Launching canister of folding wing unmanned aerial vehicle
By designing a folding wing drone launcher, the coordination of the clamping assembly and the motor-driven push rod is used to solve the problem of low take-off efficiency and achieve efficient and stable drone launch.
Patent Information
- Application Number
- CN202422257224.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-14
- Publication Date
- 2025-08-01
- Estimated Expiration
- 2034-09-14
AI Technical Summary
The current UAV takeoff method is relatively low and needs to improve launch accuracy and stability.
A folding wing drone launch cylinder is designed, including the launch cylinder body, a clamping assembly, a launch assembly and a baffle. Through the compression and accumulation of the clamping assembly and the rotation of the motor drive push rod, the precision ejection of the drone is achieved.
It realizes simple and efficient launch of the drone, and improves the launch accuracy and stability.
Smart Images
Figure CN223174341U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the technical field of folding-wing unmanned aerial vehicles, and particularly relates to a launching tube for folding-wing unmanned aerial vehicles. Background Technique
[0002] The folding-wing unmanned aerial vehicle is an innovative aviation device, mainly composed of a fuselage, wings and other parts. Its biggest feature is that the wings can be folded, which is convenient for storage and transportation. The fuselage is made of high-strength and lightweight materials, and the motor and propeller provide power. The control system and sensors ensure stable and precise flight control, and it is widely used in military, civilian and other fields.
[0003] The problems existing in the prior art are as follows: Generally, the takeoff method of the unmanned aerial vehicle is to directly take off on a flat surface, but this takeoff method has low efficiency. Therefore, a launching tube that can improve the launching accuracy and stability is needed. Therefore, we propose a launching tube for folding-wing unmanned aerial vehicles. Content of the Utility Model
[0004] The purpose of the utility model is to provide a launching tube for folding-wing unmanned aerial vehicles to solve the problems put forward in the above background technique.
[0005] The utility model is realized as follows: A launching tube for folding-wing unmanned aerial vehicles includes a launching tube body. A bottom plate is fixedly connected to the inner bottom of the launching tube body. A clamping component is arranged on the upper surface of the bottom plate. A launching component is arranged on the surface of the clamping component. The clamping component is used for compressing and storing energy for the launching component, and the launching component is used for catapulting the unmanned aerial vehicle. A baffle is fixedly connected to the middle of the inner wall of the launching tube body, and the baffle is used for restricting the movement range of the launching component.
[0006] Preferably, the clamping component includes a fixing plate, and the fixing plate is fixedly connected to the middle of the upper surface of the bottom plate. Three groups of mounting blocks are fixedly connected to the surface of the fixing plate.
[0007] Preferably, rotating rods are fixedly connected to both sides of the surfaces of the three groups of mounting blocks, and torsion springs are sleeved on both sides of the surfaces of the three groups of rotating rods.
[0008] Preferably, movable plates are fixedly connected together between the corresponding two groups of torsion springs, and clamping blocks are fixedly connected to one ends of one sides of the surfaces of the three groups of movable plates.
[0009] Preferably, the launching component includes a damper, and the damper is fixedly connected to the middle of the upper surface of the fixing plate. A spring is sleeved on the surface of the damper.
[0010] Preferably, one end of the damper and the spring are both fixedly connected to a connecting shell, and three through holes are provided at one end of the surface of the connecting shell.
[0011] Preferably, a connecting shell is fixedly connected to the inner wall of the connecting shell, a motor is fixedly connected inside the connecting shell, and three push rods corresponding to the through holes are fixedly connected to the output end of the motor.
[0012] Compared with the prior art, the beneficial effects of the present utility model are as follows:
[0013] 1. Through the design of the launching tube body, the bottom plate, the clamping component, the launching component and the baffle plate, when in use, press down the launching component. When the launching component is subjected to the downward pressure, it will move downward to store energy. When it moves downward to a certain distance, the launching component will be clamped by the clamping component to prevent the launching component from operating. Then, place the drone on the surface of the launching component inside the launching tube body. Finally, the launching component breaks away from the positioning of the clamping component to eject the drone, achieving the effect of facilitating the simple and efficient launching of the drone.
[0014] 2. Through the design of the mounting block, the rotating rod, the torsion spring, the movable plate, the fixing plate and the clamping block, when pressing down the launching component, the connecting shell will squeeze the clamping block. Since the upper side of the clamping block is a slope, the connecting shell will push the movable plate to rotate by using the rotating rod during the downward movement. When the connecting shell moves to a suitable position, the torsion spring will drive the movable plate and the clamping block to rotate and reset, so as to be clamped on the surface of the connecting shell to fix the connecting shell, achieving the effect of facilitating the positioning of the launching component after storing energy.
