Composite unmanned aerial vehicle wing
By designing composite drone wings of protective components and wing components, the collision and damage of drone wings during storage is solved, and space saving and protective effects are achieved.
Patent Information
- Application Number
- CN202421787530.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-26
- Publication Date
- 2025-08-26
- Estimated Expiration
- 2034-07-26
AI Technical Summary
The existing composite drone wings are prone to collision and damage when stored and carried, resulting in economic losses.
A composite drone wing including protective components and wing components is designed. Through the structural design of folding wings and guard plates, it provides protective measures to reduce the risk of collision and damage.
It effectively reduces the space occupied during storage of the drone, and provides further protection through the cooperation of the guard plate and the insertion rod, reducing the collision and damage of the wings and spiral blades.
Smart Images
Figure CN223267063U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of unmanned aerial vehicle (UAV) wings, in particular to a composite material UAV wing. Background Art
[0002] Drones are mainly divided into two types: fixed-wing and rotary-wing. The wings of smaller drones are mostly composed of wings and propellers. This wing structure is usually made of lightweight, high-strength composite materials to further reduce the overall weight of the drone, improve flight efficiency and reduce energy consumption.
[0003] Regarding the above-mentioned related technologies, the inventors believe that the following defects exist: although the wings of drones made of composite materials are strong enough, the strength is only due to the light weight of the drone. If the wings do not have a certain protective structure, the wings and propeller blades are prone to collision and damage when stored and carried, causing economic losses. Utility Model Content
[0004] In order to improve the problem that the wings of today's drones made of composite materials are strong enough, but the strength is only due to the light weight of the drone. If the wings do not have a certain protective structure, the wings and propeller blades are prone to collision and damage when stored and carried, causing economic losses, the present application provides a composite drone wing.
[0005] The present application provides a composite drone wing adopts the following technical solution: a composite drone wing, including a protective component and a wing component, the protective component includes a guard plate, the bottom end of the guard plate is provided with a drone body, the left and right ends of the drone body are fixedly connected to four groups of connecting seats, the outer ends of the four groups of connecting seats are fixedly connected to a first limit seat, the wing assembly includes four groups of power bases, the top of the power bases are provided with spiral blades, and the inner ends of the power bases are fixedly connected to folding wings.
[0006] It is further provided that the inner ends of the four groups of folding wings are fixedly connected to rotating rods, and the inner ends of the four groups of rotating rods are respectively rotatably connected to the four groups of connecting seats.
[0007] It is further provided that the top ends and outer ends of the four groups of the first limiting seats are provided with insertion holes, and the outer ends of the four groups of the folding wings are provided with sliding grooves.
[0008] It is further provided that the four groups of sliding grooves are all fixedly connected with sliding rods, the inner sides of the sliding rods are all sleeved with sliding blocks, and the outer sides of the sliding rods are all sleeved with springs.
[0009] It is further provided that the inner ends of the four groups of sliding blocks are fixedly connected with second plug rods, and the second plug rods are plugged into the sockets.
[0010] It is further provided that the outer ends of the four groups of power bases are fixedly connected to a second limit seat, and the outer ends of the second limit seats are also provided with a socket.
[0011] It is further configured that four groups of first plug rods are fixedly connected to the bottom end of the guard plate, and the first plug rods are all inserted into the sockets, and two groups of connecting columns are fixedly connected to the top end of the drone body.
[0012] It is further provided that two sets of fastening bolts are provided at the top of the guard plate, and the fastening bolts are all threadedly connected to the top of the connecting column.
[0013] Compared with the related art, the composite material UAV wing provided by the present invention has the following features:
[0014] Beneficial effects:
[0015] The utility model provides a composite material UAV wing. By cooperating with a protective component and a wing component, it solves the technical problem that although the wings of current composite materials have sufficient strength, the strength is only due to the light weight of the UAV. If the wing does not have a certain protective structure, the wing and the spiral blade are prone to collision and damage during storage and carrying, causing economic losses. When the UAV is not in use, the sliding block is pulled outward to release the limit of the connecting seat and the support wing, so that the support wing can be folded upward. At this time, the sliding block can be pulled upward to fix the folded support wing again. The folding of the wing can effectively reduce the space occupied by the UAV when it is stored, and reduce the risk of collision and damage to components such as the folding wing and the spiral blade.
