purpose of the present disclosure is to overcome the shortcomings in the prior art, and to provide a heavy load bracket for aircraft maintenance and an aircraft component carrying device which can fix the main support and the side support to facilitate the staff to carry the landing gear.

[0004] The purpose of the present disclosure is achieved by the following technical solutions:

[0005] A heavy load bracket for aircraft maintenance, comprising a bottom supporting plate for adapting to the forks of a forklift;

[0006] The heavy load bracket for aircraft maintenance further comprises a main load-bearing frame, a side support rod and a plurality of adaptive limiting structures;

[0007] The main load-bearing frame is fixedly arranged on the bottom supporting plate, and the main load-bearing frame has a landing gear flat table for placing the main support of the landing gear. A plurality of adaptive limiting structures are fixedly arranged on the main load-bearing frame and are dispersedly arranged on the circumferential side of the landing gear flat table. Each adaptive limiting structure is adapted and clamped to the main support of the landing gear, so that the main support of the landing gear is fixed on the landing gear flat table. The side support rod is vertically arranged on the main load-bearing frame and located in the swinging direction of the side support of the landing gear. The side support rod is fixedly connected to the main load-bearing frame, and the side support rod is used to support and lock the side support of the landing gear, so that the main support and the side support remain relatively stationary.

[0008] In some embodiments, the main load-bearing frame body comprises a load-bearing base plate and a lifting frame; the load-bearing base plate is arranged on the bottom support plate and welded with the surface of the bottom support plate; the lifting frame is detachably mounted on the load-bearing base plate and forms the landing gear flat table; the auxiliary support rod is fixedly arranged on the load-bearing base plate, and a plurality of adaptive limiting structures are fixedly arranged on the lifting frame.

[0009] In some embodiments, the lifting frame is a triangular frame.

[0010] In some embodiments, the triangular frame is a right-angled triangular frame, two right-angle sides of the right-angled triangular frame are respectively fitted on the surface of the load-bearing base plate; the hypotenuse of the right-angled triangular frame is located outside the load-bearing base plate and is flat above the bottom support plate to form a supporting and lifting part.

[0011] In some embodiments, the main load-bearing frame body further comprises a plurality of limiting abutting components; a part of the limiting abutting components are distributed in the triangular frame and abut against the inner frame edge of the triangular frame; another part of the limiting abutting components are located outside the triangular frame and abut against the outer frame edge of the triangular frame.

[0012] In some embodiments, the limiting abutting component is a limiting block, a clamping notch is formed on the limiting block; the limiting block is located outside the triangular frame and is matched with the corner of the triangular frame through the clamping notch.

[0013] In some embodiments, the limiting block is provided with a sliding abutting block and a locking screw head; the sliding abutting block is slidingly connected to the limiting block, and the sliding direction of the sliding abutting block is towards the landing gear flat table; the locking screw head is threadedly connected to the limiting block and locks the sliding abutting block.

[0014] In some embodiments, the auxiliary support rod comprises a rod body and a bolt body; the rod body is fixedly connected to the main load-bearing frame body and vertically extends to form a support part, the support part is used for supporting the side auxiliary support of the landing gear; the bolt body is threadedly connected to the support part, and the bolt body is used for locking and fixing the side auxiliary support.

[0015] In some embodiments, the bottom of the bottom support plate is fixedly provided with a pad block, the pad block is used for forming an insertion gap between the bottom support plate and the ground.

[0016] An aircraft component shipping device comprises a forklift and a heavy load carrier for aircraft maintenance according to any one of the above embodiments; the bottom support plate is adapted to the pallet fork of the forklift.

[0017] Compared with the prior art, the present disclosure has at least the following advantages:

[0018] The heavy-duty bracket for aircraft maintenance described above has the following advantages. Firstly, the main load-bearing frame body is provided with a plurality of adaptive limiting structures, which are installed on the periphery of the landing gear flat table. When the main support of the landing gear is placed in the landing gear flat table, the adaptive limiting structures can adapt to the external structure of the main support, so that the main support can be fixed on the landing gear flat table by the clamping action of the adaptive limiting structures, so that the main support can be placed flat and stably on the main load-bearing frame body. Secondly, the vertical auxiliary support rod of the main load-bearing frame body is located in the swinging direction of the side auxiliary support of the landing gear, so that after the main support is placed, the side auxiliary support can be swung relative to the main support, so that the side auxiliary support is supported by the auxiliary support rod, and then the side auxiliary support is connected by the auxiliary support rod, so that the position of the side auxiliary support is fixed, that is, the main support and the side auxiliary support remain relatively stationary, and finally the situation that the side auxiliary support easily swings relative to the main support and accidentally injures the worker is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the following will briefly introduce the drawings needed to be used in the embodiments. It should be understood that the following drawings only show some embodiments of the present disclosure, and therefore should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can also be obtained without creative labor.

