Unmanned aerial vehicle wing release device
By designing a wing release device with a fixed base, torsion spring, and gear components on the drone, the problems of complexity and poor stability of existing wing folding mechanisms are solved, enabling simple, stable release and rapid deployment of drone wings.
Patent Information
- Application Number
- CN202520767712.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-22
- Publication Date
- 2026-02-17
- Estimated Expiration
- 2035-04-22
AI Technical Summary
Existing drone wing folding mechanisms are complex, increasing manufacturing costs and resulting in poor stability.
The drone wing release device, which is connected to the fuselage by a fixed base, uses torsion springs and gear components to achieve simple folding and unfolding of the wings. The wing rotation is driven by the compression and release of the torsion springs, and the positioning is achieved by spring pins.
It achieves wing release with simple structure, low cost and high stability, and is suitable for rapid launch of UAVs.
Smart Images
Figure CN223919611U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a UAV wing release device that is simple in structure and easy to use. Background Technology
[0002] Launching a drone is the first step in its use, and the launch phase is considered one of the most difficult and critical stages. There are numerous launch methods for drones, which can be categorized based on the power source, including ballistic launch, pneumatic launch, hydraulic / pneumatic launch, gas ejection, electromagnetic ejection, and rocket-assisted launch. Based on the launch method, they can be divided into air launch and ground launch. Air launch involves loading the drone, helicopter, or transport aircraft, enabling it to be airdropped and deployed at any time during mobile warfare, allowing drones to enter the battlefield faster and more efficiently. Folding-wing drones are launched using a launch canister, where the drone's wings are folded and placed inside before launch. However, current drone wing folding mechanisms are complex, increasing manufacturing costs and resulting in poor stability. Utility Model Content
[0003] The technical problem to be solved by this utility model is how to provide a drone wing release device that is simple in structure, low in manufacturing cost, and highly stable.
[0004] To solve the above-mentioned technical problems, the technical solution adopted by this utility model is: a drone wing release device, characterized in that: it includes a fixed base, the fixed base is fixedly connected to the drone fuselage, the fixed base has two mounting cylinders formed thereon, wherein a left wing is rotatably connected to the first mounting cylinder, and a right wing is rotatably connected to the second mounting cylinder, a torsion spring is sleeved on the second mounting cylinder between the right wing and the fixed base, the lower end of the torsion spring is engaged with the fixed base, the upper end of the torsion spring is engaged with the right wing, a first gear portion is formed on the inner side of the left wing, a second gear portion is formed on the inner side of the right wing, and the first gear portion meshes with the second gear portion.
[0005] The beneficial effects of adopting the above technical solution are as follows: the wing release device described in this application includes structures such as a fixed base, has fewer overall parts, strong transmission stability, and has the advantages of simple structure and low manufacturing cost. Attached Figure Description
[0006] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.
[0007] Figure 1 This is a schematic diagram of the structure of the device described in an embodiment of the present invention;
[0008] Figure 2is a partial structure schematic diagram of the device of the embodiment of the utility model;
[0009] Figure 3 is a partial structure schematic diagram of the device of the embodiment of the utility model after removing the gland;
[0010] Figure 4 is a structure schematic diagram of the fixed seat in the device of the embodiment of the utility model;
[0011] Figure 5 is a cooperation structure schematic diagram of the fixed seat and the torsion spring in the device of the embodiment of the utility model;
[0012] Figure 6 is a partial structure schematic diagram of the left wing in the device of the embodiment of the utility model;
[0013] Figure 7 is a cooperation structure schematic diagram of the left wing and the spring pin in the device of the embodiment of the utility model;
[0014] Figure 8 is a partial structure schematic diagram of the right wing in the device of the embodiment of the utility model;
[0015] Figure 9 is a cooperation structure schematic diagram of the right wing and the torsion spring in the device of the embodiment of the utility model;
[0016] Figure 10 is a cooperation structure schematic diagram of the fixed seat and the spring pin in the device of the embodiment of the utility model;
[0017] Wherein: 1, fixed seat, 2, unmanned aerial vehicle fuselage, 3, first installation cylinder, 4, left wing, 5, second installation cylinder, 6, right wing, 7, torsion spring, 8, first gear part, 9, second gear part, 10, first torsion spring installation slot, 11, first torsion spring clamping column, 12, gland, 13, first positioning part, 14, second positioning part, 15, third installation cylinder, 16, fourth installation cylinder, 17, second torsion spring installation slot, 18, second torsion spring clamping column, 19, spring pin, 20, spring pin clamping slot. DETAILED DESCRIPTION
[0018] The technical scheme in the embodiments of the utility model will be described clearly and completely below in conjunction with the drawings in the embodiments of the utility model, obviously, the described embodiments are only a part of the embodiments of the utility model, not all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by the person skilled in the art without making creative labor belong to the scope of protection of the utility model.
