Lightweight aircraft weightlessness emergency protection system

Abstract

The lightweight aircraft weightlessness emergency protection system relates to the technical field of weightlessness protection and comprises an unmanned aerial vehicle body, a sealing plate is connected to the upper surface of the unmanned aerial vehicle body in a limiting mode, and an elastic assembly is arranged on the upper surface of the unmanned aerial vehicle body and located below the sealing plate. An elastic assembly is arranged on the upper surface of the unmanned aerial vehicle body, a parachute bag is arranged in the middle of the elastic assembly, the elastic assembly comprises an annular plate, a T-shaped block is slidably connected to the upper surface of the unmanned aerial vehicle body, a connecting rod is arranged between the T-shaped block and the annular plate, and a storage cavity used for storing the parachute bag is formed in the middle of the upper surface of the unmanned aerial vehicle body. According to the lightweight aircraft weightlessness emergency protection system, through the effect of the parachute bag on the upper surface of the unmanned aerial vehicle body, when weightlessness crash and falling occur, the parachute bag can be opened, the falling speed of the unmanned aerial vehicle body can be reduced, and therefore damage to passers-by and the unmanned aerial vehicle body can be reduced and avoided.

Description

Technical Field

[0001] The utility model relates to the technical field of weightlessness protection, in particular to a lightweight aircraft weightlessness emergency protection system. Background Art

[0002] There are many types of lightweight aircraft, one of which is the UAV, which is an unmanned aircraft controlled by a radio remote control device and a self-contained program control device. UAV is actually a general term for unmanned aircraft. From a technical point of view, it can be divided into: unmanned fixed-wing aircraft, unmanned vertical take-off and landing aircraft, unmanned airship, unmanned helicopter, unmanned multi-rotor aircraft, unmanned paraglider, etc. Compared with manned aircraft, it has the advantages of small size, low cost, and easy use.

[0003] When a drone encounters strong airflow during flight, it is very easy to cause the fuselage to become unstable, resulting in a weightless crash. A drone falling at high speed will not only pose a safety hazard to passers-by walking nearby, but will also collide violently with the ground when it falls, causing damage and causing certain economic losses to the owner. Utility Model Content

[0004] The purpose of the utility model is to provide a lightweight aircraft weightlessness emergency protection system to solve the problem that the UAV proposed in the above background technology encounters a large airflow during flight, which easily causes the fuselage to be unstable, thereby causing weightlessness and crashing. The high-speed falling UAV will not only cause safety hazards to passers-by walking nearby, but will also collide violently with the ground when falling, thereby being damaged, causing certain economic losses to the owner of the UAV.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a lightweight aircraft weightlessness emergency protection system, comprising a drone body, the upper surface of the drone body is limitedly connected to a sealing plate, an elastic component is arranged on the upper surface of the drone body and below the sealing plate, a parachute bag is arranged in the middle of the elastic component, the elastic component includes an annular plate, a T-shaped block is slidably connected to the upper surface of the drone body, a connecting rod is arranged between the T-shaped block and the annular plate, and a storage cavity for storing the parachute bag is opened in the middle of the upper surface of the drone body.

[0006] Preferably, a magnetic switch is fixedly installed on the side where the drone body and the cover plate are close to each other.

[0007] Preferably, a T-shaped slot matching the T-shaped block is provided on the upper surface of the UAV body, and a connecting slot connecting the T-shaped slot and the storage cavity is also provided on the upper surface of the UAV body, and the connecting rod is arranged in the connecting slot.

[0008] Preferably, a first spring is arranged in the T-shaped slot, and two ends of the first spring are fixedly connected to the T-shaped slot and the T-shaped block respectively.

[0009] Preferably, the annular plate is coaxial with the storage chamber, and both ends of the connecting rod are rotatably connected to the annular plate and the T-shaped block respectively.

[0010] Preferably, a squeezing device for ejecting the parachute bag is provided in the storage cavity, and the squeezing device includes a squeezing plate slidably connected to the storage cavity, a second spring is provided between the lower surface of the squeezing plate and the storage cavity, and two ends of the second spring are respectively fixedly connected to the squeezing plate and the storage cavity.

[0011] Compared with the prior art, the utility model has the following beneficial effects: the lightweight aircraft weightlessness emergency protection system, through the action of the parachute bag on the upper surface of the drone body, can open the parachute bag when a weightlessness crash occurs, reducing the falling speed of the drone body, thereby reducing and avoiding damage to passers-by and the drone body itself;

[0012] By setting an elastic component between the parachute bag and the drone body, the elastic component pops out at the same time as the parachute bag is ejected, so that the parachute rope of the parachute bag is relatively far away from the wing of the drone body, avoiding the wing from being entangled in the rope, causing damage to the wing and making it impossible to open the parachute bag normally. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0014] Figure 2 This is a schematic diagram of the structure of the utility model after the sealing plate is opened;

[0015] Figure 3 This is an exploded schematic diagram of the elastic component and the UAV body connection structure of the utility model;

[0016] Figure 4 This is a schematic diagram of the structure of the elastic component of the utility model;

[0017] Figure 5 It is a schematic cross-sectional view of the storage cavity structure of the utility model.