[0015] 3. Through the design of the spring, the damper, the connecting shell, the connecting shell, the motor, the push rod and the through hole, when pressing down the connecting shell, the spring will be compressed, and the damper is used to limit the spring. When it is necessary to launch the drone, start the motor, and the motor will drive the three push rods to rotate inside the through holes at the same time. Since both sides of the clamping block are slopes, when the push rod pushes the clamping block, the clamping block will rotate on the surface of the rotating rod by using the movable plate. At this time, the clamping block will break away from the positioning of the connecting shell, and the spring will eject the drone into the air, achieving the effect of facilitating the launching of the drone into the air. Description of the Drawings
[0016] Figure 1 It is a schematic diagram of the overall structure provided by an embodiment of the present utility model;
[0017] Figure 2 It is a schematic diagram of the damper structure provided by an embodiment of the present utility model;
[0018] [[ID=z8]] Figure 3 It is a schematic diagram of the motor structure provided by an embodiment of the present utility model;
[0019] Figure 4 This is provided by an embodiment of the present utility model Figure 2 and is a schematic diagram of a partially enlarged structure at position a in
[0020] In the figure: 1, the main body of the launch tube; 2, the bottom plate; 3, the clamping component; 301, the mounting block; 302, the rotating rod; 303, the torsion spring; 304, the movable plate; 305, the fixing plate; 306, the clamping block; 4, the launch component; 401, the spring; 402, the damper; 403, the connecting shell; 404, the connecting shell; 405, the motor; 406, the push rod; 407, the through hole; 5, the baffle plate. Specific embodiments
[0021] In order to further understand the content, features and effects of the present utility model, the following embodiments are cited and described in detail with reference to the accompanying drawings as follows.
[0022] The following will describe the structure of the present utility model in detail with reference to the accompanying drawings.
[0023] As Figures 1 to 4 shown, a folding-wing UAV launch tube provided by an embodiment of the present utility model includes a launch tube main body 1. A bottom plate 2 is fixedly connected to the inner bottom of the launch tube main body 1. A clamping component 3 is arranged on the upper surface of the bottom plate 2. A launch component 4 is arranged on the surface of the clamping component 3. The clamping component 3 is used to compress and store energy for the launch component 4. The launch component 4 is used to eject the UAV. A baffle plate 5 is fixedly connected to the middle of the inner wall of the launch tube main body 1. The baffle plate 5 is used to limit the movement range of the launch component 4.
[0024] Adopting the above scheme: Through the design of the launch tube main body 1, the bottom plate 2, the clamping component 3, the launch component 4 and the baffle plate 5, when in use, press the launch component 4 downward. When the launch component is subjected to the downward pressure, it will move downward to store energy. When it moves downward to a certain distance, the launch component 4 will be clamped by the clamping component 3 to prevent the launch component 4 from operating. Then, place the UAV on the surface of the launch component 4 inside the launch tube main body 1. Finally, the launch component 4 breaks away from the positioning of the clamping component 3 to eject the UAV, achieving the effect of facilitating the simple and efficient launch of the UAV.
[0025] Referring to Figure 2 and Figure 4 , the clamping component 3 includes a fixing plate 305. The fixing plate 305 is fixedly connected to the middle of the upper surface of the bottom plate 2. Three groups of mounting blocks 301 are fixedly connected to the surface of the fixing plate 305. A rotating rod 302 is fixedly connected to each of the three groups of mounting blocks 301. Torsion springs 303 are sleeved on both sides of the surface of the three groups of rotating rods 302. A movable plate 304 is fixedly connected between the corresponding two groups of torsion springs 303. A clamping block 306 is fixedly connected to one end of each side of the surface of the three groups of movable plates 304.
[0026] Adopting the above solution: Through the design of the mounting block 301, the rotating rod 302, the torsion spring 303, the movable plate 304, the fixed plate 305 and the clamping block 306, when pressing down the launching assembly 4, the connecting shell 403 will squeeze the clamping block 306. Since the upper side of the clamping block 306 is a slope, the connecting shell 403 will push the movable plate 304 to rotate by using the rotating rod 302 during the downward movement. When the connecting shell 403 moves to a suitable position, the torsion spring 303 will drive the movable plate 304 and the clamping block 306 to rotate and reset, so as to be clamped on the surface of the connecting shell 403 and fix the connecting shell 403, achieving the effect of facilitating the positioning of the launched assembly 4 after energy storage.
[0027] Reference Figure 2 and Figure 3 As shown in the figure, the launching assembly 4 includes a damper 402, and the damper 402 is fixedly connected to the middle of the upper surface of the fixed plate 305. A spring 401 is sleeved on the surface of the damper 402; one end of both the damper 402 and the spring 401 is fixedly connected to a connecting shell 403, and three through holes 407 are opened at one end of the surface of the connecting shell 403; a connecting shell 404 is fixedly connected to the inner wall of the connecting shell 403, a motor 405 is fixedly connected inside the connecting shell 404, and the output end of the motor 405 is fixedly connected to three push rods 406 corresponding to the through holes 407.