[0019] Many specific details are set forth in the following description in order to provide a thorough understanding of the present application. However, the present application can be practiced according to other embodiments that can not be described in detail herein, and the present application is not limited to the embodiments described herein. The present application is only limited by the claims.
[0020] As shown in Figures 1-10 the embodiments of the present application disclose a kind of unmanned aerial vehicle wing release device, the parts in the wing release device can be made of metal material or high-strength non-metal material.For the release device includes fixed seat 1, the fixed seat 1 is fixedly connected with unmanned aerial vehicle fuselage 2, the fixed connection between the two can be any one in prior art, can be through bolt, screw etc..Two installation barrels are formed on the fixed seat 1, wherein the first installation barrel 3 is rotatably connected with left wing 4, the second installation barrel 5 is rotatably connected with right wing 6, the shape of the left wing 4 and the right wing 6 is rectangular as a whole, of course, it can also be other shapes;A torsional spring 7 is sleeved on the second installation barrel 5 between the right wing 6 and the fixed seat 1, the lower end of the torsional spring 7 is clamped with fixed seat 1, and the upper end of the torsional spring 7 is clamped with right wing 6.The inner side of the left wing 4 is formed with first gear part 8, the inner side of the right wing 6 is formed with second gear part 9, the first gear part 8 is engaged with the second gear part 9, when the left wing 4 and the right wing 6 are folded together under the action of external force with the first installation barrel 3 and the second installation barrel 5 as pivot, the torsional spring 7 is in compression state, and the first gear part 8 and the second gear part 9 are driven in the process of rotating the left wing 4 and the right wing 6.
[0021] Further, as shown in Figure 2 and Figures 4-5 the lower surface of the fixed seat 1 is matched with the unmanned aerial vehicle fuselage 2, which facilitates the fixed connection between the two;The left side of the upper surface of the fixed seat 1 is formed with the first installation barrel 3, the right side of the upper surface of the fixed seat 1 is formed with the first torsional spring mounting groove 10, the first torsional spring mounting groove 10 is formed with the first torsional spring clamping column 11 and the second installation barrel 5, when the torsional spring 7 is sleeved on the second installation barrel 5, the lower end of the torsional spring 7 is clamped with the first torsional spring clamping column 11, in order to avoid interference between installation, the height of the first torsional spring clamping column 11 is not higher than the depth of the first torsional spring mounting groove 10.
[0022] Further, as shown in Figures 4-5 the axis of the first installation barrel 3 is formed with a first mounting hole, and the axis of the second installation barrel 5 is formed with a second mounting hole. Figure 6 and Figure 8As shown, the left wing 4 corresponding to the first mounting cylinder 3 is formed with a third mounting hole penetrating the left wing, the first mounting cylinder is inserted into the third mounting hole, the right wing 6 corresponding to the second mounting cylinder 5 is formed with a fourth mounting hole penetrating the right wing 6, the second mounting cylinder 5 is inserted into the fourth mounting hole. The first rotating shaft passes through the gland 12 and the first mounting hole in sequence and rotatably connects the left wing to the first mounting cylinder 3, the second rotating shaft passes through the gland and the second mounting hole in sequence and rotatably connects the right wing to the second mounting cylinder 5, the left wing can rotate around the first mounting cylinder 3 under the action of an external force, and the right wing can rotate around the second mounting cylinder 5 under the action of an external force.
