A quick dismounting structure of a wing and a fuselage of a light fixed-wing unmanned aerial vehicle

Abstract

The utility model discloses a kind of quick dismounting structure of light fixed wing unmanned aerial vehicle wing and fuselage, it is related to unmanned aerial vehicle technical field.The utility model includes wing main body mechanism, wing fuselage connecting mechanism and wing fuselage locking mechanism.Wing main body mechanism contains wing main body and wing connecting plate;Wing fuselage connecting mechanism contains fuselage main body, connecting ring, wing fixing piece and limiting screw;Wing fuselage locking mechanism contains quick-release insertion rod, round nut, round nut fixing piece.The utility model is equipped with the complete separation state of wing and fuselage in the transportation by the assembly of wing fuselage connecting mechanism, save transportation space and reduce the damage of wing fuselage connecting part in the transportation process;By modularization design, to reach the purpose that some components can be quickly replaced in actual flight process;Through the prior installation of each mechanism, without additional carrying tool in the process of executing task, truly realized the purpose of wing and fuselage tool-free quick connection.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, and in particular relates to a quick assembly and disassembly structure for the wings and fuselage of a lightweight fixed-wing UAV. Background Technology

[0002] Lightweight fixed-wing unmanned aerial vehicles (UAVs) are widely used in various fields such as military, agriculture, and surveying due to their long flight time, low cost, and flexible deployment. They can perform different tasks by carrying different mission payloads.

[0003] The evolution of modern battlefields has placed extremely high demands on the rapid deployment capabilities of unmanned aerial vehicle (UAV) systems. Traditional UAV wing connection technology relies on bolt fastening, which is time-consuming and requires carrying assembly tools. Existing quick-release mechanisms require two people to operate, resulting in low human-machine efficiency and failing to meet the needs of individual soldier carrying. Therefore, a quick-release device for wing and fuselage that can be operated by a single soldier and meets the requirements of rapid deployment on the modern battlefield is needed.

[0004] Therefore, we propose a quick assembly and disassembly structure for the wings and fuselage of a lightweight fixed-wing UAV. Utility Model Content

[0005] The purpose of this invention is to provide a quick assembly and disassembly structure for the wings and fuselage of a lightweight fixed-wing UAV, solving the problems of long time consumption and low human-machine efficiency in existing wing-fuselage connection technologies.

[0006] To solve the above-mentioned technical problems, this utility model is achieved through the following technical solution:

[0007] This utility model relates to a quick-release assembly / disassembly structure for the wing and fuselage of a lightweight fixed-wing UAV, comprising a wing main body mechanism, a wing-fuselage connection mechanism, and a wing-fuselage locking mechanism; the wing main body mechanism includes a wing connecting plate, the front end of which is provided with a U-shaped cross-section fixing groove, the upper surface of which is provided with several wing mounting positioning holes, the lower surface of which is provided with a round nut fixing positioning groove, the round nut fixing positioning groove being provided with a quick-release insert positioning hole, and the upper middle part of which is provided with a connector mounting groove;

[0008] The wing-fuselage connection mechanism includes a fuselage body and a connecting ring fixed to the front end of the fuselage body. Wing fasteners are symmetrically installed at the front end of the fuselage body. Fixing screws pass through the mounting holes of the wing fasteners, the mounting holes at the front end of the fuselage body, and the mounting holes of the connecting ring in sequence to fix the wing fasteners, the fuselage body, and the connecting ring. Limit screws are fixed to the side of the wing fasteners.

[0009] The wing-fuselage locking mechanism includes a quick-release insert rod, a round nut fixed below the quick-release insert rod, and a round nut fixing component with a round nut limiting groove and a positioning boss. The round nut fixing component has a round nut through groove in the middle.

[0010] In one embodiment, the width of the fixing slot is clearance-fitted with the diameter of the limiting screw; the quick-release insert positioning hole is clearance-fitted with the quick-release insert.

[0011] In one embodiment, the positioning boss of the round nut fastener is a frustum structure; the positioning groove of the round nut fastener of the wing connecting plate is provided with a matching conical inner wall, and the two form a self-centering mating structure.

[0012] In one embodiment, the shape and size of the round nut limiting groove are adapted to the round nut, and the round nut limiting groove and the round nut cooperate with each other.