[0028] Adopting the above solution: Through the design of the spring 401, the damper 402, the connecting shell 403, the connecting shell 404, the motor 405, the push rod 406 and the through hole 407, when pressing down the connecting shell 403, the spring 401 will be compressed, and the damper 402 is used to limit the spring 401. When it is necessary to launch the drone, start the motor 405, and the motor 405 will drive the three push rods 406 to rotate inside the through holes 407 at the same time. Since both sides of the clamping block 306 are slopes, when the push rod 406 pushes the clamping block 306, the clamping block 306 will rotate on the surface of the rotating rod 302 by using the movable plate 304. At this time, the clamping block 306 will be disengaged from the positioning of the connecting shell 403, so that the spring 401 will eject the drone into the air, achieving the effect of facilitating the launch of the drone into the air.
[0029] The working principle of the present utility model:
[0030] During use, when pressing down the launching assembly 4, the connecting shell 403 will squeeze the latch 306. Since the upper side of the latch 306 is beveled, the connecting shell 403 will push the movable plate 304 to rotate using the rotating rod 302 during the downward movement. When the connecting shell 403 moves to a suitable position, the torsion spring 303 will drive the movable plate 304 and the latch 306 to rotate and reset, thus clamping on the surface of the connecting shell 403 to fix the connecting shell 403, facilitating the positioning of the launched assembly 4 after energy storage. When pressing down the connecting shell 403, the spring 401 will be compressed, and the damper 402 is used to limit the spring 401. When it is necessary to launch the drone, start the motor 405. The motor 405 will drive the three push rods 406 to rotate simultaneously inside the through hole 407. Since both sides of the latch 306 are beveled, when the push rod 406 pushes the latch 306, the latch 306 will rotate on the surface of the rotating rod 302 using the movable plate 304. At this time, the latch 306 will disengage from the positioning of the connecting shell 403, and thus the spring 401 will eject the drone into the air, facilitating the launch of the drone into the air.
[0031] In summary: For this folding-wing drone launching tube, through the structures of the spring 401, damper 402, connecting shell 403, connecting shell 404, motor 405, push rod 406, and through hole 407, it solves the problem that the general takeoff method for drones is to directly take off on a flat surface, but this takeoff method has low efficiency, so a launching tube that can improve the launching accuracy and stability is needed.
[0032] It should be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "including", "comprising" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements, but also includes other elements not expressly listed, or also includes elements inherent to such process, method, article or device.
[0033] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. A folding-wing UAV launcher tube, comprising a launcher tube body (1), characterized in that: A bottom plate (2) is fixedly connected to the inner bottom of the launcher body (1). A clamping component (3) is arranged on the upper surface of the bottom plate (2). An ejection component (4) is arranged on the surface of the clamping component (3). The clamping component (3) is used to compress and store energy for the ejection component (4). The ejection component (4) is used to eject the drone. A baffle (5) is fixedly connected to the middle of the inner wall of the launcher body (1). The baffle (5) is used to limit the movement range of the ejection component (4).
2. The folding-wing UAV launcher according to claim 1, wherein: The clamping component (3) includes a fixing plate (305). The fixing plate (305) is fixedly connected to the middle of the upper surface of the bottom plate (2). Three mounting blocks (301) are fixedly connected to the surface of the fixing plate (305).
3. The folding-wing UAV launcher according to claim 2, wherein: A rotating rod (302) is fixedly connected to each of the three mounting blocks (301). A torsion spring (303) is sleeved on both sides of the surface of each of the three rotating rods (302).
4. A folding-wing UAV launch tube according to claim 3, characterized in that: A movable plate (304) is fixedly connected between the corresponding two torsion springs (303). A clamping block (306) is fixedly connected to one end of one side of the surface of each of the three movable plates (304).
5. The folding-wing UAV launcher according to claim 2, wherein: The ejection component (4) includes a damper (402). The damper (402) is fixedly connected to the middle of the upper surface of the fixing plate (305). A spring (401) is sleeved on the surface of the damper (402).
6. The folding-wing UAV launch tube according to claim 5, characterized in that: One end of the damper (402) and the spring (401) are fixedly connected to a connection shell (403) together. Three through holes (407) are formed in one end of the surface of the connection shell (403).
7. The folding-wing UAV launch tube according to claim 6, wherein: A connecting shell (404) is fixedly connected to the inner wall of the connection shell (403). A motor (405) is fixedly connected to the connecting shell (404). Three push rods (406) corresponding to the through holes (407) are fixedly connected to the output end of the motor (405).