[0020] Figure 1 The structure of the existing landing gear is shown in the figure;

[0021] Figure 2 The structure of the heavy-duty bracket for aircraft maintenance according to an embodiment of the present disclosure is shown in the figure;

[0022] Figure 3 The structure of the heavy-duty bracket for aircraft maintenance is shown in the figure; Figure 2 The partial cross-sectional structure of the heavy-duty bracket for aircraft maintenance is shown in the figure;

[0023] Figure 4 The structure of the heavy-duty bracket for aircraft maintenance is shown in the figure; Figure 2 The structure of the heavy-duty bracket for aircraft maintenance is shown in the figure.

[0024] Reference signs:

[0025] 10, main support; 20, side auxiliary support; 30, wheel;

[0026] 100, bottom support plate;

[0027] 200, main load-bearing frame body; 210, load-bearing base plate; 220, right triangle frame; 2210, right angle side; 2220, hypotenuse; 2230, corner position; 230, limiting block; 2310, clamping notch; 240, hook-shaped pressing plate; 250, abutting block; 260, sliding abutting block; 270, locking screw head;

[0028] 300, auxiliary support rod; 310, rod body; 3110, support part; 3101, screw hole; 320, bolt body;

[0029] 400, adaptive limiting structure;

[0030] 500, cushioning block. DETAILED DESCRIPTION

[0031] For the purpose of promoting the understanding of the present disclosure, the present disclosure will be more fully described by referring to the accompanying drawings. The preferred embodiments of the present disclosure are shown in the drawings. However, the present disclosure can be realized in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and fully convey the scope of the present disclosure to those skilled in the art.

[0032] It should be noted that when an element is referred to as being "on" another element, it can be directly on the other element or intervening elements can also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements can also be present. The terms "vertical", "horizontal", "left", "right" and similar expressions as used herein are for the purpose of illustration only and are not intended to limit the present disclosure.

[0033] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this disclosure belongs. The terminology used in the description of the disclosure herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. As used herein, the term "and / or" includes any and all combinations of one or more of the associated listed items.

[0034] In order to better understand the technical solutions and beneficial effects of the present disclosure, the present disclosure will be further described in detail below in conjunction with specific embodiments:

[0035] Please refer to Figure 1 With Figure 2The heavy-duty bracket for aircraft maintenance in an embodiment comprises a bottom supporting plate 100, a main load-bearing frame 200, a secondary support rod 300 and a plurality of adaptive limiting structures 400. The bottom supporting plate 100 is adapted to the forks of a forklift. The main load-bearing frame 200 is fixedly arranged on the bottom supporting plate 100, and the main load-bearing frame 200 has a landing gear flat table for placing the main support 10 of the landing gear. The plurality of adaptive limiting structures 400 are fixedly arranged on the main load-bearing frame 200 and are dispersedly arranged on the circumferential side of the landing gear flat table. Each adaptive limiting structure 400 is adapted to and clamped to the main support 10 of the landing gear, so as to fix the main support 10 of the landing gear on the landing gear flat table. The secondary support rod 300 is vertically arranged on the main load-bearing frame 200 and is located in the swinging direction of the side secondary support 20 of the landing gear. The secondary support rod 300 is fixedly connected to the main load-bearing frame 200 and is used for supporting and locking the side secondary support 20 of the landing gear, so as to keep the main support 10 and the side secondary support 20 relatively stationary.

[0036] It can be understood that, since the main load-bearing frame 200 is fixedly provided with a plurality of adaptive limiting structures 400, and the plurality of adaptive limiting structures 400 are dispersedly arranged on the circumferential side of the landing gear flat table, when the main support 10 of the landing gear is placed in the landing gear flat table, the adaptive limiting structures 400 can be adapted to the external structure of the main support 10, so as to fix the main support 10 on the landing gear flat table through the clamping action of the adaptive limiting structures 400, so that the main support 10 can be placed flat and stably on the main load-bearing frame 200. Since the vertically arranged secondary support rod 300 on the main load-bearing frame 200 is located in the swinging direction of the side secondary support 20 of the landing gear, after the main support 10 is placed, the side secondary support 20 can be swung relative to the main support 10, so that the side secondary support 20 is supported by the secondary support rod 300, and then the side secondary support 20 is locked by the secondary support rod 300, so that the position of the side secondary support 20 is fixed, i.e., the main support 10 and the side secondary support 20 are kept relatively stationary, and finally the situation that the side secondary support 20 swings relative to the main support 10 and accidentally injures the staff is reduced.

