Quick locking device for wings of unmanned aerial vehicle
By designing the drone wing fast locking device, the combination of hooks, docking blocks, sliders and springs, the problems of inconvenient connection and insufficient strength of the traditional drone wing are solved, and the rapid installation and disassembly of the wings are achieved, and the portability and flight safety of the drone are improved.
Patent Information
- Application Number
- CN202421587981.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-06
- Publication Date
- 2025-06-06
- Estimated Expiration
- 2034-07-06
AI Technical Summary
The connection between the wings and fuselage of traditional drones has problems such as inconvenient portability, insufficient strength and cumbersome assembly, which cannot meet the needs of drones to quickly install and take off in complex environments.
A drone wing quick locking device is designed, including wings, folding modules, butt blocks, hooks, sliders and springs. Quick locking and disassembling of the wings is achieved through the connection between the hook and the butt block and the fit of the slider and the spring.
This device makes the docking between the wing and the fuselage more convenient and fast, has strong portability, and can effectively prevent the wing from falling off during flight. At the same time, the rapid disassembly of the wing simplifies operation and is suitable for use in complex environments.
Smart Images
Figure CN222947027U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a quick locking device for the wings of unmanned aerial vehicles. Background Art
[0002] With the rapid development of drone technology, drones are increasingly used in various fields. In the pursuit of high performance and convenience, drones are also gradually changing from the initial overall construction to modularization. As an important component of drones, the stability and reliability of the connection structure of the wing have an important impact on the overall performance and safety of the drone. Traditional drone wings are fixedly connected to the fuselage, which often has problems such as inconvenient carrying, insufficient strength, and cumbersome assembly. They cannot meet the needs of drones for rapid installation and takeoff in complex environments. Utility Model Content
[0003] The purpose of the utility model is to provide a quick locking device for the wings of a UAV to solve the problems raised in the above-mentioned background technology.
[0004] The above-mentioned purpose of the utility model is achieved through the following technical solutions:
[0005] A quick locking device for unmanned aerial vehicle wings, characterized in that it includes a wing, a folding module, a docking block, a hook, a slider, and a spring. The docking block is installed in a rectangular groove between two axes of the wing, the groove contains an M2 threaded hole, and the docking block is fixed between the two axes of the wing by a countersunk screw; the hook is fixedly connected to the folding module by a countersunk screw; the slider is installed inside the docking block, and is slidably limited by the rectangular groove at the upper end of the docking block; the spring is installed at the circular hole inside the slider.
[0006] The hook is inserted into the docking block through the rectangular groove at the front end of the docking block, and the slider inside the docking block slides along the rectangular groove at the upper end of the docking block under the action of the spring, thereby limiting the hook forward and backward. After the docking is completed, the slider ensures that the hook is in a clamped position under the action of the spring to prevent the wing from falling off during flight.
[0007] Furthermore, the docking block is made of structural steel with a length of 30 mm, a width of 11 mm, a thickness of 10 mm and a hollow structure inside. A rectangular groove with a length of 11 mm and a width of 5 mm is opened at the front end for the hook to enter and exit freely, and through holes with a diameter of 2 mm are opened on both sides of the square groove for connecting the docking block to the wing.
[0008] Furthermore, the hook head is made of structural steel with a length of 15 mm, a width of 5 mm, and a thickness of 5 mm, and the tail is made of a structural steel group with a length of 18 mm, a width of 13 mm, and a thickness of 5 mm. The head and the hook body are 93°, with a certain taper, so that the hook and the slider are more stable and reliable when they are matched. The tail is provided with an M2 threaded hole for fixing with the folding module.
[0009] Furthermore, the slider is limited by the rectangular groove at the upper end of the docking block, installed inside the docking block, and can slide inside the docking block. The sliding of the slider is limited by the rectangular groove at the upper end of the docking block, and the slider contains a circular groove with a diameter of 3.2 mm to provide space for the installation of the spring.
[0010] Furthermore, the spring has an outer diameter of 3 mm and a length of 10 mm, and is installed in a circular groove inside the slider to ensure that the slider is in a clamping position with respect to the hook.
[0011] Compared with the existing utility model, the beneficial effects of the utility model are:
[0012] (1) The docking module can carry the wing and the fuselage separately, making it easy to carry.
[0013] (2) The docking of the wing and the folding module is simplified to the connection between the hook and the docking block. The slider inside the docking block can clamp and fix it after the hook is matched, which has the characteristics of convenient and fast connection.