[0013] In one embodiment, the surface of the wing connecting plate is provided with a weight-reducing groove of a weight-reducing grid array, and the round nut fastener is fixedly connected to the fuselage body through the round nut fastener mounting hole.

[0014] In one embodiment, the round nut fastener has a rectangular through-hole in the round nut slot; the length of the round nut through-hole is greater than the length of the round nut, the width of the round nut through-hole is greater than the diameter of the round nut, and the round nut through-hole and the round nut are mutually fitted.

[0015] This utility model has the following beneficial effects:

[0016] This invention, through the assembly of the wing-fuselage connection mechanism, enables the wing and fuselage to be completely separated during transportation, further saving transportation space and significantly reducing damage to the wing-fuselage connection during transportation.

[0017] This invention achieves its locking and fixing purpose through the installation of a wing-fuselage locking mechanism. In actual use, the quick-release screw passes through the reserved holes of the wing and wing connector and is fixedly connected to the round nut in the locking mechanism. With the round nut fixing component pre-installed inside the fuselage, the wing and fuselage can be effectively connected and fastened together, thereby achieving the purpose of quick assembly and disassembly of the wing and fuselage. At the same time, the wing connector positioning boss above the round nut fixing component cooperates with the round nut fixing component positioning groove on the lower surface of the wing connector to effectively play a positioning role when assembling the wing and fuselage.

[0018] This utility model uses a modular design to enable quick replacement of damaged components during actual flight.

[0019] This invention, through the pre-installation of various mechanisms, eliminates the need to carry additional tools during mission execution, truly achieving the goal of tool-free and rapid connection between the wings and fuselage.

[0020] Of course, any product implementing this utility model does not necessarily need to achieve all of the advantages described above at the same time. Attached Figure Description

[0021] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0023] Figure 2 This is a schematic diagram of the disassembled structure of this utility model;

[0024] Figure 3 This is a schematic diagram of the wing connecting plate in this utility model;

[0025] Figure 4 This is a schematic diagram of the round nut fixing component in this utility model.

[0026] The attached diagram lists the components represented by each number as follows:

[0027] 1. Wing main body mechanism; 11. Wing connecting plate; 1101. Fixing slot; 1102. Wing mounting positioning hole; 1103. Quick-release rod positioning hole; 1104. Connector mounting slot; 1105. Round nut fixing positioning slot; 2. Wing-fuselage connecting mechanism; 21. Fuselage main body; 22. Connecting ring; 23. Limit screw; 24. Wing fixing component; 3. Wing-fuselage locking mechanism; 31. Quick-release rod; 32. Round nut; 33. Round nut fixing component; 3301. Round nut limiting slot; 3302. Round nut through slot; 3303. Positioning boss; 3304. Round nut fixing mounting hole. Detailed Implementation

[0028] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0029] In the description of this utility model, it should be understood that the terms "upper", "middle", "outer", "inner", etc., which indicate orientation or positional relationship, are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the components or elements referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0030] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," "connected," etc., should be interpreted broadly. For example, "connection" 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. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0031] Example 1

[0032] Please see Figures 1-4 As shown, this utility model is a quick-release assembly and disassembly structure for the wing and fuselage of a lightweight fixed-wing UAV, including a wing main body mechanism 1, a wing-fuselage connection mechanism 2, and a wing-fuselage locking mechanism 3; the wing main body mechanism 1 includes a wing connecting plate 11, the front end of the wing connecting plate 11 is provided with a U-shaped cross-section fixing groove 1101, the upper surface of the wing connecting plate 11 is provided with a plurality of wing mounting positioning holes 1102, the lower surface of the wing connecting plate 11 is provided with a round nut fixing positioning groove 1105, the round nut fixing positioning groove 1105 is provided with a quick-release insert positioning hole 1103, and the upper middle part of the wing connecting plate 11 is provided with a connector mounting groove 1104;

[0033] The wing-fuselage connection mechanism 2 includes a fuselage body 21 and a connecting ring 22 fixed to the front end of the fuselage body 21. Wing fasteners 24 are symmetrically installed at the front end of the fuselage body 21. Fixing screws pass through the mounting holes of the wing fasteners 24, the mounting holes at the front end of the fuselage body 21, and the mounting holes of the connecting ring 22 in sequence to fix the wing fasteners 24, the fuselage body 21, and the connecting ring 22. Limit screws 23 are fixed on the side of the wing fasteners 24.