[0037] Please refer to Figure 1 and Figure 2In some embodiments, the main load-bearing frame 200 includes a load-bearing base plate 210 and a lifting frame. The load-bearing base plate 210 is arranged on the bottom support plate 100 and is welded to the surface of the bottom support plate 100. The lifting frame is detachably mounted on the load-bearing base plate 210 and forms a landing gear flat table. The auxiliary support rod 300 is fixedly arranged on the load-bearing base plate 210, and the plurality of adaptive limiting structures 400 are fixedly arranged on the lifting frame. It can be understood that, since the load-bearing base plate 210 is welded to the surface of the bottom support plate 100, a stable connection between the load-bearing base plate 210 and the bottom support plate 100 is formed. The auxiliary support rod 300 is fixedly arranged on the load-bearing base plate 210, and the adaptive limiting structure 400 is fixedly arranged on the lifting frame. The lifting frame is detachably mounted on the load-bearing base plate 210. When the landing gear needs to be unloaded, the support and connection between the auxiliary support rod 300 and the side auxiliary support 20 of the landing gear can be first released. At this time, the main support 10 of the landing gear can still be clamped and fixed by the plurality of adaptive limiting structures 400, and the entire landing gear can be stably lifted for subsequent replacement operation. In this embodiment, the number of adaptive limiting structures 400 includes at least two. The protruding part of at least one adaptive limiting structure 400 is adapted to the gap between the two wheels 30 on the main support 10, and the protruding part of at least one adaptive limiting structure 400 is inserted into the hollow part on the main support 10.

[0038] Referring to Figure 1 and Figure 2 In some embodiments, the lifting frame is a triangular frame. It can be understood that, when the lifting frame is a triangular frame, the structural stability of the triangular frame is stronger, so that the triangular frame can stably support the main support 10 of the landing gear.

[0039] Referring to Figure 1 and Figure 2 In some embodiments, the triangular frame is a right-angled triangular frame 220, and two right-angle sides 2210 of the right-angled triangular frame 220 are respectively attached to the surface of the load-bearing base plate 210. The hypotenuse 2220 of the right-angled triangular frame 220 is located outside the load-bearing base plate 210 and is placed above the bottom support plate 100 to form a supporting and lifting part. It can be understood that, since the two right-angle sides 2210 of the right-angled triangular frame 220 are respectively attached to the surface of the load-bearing base plate 210, the two right-angle sides 2210 of the right-angled triangular frame 220 can be supported by the load-bearing base plate 210, so that the load-bearing base plate 210 stably raises the right-angled triangular frame 220. At this time, the hypotenuse 2220 of the right-angled triangular frame 220 is located outside the load-bearing base plate 210 and is placed above the bottom support plate 100. When the landing gear needs to be unloaded, the connection between the right-angled triangular frame 220 and the load-bearing base plate 210 can be released, and then force can be applied to the supporting and lifting part formed on the hypotenuse 2220 of the right-angled triangular frame 220 to unload the right-angled triangular frame 220 together with the landing gear.

[0040] In some embodiments, the main load-bearing frame 200 further comprises a plurality of position-limiting abutting components; a portion of the position-limiting abutting components are distributed within the triangular frame and abut against the inner frame edges of the triangular frame; another portion of the position-limiting abutting components are located outside the triangular frame and abut against the outer frame edges of the triangular frame. It can be understood that by abutting a portion of the position-limiting abutting components against the inner frame edges of the triangular frame and by abutting another portion of the position-limiting abutting components against the outer frame edges of the triangular frame, i.e., by the position-limiting abutting components arranged inside and outside the triangular frame collectively abutting and fixing the triangular frame, the triangular frame can be pulled out from above, thereby releasing the fixation of the triangular frame by the position-limiting abutting components and facilitating the quick disassembly of the triangular frame.

