A safety airbag triggering mechanism for low-altitude aircraft

Abstract

This utility model relates to the field of aircraft safety technology and discloses a safety airbag triggering mechanism for low-altitude aircraft. It includes a mounting cylinder with a release port at the bottom and a protective cover inside the release port. A lead screw is fixedly connected to the top of the mounting cylinder, and a rotating nut is threaded onto the lead screw. A connecting rod is fixedly connected to the rotating nut, and a rotating lifting plate is fixedly connected to the connecting rod. A folding parachute is housed in the airbag compartment between the rotating lifting plate and the protective cover. A first counterweight is fixedly connected to the edge of the folding parachute, and a fixing block is fixedly connected to the connecting rope of the folding parachute. The fixing block is fixedly connected to the rotating lifting plate. This utility model senses the aircraft's descent attitude through a second counterweight. When the aircraft flips, the folding parachute rapidly rotates and unfolds under centrifugal force, thereby reducing the aircraft's descent speed and improving its safety.

Description

Technical Field

[0001] This utility model relates to the field of aircraft safety technology, specifically a safety airbag triggering mechanism for low-altitude aircraft. Background Technology

[0002] Currently, some drones use parachute devices to prevent them from crashing out of control, which can easily lead to injuries or damage to pedestrians and other facilities, and even cause the drone to break. The parachute device mainly uses a spring-loaded ejection method to launch the parachute. However, during use, because drones are very prone to flipping during a fall, the parachute is usually installed on the top of the drone. If the drone flips, the parachute will bounce downwards, causing it to fail. Utility Model Content

[0003] The purpose of this invention is to provide a safety airbag triggering mechanism for low-altitude aircraft to solve the problems mentioned in the background art.

[0004] To achieve the above objectives, this utility model provides the following technical solution:

[0005] A safety airbag triggering mechanism for a low-altitude aircraft includes a mounting cylinder with a release port at its bottom and a protective cover inside the release port. A lead screw is fixedly connected to the top of the mounting cylinder, and a rotating nut is threaded onto the lead screw. A connecting rod is fixedly connected to the rotating nut, and a rotating lifting plate is fixedly connected to the connecting rod. A folding parachute is disposed in the airbag compartment between the rotating lifting plate and the protective cover. A first counterweight is fixedly connected to the edge of the folding parachute, and a fixing block is fixedly connected to the connecting rope of the folding parachute. The fixing block is fixedly connected to the rotating lifting plate. A spring connects the top of the mounting cylinder and the rotating lifting plate. A release assembly for controlling the release of the rotating lifting plate is disposed inside the mounting cylinder.

[0006] As a further embodiment of this utility model: a mounting plate is fixedly connected to the bottom of the mounting cylinder, and mounting holes are provided in the mounting plate.

[0007] As a further embodiment of this utility model, a limiting block is fixedly connected to the lead screw.

[0008] As a further embodiment of this utility model: the release component includes a limiting slot disposed on the side of the rotating lifting plate, an installation groove disposed on the side of the mounting cylinder, a fixing frame fixedly connected to the outer wall of the installation groove, a rotating buckle rotatably connected inside the fixing frame, the rotating buckle passing through the installation groove and disposed in the limiting slot, and a torsion spring disposed between the rotating buckle and the fixing frame.

[0009] As a further embodiment of this utility model: a fixed cylinder is fixedly connected to the top of the mounting cylinder, a telescopic rod is slidably connected inside the fixed cylinder, a second counterweight is fixedly connected to the telescopic rod, a connecting frame is fixedly connected to the second counterweight, a limit rod is fixedly connected to the connecting frame, a limit groove is provided inside the rotating buckle, and the limit rod is set inside the limit groove.

[0010] As a further improvement of this utility model: a solenoid valve is fixedly connected to the side wall of the rotating buckle, and the solenoid valve cooperates with the limiting groove.

[0011] Compared with the prior art, the beneficial effects of this utility model are: this utility model senses the falling attitude of the aircraft through the second counterweight. When the aircraft flips, the folding parachute rotates and unfolds rapidly under the action of centrifugal force, thereby reducing the falling speed of the aircraft through the parachute and improving the safety of the aircraft. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the structure of a safety airbag triggering mechanism for a low-altitude aircraft according to the present invention.

[0013] Figure 2 This is a schematic diagram of the internal structure of a safety airbag triggering mechanism for a low-altitude aircraft according to the present invention.