[0023] Further, as shown in Figure 3 , Figure 6 and Figure 8 , the left wing 4 comprises a left wing body, and an inner side end of the left wing body is formed with an arc-shaped first gear portion 8 and a right-angled first positioning portion 13. The right wing 6 comprises a right wing body, and an inner side end of the right wing body is formed with an arc-shaped second gear portion 9 and a right-angled second positioning portion 14. Preferably, the central angle of the first gear portion and the second gear portion is 120°-180°. When the left wing 4 and the right wing 6 are unfolded, the first positioning portion 13 and the second positioning portion 14 are in contact, and the left wing body and the right wing body are positioned on a straight line by the positioning action of the first positioning portion 13 and the second positioning portion 14, at which time the left wing 4 and the right wing 6 are horizontally arranged as a whole.
[0024] Further, as shown in Figure 6 and Figure 7 , a third mounting cylinder 15 is formed on the lower surface of the left wing body of the first gear portion 8, the third mounting hole penetrates the third mounting cylinder 15, and the third mounting cylinder 15 is sleeved to the outside of the first mounting cylinder 3 and can rotate relative to each other under the action of an external force.
[0025] Further, as shown in Figures 8-9As shown, a fourth mounting cylinder 16 is formed on the inner end of the right wing body. The second gear part 9 and the second positioning part 14 are located on the upper side of the fourth mounting cylinder 16, and the height of the second gear part 9 is higher than the height of the right wing body, so that the height of the left wing 4 is higher than the height of the right wing. The fourth mounting hole penetrates the fourth mounting cylinder 16, and the fourth mounting cylinder 16 is sleeved on the outer side of the second mounting cylinder 5. The two can rotate relative to each other under the action of external force. When the left wing 4 and the right wing 6 are folded together, the right wing body is located on the lower side of the left wing body. Furthermore, in order to facilitate the installation of the torsion spring, a second torsion spring mounting groove 17 and a second torsion spring retaining post 18 are formed on the outer side of the fourth mounting cylinder 16. The torsion spring 7 is sleeved on the outer side of the fourth mounting cylinder 16, and the upper end of the torsion spring 7 is engaged with the second torsion spring retaining post 18.
[0026] In addition, such as Figures 6-7 as well as Figure 10 As shown, in order to position the deployed left wing 4 and right wing 6, the release device further includes a spring pin 19. The spring pin 19 is fixed to the UAV fuselage 2, and the movable end of the spring pin 19 passes through a through hole on the fixed base 1 and is positioned directly opposite the lower surface of the third mounting cylinder 15. The lower surface of the third mounting cylinder 15 has a spring pin groove 20, which is adapted to the movable end of the spring pin 19. When the left wing 4 and right wing 6 are in the retracted state, the lower surface of the third mounting cylinder 15 does not have the spring pin groove 20, causing the movable end of the spring pin 19 to be in a compressed state. When the left wing 4 and right wing 6 are in the deployed state, the movable end of the spring pin 19 is engaged in the spring pin groove 20.
[0027] In the wing release device described in this application, the torsion spring is in a released state when the wing is deployed and in a compressed state when the wing is closed. After the wing is closed and placed into the launch tube, the aircraft ejects from the launch tube during launch. The torsion spring drives the wing to rotate, and the gear on the right wing drives the left wing to deploy simultaneously. When the wing is fully deployed, the spring pin ejects and locks the wing.