[0041] Referring to Figure 2 and Figure 3 In some embodiments, the position-limiting abutting component is a position-limiting block 230, and the position-limiting block 230 is formed with a clamping notch 2310; the position-limiting block 230 is located outside the triangular frame and is fitted to the corner position 2230 of the triangular frame through the clamping notch 2310. It can be understood that by fitting the clamping notch 2310 formed on the position-limiting block 230 to the corner position 2230 of the triangular frame, the position of the triangular frame can be limited by the position-limiting block 230, thereby enabling the triangular frame to be detachably mounted on the load-bearing base plate 210. In other embodiments, the position-limiting abutting component can also be a conventional hook-shaped pressing plate 240 or an abutting block 250, which will not be described here.

[0042] Referring to Figure 2 and Figure 4 In some embodiments, the position-limiting block 230 is provided with a sliding abutting block 260 and a locking screw head 270; the sliding abutting block 260 is slidingly connected to the position-limiting block 230, and the sliding direction of the sliding abutting block 260 is toward the landing gear flat table; the locking screw head 270 is threadedly connected to the position-limiting block 230 and locks the sliding abutting block 260. It can be understood that since the sliding abutting block 260 is slidingly connected to the position-limiting block 230, after the main support 10 of the landing gear is placed on the landing gear flat table, the sliding abutting block 260 can be further abutted against the main support 10 of the landing gear by pushing the sliding abutting block 260 to slide toward the landing gear flat table; at this time, the position of the sliding abutting block 260 can be fixed by threadedly connecting the locking screw head 270 to the position-limiting block 230 to lock the sliding abutting block 260.

[0043] Referring to Figures 1 to 3In some embodiments, the auxiliary support rod 300 comprises a rod body 310 and a bolt body 320; the rod body 310 is fixedly connected to the main load-bearing frame body 200 and vertically extends to form a support portion 3110, which is used to support the side auxiliary support 20 of the landing gear; the bolt body 320 is threadedly connected to the support portion 3110, and the bolt body 320 is used to lock and fix the side auxiliary support 20. It can be understood that, since the rod body 310 fixed on the main load-bearing frame body 200 vertically extends to form the support portion 3110, the side auxiliary support 20 of the landing gear can be supported by the support portion 3110 after the side auxiliary support 20 swings relative to the main support 10, and then the threaded rod portion of the bolt body 320 penetrates the through hole on the side auxiliary support 20 of the landing gear and is threadedly connected to the support portion 3110, so that the bolt body 320 can firmly lock and fix the side auxiliary support 20 on the support portion 3110. Specifically, the end portion of the support portion 3110 is provided with a threaded hole 3101 which can threadedly cooperate with the bolt body 320.

[0044] Referring to Figure 2 With Figure 3 In some embodiments, the bottom of the bottom supporting plate 100 is fixedly provided with a lifting block 500, which is used to form an insertion gap between the bottom supporting plate 100 and the ground. It can be understood that, by fixedly providing the lifting block 500 at the bottom of the bottom supporting plate 100, the lifting block 500 can support the bottom supporting plate 100, so as to form an insertion gap between the bottom supporting plate 100 and the ground, which is more convenient for the forks of the forklift to penetrate, so as to more quickly load and unload the heavy-duty carrier for aircraft maintenance.

[0045] Referring to Figure 2 An aircraft part transporting device comprises a forklift and the heavy-duty carrier for aircraft maintenance of any of the above embodiments; the bottom supporting plate 100 is adapted to the forks of the forklift. It can be understood that, by applying the heavy-duty carrier for aircraft maintenance of the present disclosure to the aircraft part transporting device, and by adapting the bottom supporting plate 100 to the forks of the forklift, the bottom supporting plate 100 can be transported by the forklift, and the heavy-duty carrier for aircraft maintenance can be flexibly moved to different positions, which is more convenient to use.

[0046] Compared with the prior art, the present disclosure has at least the following advantages:

[0047] The heavy-duty bracket for aircraft maintenance has the advantages that the main bearing frame 200 is fixed with a plurality of adaptive limiting structures 400, and the adaptive limiting structures 400 are dispersedly arranged on the periphery of the landing gear flat table, when the main support 10 of the landing gear is placed on the landing gear flat table, the adaptive limiting structures 400 can be adapted to the external structure of the main support 10, so that the main support 10 is fixed on the landing gear flat table through the clamping action of the adaptive limiting structures 400, so that the main support 10 can be placed on the main bearing frame 200 stably and flatly. Since the vertical auxiliary support rod 300 arranged on the main bearing frame 200 is located in the swing direction of the side auxiliary support 20 of the landing gear, the side auxiliary support 20 can be swung relative to the main support 10 after the main support 10 is placed, so that the side auxiliary support 20 is supported by the auxiliary support rod 300, and then the side auxiliary support 20 is locked and connected by the auxiliary support rod 300, so that the position of the side auxiliary support 20 is fixed, that is, the main support 10 and the side auxiliary support 20 remain relatively static, and finally the situation that the side auxiliary support 20 swings relative to the main support 10 and accidentally injures the worker is reduced.