[0016] The utility model provides a composite material UAV wing. By cooperating with the protective assembly and the wing assembly, the fastening bolts are rotated to separate the wing from the connecting column, so that the guard plate can be removed. The setting of the guard plate improves the protection of the UAV body. At the same time, through the cooperation of the first plug rod and the plug hole provided at the bottom of the guard plate, further protection measures can be provided for the folded folding wings and spiral blades. The overall structure is simple, flexible and convenient to use, and has good practicality. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] Figure 1 This is a structural schematic diagram of a preferred embodiment of a composite material UAV wing provided by the utility model;
[0018] Figure 2 This is a schematic diagram of the overall rear view structure of the utility model;
[0019] Figure 3 For this utility model Figure 1 A is an enlarged structural diagram;
[0020] Figure 4 For this utility model Figure 2 A schematic diagram of the structure is enlarged at point B;
[0021] Figure 5 For this utility model Figure 2 Enlarged structural diagram at point C.
[0022] Numbers in the figure: 1. Protective component; 101. Guard plate; 102. UAV body; 103. First plug rod; 104. Connecting seat; 105. First limit seat; 106. Socket; 107. Connecting column; 108. Fastening bolt; 2. Wing assembly; 201. Power base; 202. Spiral blade; 203. Rotating rod; 204. Folding wing; 205. Sliding groove; 206. Sliding block; 207. Spring; 208. Sliding rod; 209. Second plug rod; 210. Second limit seat. DETAILED DESCRIPTION
[0023] In order to facilitate the understanding of the present invention, the present invention will be described in more detail below with reference to the accompanying drawings, in which typical embodiments of the present invention are shown.
[0024] Example 1:
[0025] like Figure 1-5 As shown, a composite material UAV wing of the present invention includes a protective component 1 and a wing component 2. The protective component 1 includes a guard plate 101. The bottom end of the guard plate 101 is provided with a UAV body 102. The left and right ends of the UAV body 102 are fixedly connected with four groups of connecting seats 104. The outer ends of the four groups of connecting seats 104 are fixedly connected with a first limit seat 105. The wing component 2 includes four groups of power bases 201. The top of the power base 201 is provided with a spiral blade 202. The inner end of the power base 201 is fixedly connected with a folding wing 204.
[0026] like Figure 1-5 As shown, the inner ends of the four groups of folding wings 204 are fixedly connected to the rotating rods 203 , and the inner ends of the four groups of rotating rods 203 are rotatably connected to the four groups of connecting seats 104 respectively.
[0027] like Figure 1-5 As shown, the top and outer ends of the four groups of first limiting seats 105 are each provided with an inserting hole 106 , and the outer ends of the four groups of folding wings 204 are each provided with a sliding groove 205 .
[0028] like Figure 1-5 As shown, the four sets of sliding grooves 205 are all fixedly connected with sliding rods 208 , the inner sides of the sliding rods 208 are all sleeved with sliding blocks 206 , and the outer sides of the sliding rods 208 are all sleeved with springs 207 .
[0029] During implementation, when the drone is not in use, the sliding block 206 is pulled outward to drive the second insertion rod 209 to move outward, separating it from the socket 106 and releasing the limit between the connecting seat 194 and the support wing 204, so that the support wing 204 can be folded upward. At this time, the sliding block 206 is pulled upward to use the reset of the spring 207 to drive the second insertion rod 209 to move downward and be inserted into the socket 106 at the top of the first limit seat 104, so that the folded support wing 204 can be fixed again. By folding the wings, the space occupied by the drone when it is stored can be effectively reduced, and the risk of collision and damage between the folding wings 204 and components such as the spiral blades 202 can be reduced.
[0030] Example 2:
[0031] like Figure 1-5 As shown, based on the first embodiment, the present invention provides a technical solution for a composite material UAV wing: the inner ends of the four sets of sliding blocks 206 are fixedly connected to the second plug rods 209, and the second plug rods 209 are all plugged into the sockets 106.
[0032] like Figure 1-5 As shown, the outer ends of the four power bases 201 are all fixedly connected to the second limiting base 210 , and the outer ends of the second limiting base 210 are also provided with a socket 106 .
[0033] like Figure 1-5 As shown, four groups of first plug rods 103 are fixedly connected to the bottom end of the guard plate 101, and the first plug rods 103 are all plugged into the sockets 106. Two groups of connecting columns 107 are fixedly connected to the top end of the drone body 102.
[0034] like Figure 1-5 As shown, two sets of fastening bolts 108 are provided at the top of the guard plate 101 , and the fastening bolts 108 are all threadedly connected to the top of the connecting column 107 .
[0035] During implementation, by cooperating with the protective component 1 and the wing component 2, the fastening bolt 106 is rotated to separate it from the connecting column 107, so that the guard plate 191 can be removed. The setting of the guard plate 101 improves the protection of the drone body 102. At the same time, through the cooperation of the first plug rod 103 and the socket 106 set at the bottom of the guard plate 101, further protection measures can be provided for the folded folding wings 204 and the spiral blades 202. The overall structure is simple, flexible and convenient to use, and has good practicality.
