Aircraft fuselage and wing connecting mechanism

Abstract

The utility model discloses an aircraft fuselage and wing connecting mechanism which comprises an aircraft fuselage, a first wing, a second wing and a connecting structure, the upper side and the lower side of the aircraft fuselage are fixedly connected with the first wing and the second wing respectively, and the connecting structure is arranged at the bottom of the right side of the aircraft fuselage. By means of running fit of an external tool and a circular groove, while the circular groove is pressed, a rectangular block moves backwards into the machine body, so that a rotating tool can drive the rectangular block to rotate, the rectangular block drives a rotating plate to rotate, and the rotating plate drives a first connecting rod and a second connecting rod to rotate; the first connecting rod and the second connecting rod drive the two limiting plates to slide and get close, at the moment, the two connecting blocks are released from limitation, and the effect of quickly disassembling and assembling the first wing or the second wing can be achieved by performing the same movement on the two connecting structures of the first wing or the second wing.

Description

Technical Field

[0001] The utility model relates to the field of aircraft, in particular to an aircraft fuselage and wing connecting mechanism. Background Art

[0002] An aircraft is a heavier-than-air aircraft with wings and one or more engines that can fly in the atmosphere under its own power. An unmanned aircraft is referred to as a "drone" and is controlled by a radio remote control device and a self-contained program control device, or is operated completely or intermittently autonomously by an on-board computer.

[0003] However, in the prior art, most unmanned aircraft are fixed-wing aircraft, and the fuselage and wings are mostly fixed with screws. The fixed-wing aircraft has a complex structure, and many tools are needed for disassembly and assembly. Moreover, disassembly and assembly may easily cause omission and loss of parts, making it inconvenient to disassemble and assemble the wings of unmanned aircraft. Utility Model Content

[0004] Therefore, in order to solve the above-mentioned shortcomings, the utility model provides an aircraft fuselage-wing connecting mechanism.

[0005] In order to achieve the above-mentioned purpose, the utility model adopts the following technical scheme: an aircraft fuselage-wing connecting mechanism, comprising a fuselage, a first wing, a second wing and a connecting structure, the upper and lower sides of the fuselage are respectively fixedly connected to the first wing and the second wing, a connecting structure is provided at the right bottom of the fuselage, the connecting structure comprises a first sliding groove, a second sliding groove, a connecting block, a limiting plate and an adjusting structure, two first sliding grooves are provided at the right bottom of the fuselage, a second sliding groove is provided on the upper side of the adjacent ends of the two first sliding grooves, the inner walls of the two first sliding grooves are respectively tightly fitted with the connecting blocks, the adjacent ends of the two connecting blocks are respectively fitted with the limiting plates, an adjusting structure is provided in the middle of the second sliding groove, and the lower end surface of the connecting block is fixedly connected to the second wing.

[0006] Optionally, the adjustment structure includes a rotating plate, a rotating seat, a first connecting rod, a second connecting rod and a rotating structure, the middle part of the rear end surface of the rotating plate is rotatably connected to the rotating seat via a rotating shaft, the rear end surface of the rotating seat is fixedly connected to the inner wall of the second sliding groove, the lower right side of the front end surface and the upper left side of the rear end surface of the rotating plate are respectively rotatably connected to one end of the first connecting rod and the second connecting rod via a rotating shaft, and the other ends of the first connecting rod and the second connecting rod are respectively rotatably connected to two limit plates via a rotating shaft, a rotating structure is fixed to the middle part of the front end surface of the rotating plate, and the front side of the rotating structure passes through the fuselage.

[0007] Optionally, the rotating structure includes an outer shell, a first spring, a limit block and a rectangular block, one end of the spring is fixed to the rear end face of the inner wall of the outer shell, and the other end of the spring is fixedly connected to the limit block, a rectangular block is fixed to the middle part of the front end face of the limit block, and the front side of the rectangular block passes through the outer shell and the fuselage.

[0008] Optionally, a total of four groups of the connection structures are provided, and are respectively fixedly connected to the left and right sides of the proximal ends of the first wing and the second wing, so as to facilitate the disassembly and assembly of the first wing and the second wing.

[0009] Optionally, upper and lower sides of the middle portions of the adjacent ends of the two limiting plates are respectively fixedly connected to one end of the second spring, which is conducive to limiting the two limiting plates by the second spring.

[0010] Optionally, the limiting rod is fixedly connected to the upper and lower sides of the middle parts of the adjacent ends of the two limiting plates, and the limiting rod is sleeved inside the second spring to prevent the second spring from shaking.

[0011] Optionally, a circular groove is provided in the middle of the front end surface of the rectangular block, and the rectangular block can be rotated by pressing the circular groove with the help of a tool.