[0048] The above-described embodiments only express several implementation manners of the present disclosure, and the description is relatively specific and detailed, but it cannot be understood as the limitation of the scope of the utility model patent. It should be noted that, for ordinary skilled persons in the art, without departing from the concept of the present disclosure, several modifications and improvements can be made, which all belong to the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure patent should be subject to the appended claims.

Claims

1. A heavy load bracket for aircraft maintenance, comprising a bottom supporting plate, the bottom supporting plate being adapted to the forks of a forklift truck; characterized in that The heavy load bracket for aircraft maintenance further comprises a main load-bearing frame, a secondary support rod and a plurality of adaptive limiting structures; The main load-bearing frame is fixedly arranged on the bottom supporting plate, and the main load-bearing frame is provided with a landing gear flat table for placing the main support of the landing gear; a plurality of adaptive limiting structures are fixedly arranged on the main load-bearing frame and are dispersedly arranged on the circumferential side of the landing gear flat table; each adaptive limiting structure is respectively adapted and clamped to the main support of the landing gear, so that the main support of the landing gear is fixed on the landing gear flat table; the secondary support rod is vertically arranged on the main load-bearing frame and located in the swinging direction of the side secondary support of the landing gear; the secondary support rod is fixedly connected to the main load-bearing frame, and the secondary support rod is used for supporting and locking the side secondary support connected to the landing gear, so that the main support and the side secondary support remain relatively static.

2. The heavy load carriage for aircraft maintenance according to claim 1, characterized in that, The main load-bearing frame comprises a load-bearing base plate and a lifting frame; the load-bearing base plate is arranged on the bottom supporting plate and is welded with the surface of the bottom supporting plate; the lifting frame is detachably mounted on the load-bearing base plate and forms the landing gear flat table; the secondary support rod is fixedly arranged on the load-bearing base plate, and a plurality of adaptive limiting structures are fixedly arranged on the lifting frame.

3. The heavy load carriage for aircraft maintenance according to claim 2, characterized in that, The lifting frame is a triangular frame.

4. The heavy load carriage for aircraft maintenance according to claim 3, characterized in that, The triangular frame is a right-angled triangular frame, and two right-angled sides of the right-angled triangular frame are respectively fitted to the surface of the load-bearing base plate; the hypotenuse of the right-angled triangular frame is located outside the load-bearing base plate and is placed above the bottom supporting plate to form a supporting and lifting part.

5. The heavy duty cart for aircraft maintenance of claim 3, wherein, The main load-bearing frame further comprises a plurality of limiting and abutting parts; a part of the limiting and abutting parts are distributed in the triangular frame and abut against the inner frame edge of the triangular frame; another part of the limiting and abutting parts are located outside the triangular frame and abut against the outer frame edge of the triangular frame.

6. The heavy load carriage for aircraft maintenance of claim 5, wherein, The limiting and abutting part is a limiting block, and the limiting block is formed with a clamping notch; the limiting block is located outside the triangular frame and is matched with the corner of the triangular frame through the clamping notch.

7. The heavy load carriage for aircraft maintenance according to claim 6, characterized in that, The limiting block is provided with a sliding abutting block and a locking screw head; the sliding abutting block is slidingly connected to the limiting block, and the sliding direction of the sliding abutting block is towards the landing gear flat table; the locking screw head is threadedly connected to the limiting block and locks the sliding abutting block.

8. The heavy duty cart for aircraft maintenance of claim 1, wherein, The secondary support rod comprises a rod body and a bolt body; the rod body is fixedly connected to the main load-bearing frame and vertically extends to form a supporting part, and the supporting part is used for supporting the side secondary support of the landing gear; the bolt body is threadedly connected to the supporting part, and the bolt body is used for locking the side secondary support.

9. The heavy duty cart for aircraft maintenance of claim 1, wherein, The bottom of the bottom supporting plate is fixedly provided with a heightening block, and the heightening block is used for forming an inserting gap between the bottom supporting plate and the ground.

10. An aircraft component shipping device, comprising: The forklift truck and the heavy load bracket for aircraft maintenance according to any one of claims 1 to 9 are comprised; the bottom supporting plate is adapted to the forks of the forklift truck.

Images