[0014] Figure 3 This is a cross-sectional view of a low-altitude aircraft airbag triggering mechanism according to the present invention.

[0015] In the diagram: 1-Installation cylinder, 2-Installation plate, 3-Installation hole, 4-Screw rod, 5-Rotating nut, 6-Connecting rod, 7-Rotating lifting plate, 8-Spring, 9-Protective cover, 10-Airbag compartment, 11-Folding umbrella bag, 12-Fixing block, 13-Connecting rope, 14-First counterweight block, 15-Installation groove, 16-Limiting slot, 17-Fixing cylinder, 18-Telescopic rod, 19-Second counterweight block, 20-Connecting frame, 21-Fixing frame, 22-Rotating buckle, 23-Limiting groove, 24-Limiting rod, 25-Solenoid valve, 26-Limiting block. Detailed Implementation

[0016] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0017] See Figures 1-3In this embodiment of the present invention, a safety airbag triggering mechanism for a low-altitude aircraft includes an installation cylinder 1. A release port is provided at the bottom of the installation cylinder 1, and a protective cover 9 is provided inside the release port. A lead screw 4 is fixedly connected to the top of the installation cylinder 1, and a rotating nut 5 is threaded onto the lead screw 4. A connecting rod 6 is fixedly connected to the rotating nut 5, and a rotating lifting plate 7 is fixedly connected to the connecting rod 6. A folding parachute 11 is provided in the airbag compartment 10 between the rotating lifting plate 7 and the protective cover 9. A first counterweight 14 is fixedly connected to the edge of the folding parachute 11. A fixing block 12 is fixedly connected to the connecting rope 13 of the folding parachute 11, and the fixing block 12 is fixedly connected to the rotating lifting plate 7. A spring 8 is connected between the top of the installation cylinder 1 and the rotating lifting plate 7. A release assembly for releasing the rotating lifting plate 7 is provided inside the installation cylinder 1. The present invention first installs and fixes the installation cylinder 1 to the aircraft. At the bottom, when the aircraft loses power and flips during flight, the release assembly releases the limit on the rotating lifting plate 7. At this time, the spring 8 pushes the rotating lifting plate 7 towards the release port. During this process, the rotating lifting plate 7 drives the rotating nut 5 to move on the screw 4 through the connecting rod 6. During this process, the linear motion of the rotating nut 5 is converted into the rotational motion of the rotating nut 5 through the threaded connection between the screw 4 and the rotating nut 5. The rotating nut 5 drives the rotating lifting plate 7 to rotate and rise through the connecting rod 6. At this time, the rotating lifting plate 7 drives the folding parachute 11 to rotate and push out. During this process, the folding parachute 11 pushes the protective cover 9 to come out, and the folding parachute 11 rotates during this process. At this time, the first counterweight 14 drives the folding parachute 11 to rotate and unfold rapidly under the action of centrifugal force, thereby reducing the descent speed of the aircraft through the parachute and improving the safety of the aircraft.

[0018] In one instance of this embodiment, please refer to Figures 1-3 The bottom of the mounting cylinder 1 is fixedly connected to a mounting plate 2, and a mounting hole 3 is provided in the mounting plate 2. This utility model fixes the mounting cylinder 1 to the bottom of the aircraft by setting the mounting plate 2 and the mounting hole 3.

[0019] In one instance of this embodiment, please refer to Figures 1-3 A limiting block 26 is fixedly connected to the lead screw 4. The present invention limits the position of the rotating nut 5 on the lead screw 4 by setting the limiting block 26, thereby preventing the rotating nut from coming off.

