Unmanned aerial vehicle device capable of being catapulted by single person

Abstract

The utility model discloses a single-person catapultable unmanned aerial vehicle device which comprises a first rack and a second rack, a folding piece is arranged on one side of the joint of the first rack and the second rack, supporting frames are arranged at the bottoms of the two sides of one end of the first rack, a rear supporting frame is arranged at the bottom of one end of the second rack, guide rails are arranged on the tops of the first rack and the second rack, and a mounting frame is arranged on the top of the second rack. A hand-cranking winch is arranged at the bottom of one end of the second rack, a traction rope is connected in the hand-cranking winch in a winding mode, the other end of the traction rope is fixedly connected with a rubber band, and one end of the rubber band is connected to the end of the mounting frame. Compared with the prior art, the folding device has the advantages that the first rack and the second rack can be overlapped through the folding piece, the supporting frame is installed at one end of the rack through the supporting frame connecting piece, and meanwhile the supporting frame and the first rack can be overlapped through the supporting frame connecting piece; and the whole size is reduced, so that the structure occupies a minimum space when not used, and is convenient to carry.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a single-person ejectable unmanned aerial vehicle device. Background Art

[0002] A single-person drone ejection device is a special device used to launch drones, usually suitable for single-person or small-team combat environments. This device is designed to improve the deployment speed and flexibility of drones, especially in complex or restricted environments. The core parts of the device usually include an ejection mechanism and a control system. The ejection mechanism is responsible for quickly pushing the drone out of the device, while the control system ensures the accuracy and safety of the entire process. Through pre-set parameters, the control system can accurately control the force, angle and timing of the ejection, thereby ensuring that the drone can take off stably and safely.

[0003] The advantages of a single-person UAV ejection device are its portability and rapid deployment capability. Due to its small size and light weight, it can be carried and operated by a single person, which makes it possible to quickly deploy UAVs in complex terrain or battlefield environments. In addition, this device can also improve the survivability of UAVs, because it can launch UAVs into the air in a short time, reduce the time they are exposed on the ground, and reduce the risk of being discovered and attacked by the enemy.

[0004] In actual combat applications, the single-person UAV ejection device can be used to perform various tasks, such as filming, reconnaissance, surveillance, communication relay, etc. By quickly deploying UAVs, combatants can quickly obtain battlefield information and provide strong support for command decisions. At the same time, UAVs can also be used to perform tasks such as target indication and fire strikes to improve combat effectiveness. Utility Model Content

[0005] The technical problem to be solved by the utility model is to overcome the above technical defects and provide a single-person ejectable drone device.

[0006] In order to solve the above problems, the technical solution of the utility model is: a single-person ejectable drone device, including a frame one and a frame two, a folding piece is provided at the bottom of the connection between the frame one and the frame two, pulleys are provided on both sides of the frame one away from the frame two, support frames are provided at the bottom of both sides of the frame one away from the frame two, a rear support frame is provided at the bottom of the frame two away from the frame one, guide rails are provided on the top of the frame one and the frame two, the two guide rails are connected, a mounting frame is provided on the top of the frame two away from the frame one, and the The mounting frame is clamped in the guide rail, and a hand winch is provided at the bottom of the frame 2 near one end of the rear support frame, a traction rope is wound in the hand winch, and a rubber band is fixedly connected to the end of the traction rope away from the hand winch, the rubber band is sleeved on the outside of the pulley, and the end of the rubber band away from the traction rope is connected to the end of the mounting frame, a release switch is provided at the bottom of the mounting frame, and a switch rope is provided at one end of the release switch, an aircraft support frame is provided at the top of the mounting frame, and aircraft rear support frames are provided on both sides of the top of the mounting frame near one end of the rear support frame.

[0007] Furthermore, a support frame connecting piece is provided between the support frame and one end of the frame, and the support frame connecting piece is rotatably connected to the frame one.

[0008] Furthermore, a pulley mounting pin is inserted into the pulley, and the pulley mounting pin is fixedly connected to both sides of one end of the frame.

[0009] Furthermore, a shock-absorbing pad is fixedly connected to one end of the top guide rail of the frame 1 away from the frame 2.

[0010] Furthermore, a guide rail holder is provided at the bottom of the mounting frame near one end of the switch rope, and the guide rail holder is clamped in the guide rail.

[0011] Furthermore, two sides of the mounting frame close to one end of the guide rail holder are fixedly connected with rubber band fixing screws, and the rubber band fixing screws are fixedly connected to one end of the rubber band away from the traction rope.

[0012] Furthermore, ejection hooks are provided on the tops of the aircraft support frame and the aircraft rear support frame.

[0013] The advantages of the utility model compared with the existing technology are:

[0014] (1) The folding member can be used to overlap the frame one and the frame two, and the support frame connecting member can be used to install the support frame at the end of the frame one. At the same time, the support frame can be overlapped with the frame one through the support frame connecting member, thereby reducing the overall volume so that the structure takes up the minimum space when not in use, which is convenient to carry.