[0012] Beneficial effects of the utility model:

[0013] The utility model discloses a connecting mechanism for an aircraft fuselage and a wing. By setting a connecting structure, an external tool is used to rotate with a circular groove. When the circular groove is pressed, a rectangular block is moved backward to the inside of the fuselage, so that the rotating tool can drive the rectangular block to rotate, the rectangular block drives a rotating plate to rotate, the rotating plate drives a first connecting rod and a second connecting rod to rotate, the first connecting rod and the second connecting rod drive two limit plates to slide close to each other, and at this time, the restrictions on the two connecting blocks are released. By performing the same movement on the two connecting structures of the first wing or the second wing, the effect of quickly disassembling and assembling the first wing or the second wing can be achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the internal structure of the utility model;

[0015] Figure 2 This utility model structure Figure 1 A partial enlarged view of

[0016] Figure 3 It is a three-dimensional schematic diagram of the limiting plate of the utility model;

[0017] Figure 4 It is a schematic diagram of the adjustment structure of the utility model;

[0018] Figure 5 It is a left view of the rotating structure of the utility model.

[0019] Among them: fuselage-1, first wing-2, second wing-3, connecting structure-4, first sliding groove-41, second sliding groove-42, connecting block-43, limiting plate-44, adjusting structure-45, second spring-46, limiting rod-441, rotating plate-451, rotating seat-452, first connecting rod-453, second connecting rod-454, rotating structure-455, outer shell-4551, first spring-4552, limiting block-4553, rectangular block-4554, circular groove-4555. DETAILED DESCRIPTION

[0020] In order to further explain the technical solution of the present utility model, it is described in detail through specific embodiments below.

[0021] See also Figure 1 , Figure 2 and Figure 3 The utility model provides an aircraft fuselage-wing connection mechanism, comprising a fuselage 1, a first wing 2, a second wing 3 and a connection structure 4. The upper and lower sides of the fuselage 1 are respectively fixedly connected to the first wing 2 and the second wing 3. The right bottom of the fuselage 1 is provided with a connection structure 4, and the connection structure 4 comprises a first sliding groove 41, a second sliding groove 42, a connection block 43, a limit plate 44 and an adjustment structure 45. The right bottom of the fuselage 1 is provided with two first sliding grooves 41, and the upper sides of the adjacent ends of the two first sliding grooves 41 are provided with a second sliding groove 42. The inner walls of the two first sliding grooves 41 are respectively tightly fitted with the connection blocks 43, and the adjacent ends of the two connection blocks 43 are respectively fitted with the limit plates 44. The second sliding groove 42 is fitted with an adjustment structure 45 in the middle part, the lower end surface of the connecting block 43 is fixedly connected to the second wing 3, and a total of four connecting structures 4 are provided, which are respectively fixedly connected to the left and right sides of the proximal ends of the first wing 2 and the second wing 3, so as to facilitate the disassembly and assembly of the first wing 2 and the second wing 3, and the upper and lower sides of the middle part of the proximal ends of the two limiting plates 44 are respectively fixedly connected to one end of the second spring 46, which is conducive to limiting the two limiting plates 44 by the second spring 46, and the limiting rod 441 is respectively fixedly connected to the upper and lower sides of the middle part of the proximal ends of the two limiting plates 44, and the limiting rod 441 is sleeved inside the second spring 46 to prevent the second spring 46 from shaking.

[0022] See also Figure 4The utility model provides an aircraft fuselage-wing connection mechanism, the adjustment structure 45 comprises a rotating plate 451, a rotating seat 452, a first connecting rod 453, a second connecting rod 454 and a rotating structure 455, the middle part of the rear end surface of the rotating plate 451 is rotatably connected with the rotating seat 452 through a rotating shaft, the rear end surface of the rotating seat 452 is fixedly connected with the inner wall of the second sliding groove 42, the lower right side of the front end surface and the upper left side of the rear end surface of the rotating plate 451 are rotatably connected with one end of the first connecting rod 453 and the second connecting rod 454 through a rotating shaft respectively, and the other ends of the first connecting rod 453 and the second connecting rod 454 are rotatably connected with the two limiting plates 44 through rotating shafts respectively, the middle part of the front end surface of the rotating plate 451 is fixed with a rotating structure 455, and the front side of the rotating structure 455 passes through the fuselage 1.

[0023] See also Figure 5 The utility model provides an aircraft fuselage-wing connection mechanism, wherein a rotating structure 455 comprises an outer shell 4551, a first spring 4552, a limiting block 4553 and a rectangular block 4554, one end of the spring 4552 is fixed to the rear end face of the inner wall of the outer shell 4551, and the other end of the spring 4552 is fixedly connected to the limiting block 4553, a rectangular block 4554 is fixed to the middle of the front end face of the limiting block 4553, and the front side of the rectangular block 4554 penetrates the outer shell 4551 and the fuselage 1, and a circular groove 4555 is provided in the middle of the front end face of the rectangular block 4554, which can be rotated by pressing the circular groove 4555 with the help of a tool.