[0034] The wing-fuselage locking mechanism 3 includes a quick-release insert 31, a round nut 32 fixed below the quick-release insert 31, and a round nut fixing member 33 with a round nut limiting groove 3301 and a positioning boss 3303. A round nut through groove 3302 is provided in the middle of the round nut fixing member 33.

[0035] Furthermore, the width of the fixed slot 1101 is clearance-fitted with the diameter of the limit screw 23; the quick-release insert positioning hole 1103 is clearance-fitted with the quick-release insert 31.

[0036] Furthermore, the positioning boss 3303 of the round nut fastener 33 is a frustum structure; the positioning groove 1105 of the round nut fastener of the wing connecting plate 11 is provided with a matching conical inner wall, and the two form a self-centering mating structure.

[0037] Furthermore, the shape and size of the round nut limiting groove 3301 are adapted to the round nut 32, and the round nut limiting groove 3301 and the round nut 32 cooperate with each other.

[0038] Furthermore, the surface of the wing connecting plate 11 is provided with a weight-reducing groove of a weight-reducing grid array, and the round nut fastener 33 is fixedly connected to the fuselage body 21 through the round nut fastener mounting hole 3304.

[0039] Furthermore, the round nut fastener 33 has a rectangular through-hole through the round nut through slot 3302; the length of the round nut through slot 3302 is greater than the length of the round nut 32, and the width of the round nut through slot 3302 is greater than the diameter of the round nut 32, and the round nut through slot 3302 and the round nut 32 cooperate with each other.

[0040] Example 2

[0041] Please see Figures 1-4 As shown in the figure, this embodiment illustrates the working principle of a quick-assembly and disassembly structure for the wing and fuselage of a lightweight fixed-wing UAV:

[0042] During the preparation phase, firstly, the wing connecting plate 11 in the wing main body mechanism 1 is fixedly connected to the wing main body through the wing mounting positioning hole 1102. Then, the quick-release rod 31 in the wing fuselage locking mechanism 3 is passed through the pre-drilled hole at the rear end of the wing main body and through the quick-release rod positioning hole 1103 at the rear end of the wing connecting plate 11, and connected to the round nut 32 in the wing fuselage locking mechanism 3. The round nut 32 is adjusted to a suitable position on the quick-release rod 31, ensuring that the direction of the quick-release rod 31 pressing the handle after adjustment is aligned with the direction of the round nut 32. The axial direction of the mother 32 is kept consistent. Then, the connecting ring 22 in the wing-fuselage connection mechanism 2 is sleeved inside the front end of the fuselage body 21. The wing fixing member 24 is symmetrically installed on the front end of the fuselage body 21 through the reserved hole and fixedly connected with the connecting ring 22. The limiting screw 23 is fixed to the upper side of the wing fixing member 24. Then, the round nut fixing member 33 is fixed to the upper inner surface of the fuselage body 21. The wing connecting member positioning boss 3303 protrudes from the outer surface of the fuselage body 21 through the reserved hole at the rear end of the fuselage body 21.

[0043] During assembly, hold the lower part of the fuselage body 21 with your left hand and the wing body mechanism 1 with your right hand. Insert the fixing slot 1101 on the wing connecting plate 11 into the smooth surface of the wing fixing component 24 exposed by the limit screw 23 at a 45° angle upwards along the axis of the fuselage body 21. Open the quick-release lever 31 handle and rotate it so that the handle's opening direction is perpendicular to the axis of the fuselage body 21. Press down the wing body mechanism 1 so that the lower surface of the wing connecting plate 11 fits against the upper surface of the fuselage body 21. At this time, the round nut 32 passes through the round nut through slot 3302 in the round nut fixing component 33, ensuring... With the quick-release lever 31 handle open, press down on the wing while rotating the quick-release lever 31 until its open direction is parallel to the axis of the fuselage body 21 and the handle in its open state is away from the rear of the fuselage body 21. Then close the quick-release lever 31 handle. At this time, the upper surface of the round nut 32 is in contact with the surface of the round nut limiting groove 3301 in the round nut fixing member 33, and the wing connector positioning boss 3303 on the surface of the round nut fixing member 33 is inserted into the round nut fixing member positioning groove 1105 on the lower surface of the wing connecting plate 11, so that the wing body mechanism 1 and the fuselage body 21 are connected.