[0015] (2) After placing the aircraft on top of the aircraft support frame and the rear aircraft support frame, pull the release switch through the switch rope. The release switch is a locking switch. After opening, the elastic potential energy is released and acts on the mounting frame. The aircraft support frame and the rear aircraft support frame are installed on the aircraft through the ejection hook on the top, and the elastic potential energy is converted into kinetic energy, which acts on the aircraft, causing the aircraft to generate a certain amount of kinetic energy and fly forward and upward along the direction of the rack one and the rack two. In a very short time, after the aircraft is ejected from the ejection rack, the aircraft's own power is turned on, allowing the aircraft to complete the flight mission. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 The utility model is a three-dimensional structure of a single-person ejectable drone device Figure 1 .

[0017] Figure 2 The utility model is a three-dimensional structure of a single-person ejectable drone device Figure 2 .

[0018] Figure 3 The utility model is a three-dimensional structural diagram of a mounting frame of a single-person ejectable unmanned aerial vehicle device.

[0019] Figure 4 The utility model discloses a folding structure diagram of a single-person ejectable unmanned aerial vehicle device.

[0020] Figure 5 The utility model discloses a guide rail structure diagram of a single-person ejectable unmanned aerial vehicle device.

[0021] As shown in the figure: 1. Frame one; 2. Frame two; 3. Folding part; 4. Pulley; 5. Support frame; 6. Rear support frame; 7. Guide rail; 8. Mounting frame; 9. Hand winch; 10. Towing rope; 11. Rubber band; 12. Release switch; 13. Switch rope; 14. Aircraft support frame; 15. Aircraft rear support frame; 16. Support frame connector; 17. Pulley mounting pin; 18. Shock-absorbing cushion; 19. Guide rail holder; 20. Rubber band fixing screw; 21. Ejection hook. DETAILED DESCRIPTION

[0022] The specific implementation of the utility model is further described below in conjunction with the accompanying drawings, wherein the same parts are represented by the same reference numerals.

[0023] It should be noted that the words "front", "rear", "left", "right", "up" and "down" used in the following description refer to directions in the drawings, and the words "inside" and "outside" refer to directions toward or away from the geometric center of a specific component, respectively.

[0024] In order to make the contents of the present invention more clearly understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention.

[0025] like Figures 1 to 5As shown, it includes a frame 1 and a frame 2, a folding member 3 is provided on one side of the connection between the frame 1 and the frame 2, a support frame 5 is provided at the bottom of both sides of the end of the frame 1 away from the frame 2, a rear support frame 6 is provided at the bottom of the end of the frame 2 away from the frame 1, the support frame 5 and the rear support frame 6 are used in conjunction with each other to support the frame 1 and the frame 2, a support frame connecting member 16 is provided between the support frame 5 and the end of the frame 1, the support frame connecting member 16 is rotatably connected to the frame 1, guide rails 7 are provided on the top of the frame 1 and the frame 2, the two guide rails 7 are connected, the guide rails 7 limit the left and right, up and down movement of the aircraft on the frame, but do not limit its forward and backward movement, a mounting frame 8 is provided on the top of the end of the frame 2 away from the frame 1, and the bottom of the mounting frame 8 is close to the switch rope 13. A guide rail holder 19 is provided at the end, and the guide rail holder 19 is clamped in the guide rail 7. By using the mounting frame 8 in conjunction with the guide rail 7, the friction of the mounting frame 8 on the frame 1 and the frame 2 can be reduced, the energy efficiency conversion rate can be improved, and the aircraft can be given a greater ejection rate. A hand winch 9 is provided at the bottom of the end of the frame 2 close to the rear support frame 6. A traction rope 10 is wound and connected in the hand winch 9. The traction rope 10 is fixedly connected to the end of the hand winch 9 away from the hand winch 9. Pulleys 4 are provided on both sides of the end of the frame 1 away from the frame 2, and the rubber band 11 is sleeved on the outside of the pulley 4. A pulley mounting pin 17 is inserted in the pulley 4. The pulley mounting pin 17 is fixedly connected to both sides of the end of the frame 1, and the pulley mounting pin 17 is used in conjunction with the pulley 4 to facilitate the rubber band 11 The passing rate between the pulley 4, and the end of the rubber band 11 away from the traction rope 10 is connected to the end of the mounting frame 8, and the two sides of the mounting frame 8 close to the guide rail card seat 19 are fixedly connected with rubber band fixing screws 20, and the rubber band fixing screws 20 are fixedly connected to the end of the rubber band 11 away from the traction rope 10. By manually rotating the hand winch 9, the rubber band 11 is pulled by the traction rope 10. At this time, the rubber band 11 is stretched and stored to generate elastic potential energy. A release switch 12 is provided at the bottom of the mounting frame 8, and a switch rope 13 is provided at one end of the release switch 12. An aircraft support frame 14 is provided at the top of the mounting frame 8. Aircraft rear support frames 15 are provided on both sides of the top of the mounting frame 8 close to the rear support frame 6. The aircraft is placed on the top of the aircraft support frame 14 and the aircraft rear support frame 15 After that, the release switch 12 is pulled by the switch rope 11. The release switch 12 is a locking switch. After it is opened, the elastic potential energy is released and acts on the mounting frame 8. The aircraft support frame 14 and the aircraft rear support frame 15 install the aircraft through the ejection hook 21 on the top, and the elastic potential energy is converted into kinetic energy, which acts on the aircraft, so that the aircraft generates a certain amount of kinetic energy and flies forward and upward along the direction of the rack 1 and the rack 2. In a very short time, after the aircraft is ejected from the ejection frame, the aircraft's own power is turned on, so that the aircraft completes the flight mission. The top guide rail 7 of the rack 1 is fixedly connected to the end away from the rack 2. The end of the rack 2 is fixedly connected with a shock-absorbing pad 18. The mounting frame 8 and the shock-absorbing pad 18 can be used in conjunction with each other to reduce the impact damage between the mounting frame and the rack 1 after the aircraft is ejected.