[0020] In one instance of this embodiment, please refer to Figures 1-3The release assembly includes a limiting slot 16 located on the side of the rotating lifting plate 7. An installation groove 15 is provided on the side of the installation cylinder 1. A fixing frame 21 is fixedly connected to the outer wall of the installation groove 15. A rotating buckle 22 is rotatably connected inside the fixing frame 21. The rotating buckle 22 passes through the installation groove 15 and is located within the limiting slot 16. A torsion spring is provided between the rotating buckle 22 and the fixing frame 21. A fixing cylinder 17 is fixedly connected to the top of the installation cylinder 1. A telescopic rod 18 is slidably connected inside the fixing cylinder 17. A second counterweight 19 is fixedly connected to the telescopic rod 18. A connecting frame 20 is fixedly connected to the second counterweight 19. A limiting rod 24 is fixedly connected to the connecting frame 20. A limiting groove 23 is provided inside the rotating buckle 22, and the limiting rod 24 is located within the limiting groove 23. This utility model firstly utilizes the mutual interlocking of the rotating buckle 22 and the limiting slot 16. The rotating lifting plate 7 is limited to restrict its rotation. At the same time, a set of rotational driving force is applied to the rotating buckle 22 through the torsion spring, thereby driving the rotating buckle 22 to reverse and disengage from the limiting groove 16. When the release component is in the locked state, the limiting rod 24 is inserted into the limiting groove 23, thereby limiting the rotating buckle 22 and preventing it from reversing and disengaging from the limiting groove 16. However, when the aircraft loses power and flips during the fall, causing the bottom to face upward, the second counterweight 19 moves towards the fixed cylinder 17 under the action of gravity. The second counterweight 19 drives the limiting rod 24 to disengage from the limiting groove 23 through the connecting frame 20. At this time, the rotating buckle 22 loses its limit, the torsion spring releases energy, thereby rotating and disengaging the rotating buckle 22 from the limiting groove 16. At this time, the rotating lifting plate 7 loses its limit.

[0021] In one instance of this embodiment, please refer to Figures 1-3 A solenoid valve 25 is fixedly connected to the side wall of the rotating buckle 22. The solenoid valve 25 cooperates with the limiting groove 23. When the present invention is in a stopped state, the solenoid valve 25 extends to lock the limiting groove 23, thereby preventing the limiting rod 24 from coming off due to the operator flipping the equipment. When the equipment is in flight and suddenly loses power, the solenoid valve 25 is controlled to contract, thereby opening the limiting groove 23.

[0022] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. It will be apparent to those skilled in the art that this utility model is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or basic characteristics of this utility model. Therefore, the embodiments should be considered exemplary and non-limiting in all respects. The scope of this utility model is defined by the appended claims rather than the foregoing description, and thus all variations falling within the meaning and scope of equivalents of the claims are intended to be included within this utility model. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0023] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A safety airbag triggering mechanism for low-altitude aircraft, comprising a mounting cylinder, characterized in that, The bottom of the mounting cylinder has a release port, and a protective cover is installed inside the release port. A lead screw is fixedly connected to the top of the mounting cylinder, and a rotating nut is threaded onto the lead screw. A connecting rod is fixedly connected to the rotating nut, and a rotating lifting plate is fixedly connected to the connecting rod. A folding umbrella is installed in the airbag chamber between the rotating lifting plate and the protective cover. A first counterweight is fixedly connected to the edge of the folding umbrella. A fixing block is fixedly connected to the connecting rope of the folding umbrella, and the fixing block is fixedly connected to the rotating lifting plate. A spring is connected between the top of the mounting cylinder and the rotating lifting plate. A release component for releasing the rotating lifting plate is installed inside the mounting cylinder.

2. The airbag triggering mechanism for a low-altitude aircraft according to claim 1, characterized in that, The bottom of the mounting cylinder is fixedly connected to a mounting plate, and the mounting plate has mounting holes.

3. The airbag triggering mechanism for a low-altitude aircraft according to claim 1, characterized in that, A limit block is fixedly connected to the lead screw.

4. The airbag triggering mechanism for a low-altitude aircraft according to claim 1, characterized in that, The release assembly includes a limiting slot disposed on the side of the rotating lifting plate, an installation slot disposed on the side of the installation cylinder, a fixing frame fixedly connected to the outer wall of the installation slot, a rotating buckle rotatably connected inside the fixing frame, the rotating buckle passing through the installation slot and disposed in the limiting slot, and a torsion spring disposed between the rotating buckle and the fixing frame.

5. The airbag triggering mechanism for a low-altitude aircraft according to claim 4, characterized in that, A fixed cylinder is fixedly connected to the top of the mounting cylinder, and a telescopic rod is slidably connected inside the fixed cylinder. A second counterweight is fixedly connected to the telescopic rod, and a connecting frame is fixedly connected to the second counterweight. A limit rod is fixedly connected to the connecting frame, and a limit groove is provided inside the rotating buckle. The limit rod is located inside the limit groove.

6. The airbag triggering mechanism for a low-altitude aircraft according to claim 5, characterized in that, A solenoid valve is fixedly connected to the side wall of the rotating buckle, and the solenoid valve cooperates with the limiting groove.

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