Claims
1. A wing release device for a drone, characterized in that: The device includes a fixed base (1) which is fixedly connected to the fuselage (2) of the UAV. Two mounting cylinders are formed on the fixed base (1). The left wing (4) is rotatably connected to the first mounting cylinder (3), and the right wing (6) is rotatably connected to the second mounting cylinder (5). A torsion spring (7) is sleeved on the second mounting cylinder (5) between the right wing (6) and the fixed base (1). The lower end of the torsion spring (7) is engaged with the fixed base (1), and the upper end of the torsion spring (7) is engaged with the right wing (6). A first gear part (8) is formed on the inner side of the left wing (4), and a second gear part (9) is formed on the inner side of the right wing (6). The first gear part (8) and the second gear part (9) mesh.
2. The UAV wing release device as described in claim 1, characterized in that: The lower surface of the fixed base (1) is adapted to the fuselage (2) of the UAV. A first mounting cylinder (3) is formed on the left side of the upper surface of the fixed base (1), and a first torsion spring mounting groove (10) is formed on the right side of the upper surface of the fixed base (1). A first torsion spring retaining post (11) and a second mounting cylinder (5) are formed in the first torsion spring mounting groove (10).
3. The UAV wing release device as described in claim 1, characterized in that: The first mounting cylinder (3) has a first mounting hole formed on its axis, the second mounting cylinder (5) has a second mounting hole formed on its axis, the left wing (4) corresponding to the first mounting cylinder (3) has a third mounting hole that penetrates the left wing, the first mounting cylinder is inserted into the third mounting hole, the right wing (6) corresponding to the second mounting cylinder (5) has a fourth mounting hole that penetrates the right wing (6), the second mounting cylinder (5) is inserted into the fourth mounting hole, the first rotating shaft passes through the pressure cap (12) and the first mounting hole in sequence to rotatably connect the left wing to the first mounting cylinder (3), the second rotating shaft passes through the pressure cap and the second mounting hole in sequence to rotatably connect the right wing to the second mounting cylinder (5).
4. The UAV wing release device as described in claim 3, characterized in that: The left wing (4) includes a left wing body, and an arc-shaped first gear part (8) and a right-angled first positioning part (13) are formed on the inner end of the left wing body. The right wing (6) includes a right wing body, and an arc-shaped second gear part (9) and a right-angled second positioning part (14) are formed on the inner end of the right wing body. When the left wing (4) and the right wing (6) are deployed, the first positioning part (13) and the second positioning part (14) come into contact.
5. The UAV wing release device as described in claim 4, characterized in that: A third mounting cylinder (15) is formed on the left wing body of the lower surface of the first gear part (8), the third mounting hole penetrates the third mounting cylinder (15), and the third mounting cylinder (15) is sleeved on the outside of the first mounting cylinder (3).
6. The UAV wing release device as described in claim 4, characterized in that: A fourth mounting cylinder (16) is formed on the inner end of the right wing body. The second gear part (9) and the second positioning part (14) are located on the upper side of the fourth mounting cylinder (16), and the height of the second gear part (9) is higher than the height of the right wing body. The fourth mounting hole penetrates the fourth mounting cylinder (16), and the fourth mounting cylinder (16) is sleeved on the outer side of the second mounting cylinder (5).
7. The UAV wing release device as described in claim 6, characterized in that: The fourth mounting cylinder (16) has a second torsion spring mounting groove (17) and a second torsion spring retainer (18) formed on its outer side. The torsion spring (7) is sleeved on the outer side of the fourth mounting cylinder (16), and the upper end of the torsion spring (7) is engaged with the second torsion spring retainer (18).
8. The UAV wing release device as described in claim 4, characterized in that: The central angle between the first gear section () and the second gear section is 120°-180°.
9. The UAV wing release device as described in claim 5, characterized in that: The release device also includes a spring pin (19), which is fixed on the fuselage (2) of the drone. The movable end of the spring pin (19) passes through the through hole on the fixed base (1) and is positioned opposite to the lower surface of the third mounting cylinder (15). A spring pin groove (20) is formed on the lower surface of the third mounting cylinder (15), and the spring pin groove (20) is adapted to the movable end of the spring pin (19).
10. The UAV wing release device as described in claim 1, characterized in that: The wing release device is made of metallic or high-strength non-metallic materials.