[0026] The folding member 3 can overlap the frame 1 and the frame 2 2, and the support frame connecting member 16 can install the support frame 5 on the end of the frame 1. At the same time, the support frame 5 can overlap with the frame 1 through the support frame connecting member 16, so as to reduce the overall volume and make the structure occupy the minimum space when not in use, which is convenient to carry.

[0027] The above description of the utility model and its implementation methods is not restrictive. The drawings show only one implementation method of the utility model, and the actual structure is not limited thereto. In short, if ordinary technicians in this field are inspired by it and design structural methods and embodiments similar to the technical solution without creativity without departing from the purpose of the invention of the utility model, they should all fall within the protection scope of the utility model.

Claims

1. A single-person ejectable drone device, characterized in that: The invention comprises a frame 1 (1) and a frame 2 (2), wherein a folding member (3) is provided at the bottom of the connection between the frame 1 (1) and the frame 2 (2), pulleys (4) are provided on both sides of the end of the frame 1 (1) away from the frame 2 (2), support frames (5) are provided at the bottom of both sides of the end of the frame 1 (1) away from the frame 2 (2), a rear support frame (6) is provided at the bottom of the end of the frame 2 (2) away from the frame 1 (1), guide rails (7) are provided at the top of the frame 1 (1) and the frame 2 (2), and the two guide rails (7) are connected, a mounting frame (8) is provided at the top of the end of the frame 2 (2) away from the frame 1 (1), and the mounting frame (8) is clamped in the guide rail (7), and the frame 2 (2) is close to the rear support frame (6). A hand winch (9) is provided at the bottom of one end of the support frame (6), a traction rope (10) is wound and connected in the hand winch (9), a rubber band (11) is fixedly connected to one end of the traction rope (10) away from the hand winch (9), the rubber band (11) is sleeved on the outside of the pulley (4), and the end of the rubber band (11) away from the traction rope (10) is connected to the end of the mounting frame (8), a release switch (12) is provided at the bottom of the mounting frame (8), a switch rope (13) is provided at one end of the release switch (12), an aircraft support frame (14) is provided at the top of the mounting frame (8), and aircraft rear support frames (15) are provided on both sides of the top of the mounting frame (8) close to one end of the rear support frame (6).

2. The single-person ejectable drone device according to claim 1, characterized in that: A support frame connecting piece (16) is provided between the support frame (5) and the end of the frame one (1), and the support frame connecting piece (16) is rotatably connected to the frame one (1).

3. The one-person ejectable drone device according to claim 1, characterized in that: A pulley mounting pin (17) is inserted into the pulley (4), and the pulley mounting pin (17) is fixedly connected to both sides of the end of the frame (1).

4. The one-person ejectable drone device according to claim 1, characterized in that: A shock-absorbing cushion (18) is fixedly connected to one end of the top guide rail (7) of the frame one (1) away from the frame two (2).

5. The one-person ejectable drone device according to claim 1, characterized in that: A guide rail clamping seat (19) is provided at the bottom of the mounting frame (8) near one end of the switch rope (13), and the guide rail clamping seat (19) is clamped in the guide rail (7).

6. The one-person ejectable drone device according to claim 1, characterized in that: The two sides of the mounting frame (8) close to one end of the guide rail holder (19) are fixedly connected with rubber band fixing screws (20), and the rubber band fixing screws (20) are fixedly connected to one end of the rubber band (11) away from the traction rope (10).

7. The one-person ejectable drone device according to claim 1, characterized in that: The tops of the aircraft support frame (14) and the aircraft rear support frame (15) are both provided with ejection hooks (21).

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