[0014] (3) To separate the wing from the fuselage, simply manually push the slider to its initial position to quickly disassemble the wing. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] Figure 1 Installation diagram for docking block
[0016] Figure 2 Installation diagram for hooks
[0017] Figure 3 This is a sectional view of the wing not docked
[0018] Figure 4 Complete the cutaway view for the wing docking
[0019] Figure 5 For unattached axis view
[0020] Figure 6 For docked axis view
[0021] Among them: 1-wing, 2-folding module, 3-docking block, 4-hook, 5-slider, 6-spring. DETAILED DESCRIPTION
[0022] like Figure 1-Figure 4 The wing quick locking device shown includes a front wing 1, a folding module 2, a docking block 3, a hook 4, a slider 5, and a spring 6. The docking block 3 is installed in the front wing 1 through a countersunk screw; the hook 4 is installed in the folding module 2 through a countersunk screw; the slider 5 is installed inside the docking block 3 and can slide inside the docking block 3; one end of the spring 6 is installed in a circular groove on one side of the slider 5, and the other end is in contact with the docking block 3;
[0023] like Figure 1 As shown, the docking block 3 is installed in the rectangular groove between the two axes of the wing 1 and fixed to the wing 1 by screws. The docking block 3 is a hollow structure inside, and a rectangular groove with a length of 11 mm and a width of 5 mm is opened at the front end to provide a limit for the entry and exit of the hook 4. A rectangular groove with a length of 14 mm and a width of 2.5 mm is opened at the upper end to provide a limit for the movement of the internal slider 5.
[0024] like Figure 2 As shown, the hook 4 is installed in the folding module 2 by screws, and its head and the hook body are 93 degrees, with a certain taper, so that the hook 4 and the slider 5 are more stable and reliable when they cooperate.
[0025] like Figure 3 , Figure 4 As shown, firstly, the shafts on both sides of the wing 1 are matched with the circular grooves in the folding module 2, and the slider 5 in the docking block is pushed to the initial position before the hook is matched with the docking block 3. The slider 5 inside the docking block 3 locks the hook 4 under the action of the spring 6 and the limit groove at the upper end of the docking block, thereby realizing rapid installation, and the wing 1 can be quickly disassembled only when the slider 6 is pushed to the initial position.
[0026] like Figure 4 As shown, one end of the spring 6 is installed in the circular groove on one side of the slider 5, and the other end is in contact with the docking block 3, providing the slider 5 with a thrust to clamp the hook and prevent the hook 4 from falling off.
Claims
1. A UAV wing quick locking device, characterized in that: The invention comprises a wing (1), a folding module (2), a docking block (3), a hook (4), a slider (5), and a spring (6); the docking block (3) is installed in a rectangular groove between two axes of the wing (1); the groove contains an M2 threaded hole; the docking block (3) is fixed between the two axes of the wing (1) by countersunk screws; the hook (4) is fixedly connected to the folding module (2) by countersunk screws; the slider (5) is installed inside the docking block (3); and the spring (6) is installed at the circular hole inside the slider (5); The hook (4) is inserted into the docking block through the rectangular groove at the front end of the docking block (3); the slider (5) inside the docking block (3) slides along the rectangular groove at the upper end of the docking block (3) under the action of the spring (6), thereby limiting the front and rear positions of the hook (4); after the docking is completed, the slider (5) ensures that the hook (4) is in a clamping position under the action of the spring (6).
2. The UAV wing quick locking device according to claim 1 is characterized in that The docking block (3) is made of structural steel with a length of 30 mm, a width of 11 mm, a thickness of 10 mm and a hollow structure inside. A rectangular groove with a length of 11 mm and a width of 5 mm is opened at the front end to allow the hook (4) to enter and exit freely. Through holes with a diameter of 2 mm are opened on both sides of the square groove.
3. The UAV wing quick locking device according to claim 1 is characterized in that The head of the hook (4) is composed of a structural steel with a length of 15 mm, a width of 5 mm and a thickness of 5 mm, and the tail is composed of a structural steel group with a length of 18 mm, a width of 13 mm and a thickness of 5 mm, and the tail is opened with an M2 threaded hole.
4. The UAV wing quick locking device according to claim 1 is characterized in that The slider (5) is limited by the rectangular groove at the upper end of the docking block (3), is installed inside the docking block (3), and can slide inside the docking block (3); the slider (5) contains a circular groove with a diameter of 3.2 mm; the side of the slider in contact with the hook contains a 3° slope, which can be used for the slider to clamp the hook.
5. The UAV wing quick locking device according to claim 1 is characterized in that The spring (6) has an outer diameter of 3 mm and a length of 10 mm and is installed in a circular groove inside the slider (5).