[0036] The advantages of this technical solution in practical applications include but are not limited to the following:
[0037] 1. By pulling the sliding block 206 outward, the limit between the connecting seat 194 and the supporting wing 204 is released, so that the supporting wing 204 can be folded upward. At this time, pulling the sliding block 206 upward can fix the folded supporting wing 204 again. By folding the wings, the space occupied by the drone when it is stored can be effectively reduced, and the risk of collision and damage between the folding wings 204 and the spiral blades 202 and other components can be reduced.
[0038] 2. By rotating the fastening bolt 106 to separate it from the connecting column 107, the guard plate 191 can be removed. The setting of the guard plate 101 improves the protection of the drone body 102. Through the cooperation of the first insertion rod 103 and the socket 106, further protection measures can be provided for the folded folding wings 204 and the spiral blades 202. The overall structure is simple, flexible and convenient to use, and has good practicality.
[0039] This technical solution separates the fastening bolt 108 from the connecting column 108 by rotating the fastening bolt 108, so that personnel can disassemble and assemble the guard plate 101 according to needs. When the drone body 102 is not in use, the sliding block 206 is pulled outward to drive the second insertion rod 209 to move outward from the socket 106. At this time, rotating the folding wing 204 can drive the power base 201 and the spiral blade 202 to flip upward. At this time, the sliding block 206 is lifted upward, and the spring 207 is deformed and reset under force, which will drive the second insertion rod 209 to be inserted downward into the socket 106 to provide limit fixation for the folded folding wing 204. At the same time, the four groups of first insertion rods 103 set at the bottom end of the guard plate 101 can be respectively inserted into the sockets 106 set on the four groups of second limit seats 210, thereby greatly improving the protection effect of the wing assembly 2.
[0040] The above are merely exemplary embodiments of the present disclosure and are not intended to limit the scope of the present disclosure. That is, any equivalent changes and modifications made in accordance with the teachings of the present disclosure are still within the scope of the present disclosure. After considering the disclosure of the specification and practice, those skilled in the art will easily think of other embodiments of the present disclosure. This application is intended to cover any variations, uses, or adaptive changes of the present disclosure, which follow the general principles of the present disclosure and include common knowledge or customary technical means in the art that are not recorded in the present disclosure.
Claims
1. A composite material UAV wing, comprising a protective component (1) and a wing component (2), characterized in that: The protective assembly (1) comprises a guard plate (101), a drone body (102) is provided at the bottom end of the guard plate (101), four groups of connecting seats (104) are fixedly connected at both left and right ends of the drone body (102), and the outer ends of the four groups of connecting seats (104) are fixedly connected to first limit seats (105). The wing assembly (2) comprises four groups of power bases (201), the top ends of the power bases (201) are each provided with a spiral blade (202), and the inner ends of the power bases (201) are each fixedly connected to a folding wing (204).
2. A composite material UAV wing according to claim 1, characterized in that: The inner ends of the four groups of folding wings (204) are all fixedly connected to the rotating rods (203), and the inner ends of the four groups of rotating rods (203) are respectively rotatably connected to the four groups of connecting seats (104).
3. A composite material UAV wing according to claim 2, characterized in that: The top and outer ends of the four groups of the first limiting seats (105) are all provided with insertion holes (106), and the outer ends of the four groups of the folding wings (204) are all provided with sliding grooves (205).
4. A composite material UAV wing according to claim 3, characterized in that: The four groups of sliding grooves (205) are all fixedly connected with sliding rods (208), the inner sides of the sliding rods (208) are all sleeved with sliding blocks (206), and the outer sides of the sliding rods (208) are all sleeved with springs (207).
5. The composite material UAV wing according to claim 4, characterized in that: The inner ends of the four groups of sliding blocks (206) are all fixedly connected with second plug rods (209), and the second plug rods (209) are all plugged into the sockets (106).
6. The composite material UAV wing according to claim 5, characterized in that: The outer ends of the four groups of power bases (201) are all fixedly connected to a second limiting seat (210), and the outer ends of the second limiting seats (210) are also provided with a socket (106).
7. The composite material UAV wing according to claim 6, characterized in that: Four groups of first plug rods (103) are fixedly connected to the bottom end of the guard plate (101), and the first plug rods (103) are all plugged into the sockets (106). Two groups of connecting columns (107) are fixedly connected to the top end of the drone body (102).
8. The composite material UAV wing according to claim 7, characterized in that: Two groups of fastening bolts (108) are provided at the top of the guard plate (101), and the fastening bolts (108) are both threadedly connected to the top of the connecting column (107).