[0024] Here’s how it works:

[0025] First, place the new device in the desired location;

[0026] Second, by using a tool that rotates with the circular groove 4555 of the connecting structure 4 on the right side of the second wing 3, first use the tool to push the circular groove 4555 backward, and the circular groove 4555 drives the rectangular block 4554 to move backward to the inside of the fuselage 1, and then rotate the tool. The tool drives the rectangular block 4554 to rotate by using the circular groove 4555, and the rectangular block 4554 drives the outer shell 4551 to rotate, and the outer shell 4551 drives the rotating plate 451 to rotate, and the rotating plate 451 drives the first connecting rod 453 and the second connecting rod 454 to rotate;

[0027] Third, the first connecting rod 453 and the second connecting rod 454 use the second sliding groove 42 to respectively drive the limit plates 44 on the left and right sides to slide closer, and the limit plates 44 are restricted by the second spring 46 and the limit rod 441 to move smoothly. When the rotating plate 451 rotates forty-five degrees, the limit plates 44 on both sides are close to the rotating plate 44, the restriction on the connecting plates 43 on both sides is released, and the connecting structure 4 on the left side of the second wing 3 moves according to the same principle. At this time, the second wing 3 can be disassembled downward by using the first sliding groove 41, and the first wing 2 and the second wing 3 can be moved according to the same principle, thereby achieving the effect of facilitating the disassembly and assembly of the first wing 2 and the second wing 3.

[0028] The control method of the present invention is to control by manually starting and closing the switch. The wiring diagram of the power element and the provision of power supply are common knowledge in the field, and the present invention is mainly used to protect mechanical devices, so the present invention will not explain the control method and wiring arrangement in detail.

[0029] The control method of the present invention is automatic control through a controller. The control circuit of the controller can be realized by simple programming by technicians in this field. The provision of power is also common knowledge in this field. The present invention is mainly used to protect mechanical devices, so the present invention will no longer explain the control method and circuit connection in detail.

[0030] The above description is only a preferred example of the present invention and is not intended to limit the present invention. Although the present invention is described in detail with reference to the above embodiments, those skilled in the art can still modify the technical solutions described in the above embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An aircraft fuselage-wing connection mechanism, comprising a fuselage (1), a first wing (2) and a second wing (3), wherein the upper and lower sides of the fuselage (1) are fixedly connected to the first wing (2) and the second wing (3) respectively; Features: The invention also comprises a connection structure (4), wherein the right bottom of the fuselage (1) is provided with the connection structure (4), wherein the connection structure (4) comprises a first sliding groove (41), a second sliding groove (42), a connection block (43), a limit plate (44) and an adjustment structure (45), wherein the right bottom of the fuselage (1) is provided with two first sliding grooves (41), the upper sides of the adjacent ends of the two first sliding grooves (41) are provided with second sliding grooves (42), the inner walls of the two first sliding grooves (41) are respectively tightly fitted with the connection blocks (43), the adjacent ends of the two connection blocks (43) are respectively fitted with the limit plate (44), the middle part of the second sliding groove (42) is provided with an adjustment structure (45), and the lower end surface of the connection block (43) is fixedly connected with the second wing (3).

2. The aircraft fuselage-wing connection mechanism according to claim 1, characterized in that: The adjusting structure (45) comprises a rotating plate (451), a rotating seat (452), a first connecting rod (453), a second connecting rod (454) and a rotating structure (455); the middle part of the rear end surface of the rotating plate (451) is rotatably connected to the rotating seat (452) via a rotating shaft; the rear end surface of the rotating seat (452) is fixedly connected to the inner wall of the second sliding groove (42); the lower right side of the front end surface and the upper left side of the rear end surface of the rotating plate (451) are rotatably connected to one end of the first connecting rod (453) and the second connecting rod (454) via a rotating shaft, respectively; and the other ends of the first connecting rod (453) and the second connecting rod (454) are rotatably connected to the two limit plates (44) via a rotating shaft, respectively; the rotating structure (455) is fixed to the middle part of the front end surface of the rotating plate (451), and the front side of the rotating structure (455) passes through the fuselage (1).

3. The aircraft fuselage-wing connection mechanism according to claim 2, characterized in that: The rotating structure (455) comprises a shell (4551), a first spring (4552), a limit block (4553) and a rectangular block (4554); one end of the spring (4552) is fixed to the rear end face of the inner wall of the shell (4551), and the other end of the spring (4552) is fixedly connected to the limit block (4553); a rectangular block (4554) is fixed to the middle part of the front end face of the limit block (4553), and the front side of the rectangular block (4554) passes through the shell (4551) and the fuselage (1).

4. The aircraft fuselage-wing connection mechanism according to claim 1, characterized in that: The connection structures (4) are provided in four groups in total, and are respectively fixedly connected to the left and right sides of the proximal ends of the first wing (2) and the second wing (3).

5. The aircraft fuselage-wing connection mechanism according to claim 1, characterized in that: The upper and lower sides of the middle parts of the adjacent ends of the two limit plates (44) are respectively fixedly connected to one end of the second spring (46).

6. The aircraft fuselage-wing connection mechanism according to claim 1, characterized in that: The upper and lower sides of the middle parts of the adjacent ends of the two limit plates (44) are respectively fixedly connected to the limit rods (441), and the limit rods (441) are sleeved inside the second spring (46).

7. The aircraft fuselage-wing connection mechanism according to claim 3, characterized in that: A circular groove (4555) is provided in the middle of the front end surface of the rectangular block (4554).

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