[0044] During the disassembly process after use, open the handle of the quick-release lever 31, press down the wing, and rotate the quick-release lever 31 until its handle is perpendicular to the axis of the fuselage body 21. At this time, the axis of the round nut 32 is aligned with the direction of the round nut through slot 3302. Lift the wing body so that the round nut 32 passes through the round nut through slot 3302 on the round nut fixing member 33. Then pull it towards the tail of the fuselage body 21 to separate the fixing slot 1101 at the front end of the wing connecting plate 11 from the limiting screw 23 on the wing fixing member 24, thus completing the separation of the wing from the fuselage.

[0045] In the description of this specification, references to terms such as "an embodiment," "example," and "specific example" indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0046] The preferred embodiments of this utility model disclosed above are merely illustrative of the present utility model. These preferred embodiments do not exhaustively describe all details, nor do they limit the utility model to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of this utility model, thereby enabling those skilled in the art to better understand and utilize it. This utility model is limited only by the claims and their full scope and equivalents.

Claims

1. A quick-release structure for the wing and fuselage of a lightweight fixed-wing unmanned aerial vehicle (UAV), comprising a wing main body mechanism (1), a wing-fuselage connection mechanism (2), and a wing-fuselage locking mechanism (3); characterized in that: The main wing structure (1) includes a wing connecting plate (11). The front end of the wing connecting plate (11) is provided with a U-shaped cross-section fixing slot (1101). The upper surface of the wing connecting plate (11) is provided with a plurality of wing mounting positioning holes (1102). The lower surface of the wing connecting plate (11) is provided with a round nut fixing positioning groove (1105). The round nut fixing positioning groove (1105) is provided with a quick-release insert positioning hole (1103). The upper part of the wing connecting plate (11) is provided with a connector mounting groove (1104). The wing-fuselage connection mechanism (2) includes a fuselage body (21) and a connecting ring (22) fixed to the front end of the fuselage body (21). Wing fasteners (24) are symmetrically installed at the front end of the fuselage body (21). Fixing screws pass through the mounting holes of the wing fasteners (24), the mounting holes at the front end of the fuselage body (21), and the mounting holes of the connecting ring (22) in sequence to fix the wing fasteners (24), the fuselage body (21), and the connecting ring (22) together. Limit screws (23) are fixed on the side of the wing fasteners (24). The wing-fuselage locking mechanism (3) includes a quick-release insert (31), a round nut (32) fixed below the quick-release insert (31), and a round nut fixing member (33) with a round nut limiting groove (3301) and a positioning boss (3303). The round nut fixing member (33) has a round nut through groove (3302) in the middle.

2. The quick-assembly and disassembly structure for the wing and fuselage of a lightweight fixed-wing UAV according to claim 1, characterized in that, The width of the fixed slot (1101) is clearance-fitted with the diameter of the limiting screw (23); the quick-release rod positioning hole (1103) is clearance-fitted with the quick-release rod (31).

3. The quick-assembly and disassembly structure for the wing and fuselage of a lightweight fixed-wing UAV according to claim 1, characterized in that, The positioning boss (3303) of the round nut fastener (33) is a frustum structure; the positioning groove (1105) of the round nut fastener of the wing connecting plate (11) is provided with a matching conical inner wall, and the two form a self-centering mating structure.

4. The quick-assembly and disassembly structure for the wing and fuselage of a lightweight fixed-wing UAV according to claim 1, characterized in that, The shape and size of the round nut limiting groove (3301) are adapted to the round nut (32), and the round nut limiting groove (3301) and the round nut (32) cooperate with each other.

5. The quick-assembly and disassembly structure for the wing and fuselage of a lightweight fixed-wing UAV according to claim 1, characterized in that, The surface of the wing connecting plate (11) is provided with a weight-reducing groove of a weight-reducing grid array, and the round nut fastener (33) is fixedly connected to the fuselage body (21) through the round nut fastener mounting hole (3304).

6. The quick-assembly and disassembly structure for the wing and fuselage of a lightweight fixed-wing UAV according to claim 1, characterized in that, The round nut fastener (33) has a rectangular through-hole through groove (3302); the length of the round nut through groove (3302) is greater than the length of the round nut (32), the width of the round nut through groove (3302) is greater than the diameter of the round nut (32), and the round nut through groove (3302) and the round nut (32) cooperate with each other.

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