[0018] In the figure: 1. UAV body; 11. T-shaped slot; 12. Connecting slot; 13. Storage chamber; 2. Closing plate; 3. Elastic component; 31. Connecting rod; 32. T-shaped block; 33. Ring plate; 34. First spring; 41. Extrusion plate; 42. Second spring; 5. Magnetic switch. DETAILED DESCRIPTION

[0019] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0020] See also Figure 1-5 The utility model provides a technical solution: a lightweight aircraft weightlessness emergency protection system, including a drone body 1, the upper surface of the drone body 1 is limitedly connected with a sealing plate 2, an elastic component 3 is arranged on the upper surface of the drone body 1 and below the sealing plate 2, a parachute bag is arranged in the middle of the elastic component 3, the elastic component 3 includes an annular plate 33, a T-shaped block 32 is slidably connected to the upper surface of the drone body 1, a connecting rod 31 is arranged between the T-shaped block 32 and the annular plate 33, and a storage cavity 13 for storing the parachute bag is opened in the middle of the upper surface of the drone body 1.

[0021] Specifically, the UAV body 1 is of prior art, and the sealing plate 2 compresses the elastic component 3 to put it in a compressed state. After the sealing plate 2 pops out and falls, the elastic component 3 can pop out, thereby driving the parachute rope of the parachute bag to be relatively away from the wing to prevent the parachute rope from being entangled in the wing. The parachute bag is of prior art and opens after popping out, thereby reducing the falling speed of the UAV body 1.

[0022] A magnetic switch 5 is fixedly installed on the side where the drone body 1 and the cover plate 2 are close to each other.

[0023] Specifically, the magnetic switch 5 is a prior art, and is connected to the control handle of the drone body 1 by radio, so that when the drone body 1 loses weight, the magnetic switch 5 can be manually opened to separate the sealing plate 2 from the drone body 1.

[0024] The upper surface of the drone body 1 is provided with a T-shaped slot 11 matching the T-shaped block 32 . The upper surface of the drone body 1 is also provided with a connecting slot 12 connecting the T-shaped slot 11 and the storage cavity 13 . The connecting rod 31 is arranged in the connecting slot 12 .

[0025] Specifically, the T-shaped blocks 32 slide in the T-shaped slots 11 and approach each other. Under the action of the connecting rod 31 , the annular plate 33 is driven away from the drone body 1 , and the parachute rope of the parachute bag is fixedly connected to the annular plate 33 .

[0026] A first spring 34 is disposed in the T-shaped slot 11 , and two ends of the first spring 34 are fixedly connected to the T-shaped slot 11 and the T-shaped block 32 , respectively.

[0027] Specifically, the first spring 34 drives the T-shaped blocks 32 to slide in the T-shaped slot 11 and approach each other.

[0028] The annular plate 33 is coaxial with the storage chamber 13 , and both ends of the connecting rod 31 are rotatably connected to the annular plate 33 and the T-shaped block 32 respectively.

[0029] Specifically, the parachute bag is stored in the storage chamber 13 and is moved out through the center of the annular plate 33 when ejected.

[0030] A squeezing device for ejecting the parachute bag is provided in the storage cavity 13, and the squeezing device includes a squeezing plate 41 slidably connected to the storage cavity 13, and a second spring 42 is provided between the lower surface of the squeezing plate 41 and the storage cavity 13, and the two ends of the second spring 42 are fixedly connected to the squeezing plate 41 and the storage cavity 13 respectively.

[0031] Specifically, when the sealing plate 2 is separated from the UAV body 1 , the squeezing device ejects the parachute bag away from the UAV body 1 .

[0032] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A lightweight aircraft weightlessness emergency protection system, characterized by: The invention comprises a drone body (1); The upper surface of the drone body (1) is limitedly connected to a sealing plate (2); An elastic component (3) is provided on the upper surface of the drone body (1) and below the sealing plate (2), and a parachute bag is provided in the middle of the elastic component (3); The elastic component (3) comprises an annular plate (33), a T-shaped block (32) is slidably connected to the upper surface of the drone body (1), and a connecting rod (31) is provided between the T-shaped block (32) and the annular plate (33); A storage cavity (13) for storing a parachute bag is provided in the middle of the upper surface of the drone body (1).

2. A lightweight aircraft weightlessness emergency protection system according to claim 1, characterized in that: A magnetic switch (5) is fixedly mounted on the side of the drone body (1) and the cover plate (2) that are close to each other.

3. A lightweight aircraft weightlessness emergency protection system according to claim 1, characterized in that: The upper surface of the drone body (1) is provided with a T-shaped groove (11) matching the T-shaped block (32), and the upper surface of the drone body (1) is also provided with a connecting groove (12) connecting the T-shaped groove (11) and the storage cavity (13) to each other, and the connecting rod (31) is arranged in the connecting groove (12).

4. A lightweight aircraft weightlessness emergency protection system according to claim 3, characterized in that: A first spring (34) is arranged in the T-shaped slot (11), and two ends of the first spring (34) are respectively fixedly connected to the T-shaped slot (11) and the T-shaped block (32).

5. A lightweight aircraft weightlessness emergency protection system according to claim 1, characterized in that: The annular plate (33) is coaxial with the storage chamber (13), and the two ends of the connecting rod (31) are rotatably connected to the annular plate (33) and the T-shaped block (32) respectively.

6. A lightweight aircraft weightlessness emergency protection system according to claim 1, characterized in that: A squeezing device for ejecting the parachute bag is arranged in the storage cavity (13), the squeezing device comprising a squeezing plate (41) slidably connected to the storage cavity (13), a second spring (42) being arranged between the lower surface of the squeezing plate (41) and the storage cavity (13), and two ends of the second spring (42) being fixedly connected to the squeezing plate (41) and the storage cavity (13), respectively.

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