An emergency landing protection structure for a rotary-wing UAV

Abstract

The utility model discloses an emergency landing protection structure for a rotary-wing unmanned aerial vehicle, belonging to the technical field of rotary-wing unmanned aerial vehicles. The key points of the technical solution include an unmanned aerial vehicle body, wherein the unmanned aerial vehicle body is provided with rotors all around, and a speed monitor is embedded in the bottom of the front side of the unmanned aerial vehicle body. By arranging the unmanned aerial vehicle body, the speed monitor, the storage box, the top plate, the microprocessor, the V-shaped closing plate, the detonator, the sodium azide substance, the speed reduction component, the support tube, the buffer component and the reinforcement component, the storage battery inside the unmanned aerial vehicle body supplies power to various monitors and electronic components inside, so that the rotor rotates to make the unmanned aerial vehicle body take off, and then when the unmanned aerial vehicle body loses power and falls downward, the speed monitor detects and feeds back to the microprocessor inside the rear storage box, and then the microprocessor quickly responds and issues an opening command to the detonator located on the top of the bottom plate.

Description

Technical Field

[0001] The utility model relates to the technical field of rotary-wing unmanned aerial vehicles, and in particular to an emergency landing protection structure for rotary-wing unmanned aerial vehicles. Background Art

[0002] Unmanned aerial vehicles, also known as "drones", are unmanned aircraft that are controlled by radio remote control equipment and self-contained program control devices, or are operated completely or intermittently autonomously by on-board computers. During flight, drones can easily lose power due to collisions or signal shielding, which can cause the drone to be unable to hover in the air and cause a crash.

[0003] At present, a Chinese utility model with announcement number: CN211996179U discloses a safe landing mechanism for a multi-rotor UAV. This utility model provides a safe landing mechanism for a multi-rotor UAV, which belongs to the technical field of UAV landing protection. This safe landing mechanism for a multi-rotor UAV includes a UAV body and an emergency landing protection component. The emergency landing protection component includes an elastic telescopic part, a gliding cloth layer, a locking part, a gyroscope sensor and an emergency switch. A accommodating area is provided between adjacent wings of the UAV body, and slide rails are provided on both sides of the wings of the UAV body. The number of elastic telescopic parts is set to twice that of the wings. The elastic telescopic part includes a spring I, a punch block part and a limit part. The spring I is connected to the inner wall of the accommodating area. The punch block part includes a fixed block, a punch block, a slide rod and a plug-in cavity I and a plug-in cavity II. The emergency landing protection component can use the gliding cloth layer to decelerate when the fuselage falls, protect the fuselage, and improve the safety of the operation.

[0004] Most of the existing rotor UAVs perform emergency landings by parachutes, but general parachutes have a slow opening speed, and the UAV often falls to the ground and crashes before it can be fully opened, which is insufficient. Therefore, an emergency landing protection structure for rotor UAVs is proposed to solve the problem. Utility Model Content

[0005] The utility model provides an emergency landing protection structure for a rotary-wing UAV, aiming to solve the problem that the emergency landing of the existing rotary-wing UAV is mostly carried out by parachute, but the general parachute has a slow opening speed, and the UAV often falls to the ground and is destroyed before it can be fully opened, which leads to inadequate use.

[0006] The utility model is implemented as follows: an emergency landing protection structure for a rotary-wing UAV comprises a UAV body, wherein the UAV body is provided with rotors all around, a speed monitor is embedded in the bottom of the front side of the UAV body, a storage box is embedded in the inner side of the top of the UAV body, a top plate is clamped on the top of the storage box, a microprocessor is bolted to the bottom side of the storage box, the microprocessor is electrically connected to the speed monitor, a bottom plate is bolted to the bottom side of the storage box, and the top of the storage box is A V-shaped closing plate is provided at the bottom, a detonator is bolted to the top of the bottom plate, the detonator is electrically connected to the microprocessor, the detonating end of the detonator passes through the bottom of the V-shaped closing plate, a sodium azide substance is provided on the top of the V-shaped closing plate, a speed reduction component is provided on the top side of the storage box, the bottom of the speed reduction component is bolted and sealed to the V-shaped closing plate, support tubes are bolted to the four corners of the bottom of the drone body, a buffer component is provided inside the support tube, and reinforcement components are provided on both sides of the support tube and the buffer component;

[0007] The deceleration assembly includes a carrier plate, a wire wheel, a steel wire rope and a parachute. The carrier plate is bolted to two sides of the storage box respectively, the wire wheel is bolted to the top of the carrier plate, the steel wire rope is wound around the surface of the wire wheel, the parachute is arranged inside the carrier plate, the outer side of the parachute is in contact with the inner side of the carrier plate, the outer side of the parachute is bolted to the inner side of the steel wire rope, and the parachute is located on top of the sodium azide substance.

[0008] In order to further achieve the effect of providing a buffer when the UAV body is supported on the ground for emergency landing, the emergency landing protection structure for a rotary-wing UAV of the utility model is preferably such that the buffer assembly includes a spring, a buffer rod and a caster, the spring being arranged inside a support tube, the buffer rod being slidably connected to the bottom side of the support tube, the top of the buffer rod being in contact with the bottom of the spring, and the caster being bolted to the bottom of the buffer rod.

[0009] In order to achieve the effect of reinforcing the buffer component, as a preferred emergency landing protection structure for a rotorcraft UAV of the utility model, the reinforcement component includes a top block, a bottom block, a first rotating rod and a second rotating rod, the top block is bolted to both sides of the support tube, the bottom block is respectively bolted to both sides of the caster, the inner side of the first rotating rod is rotatably connected to the outer side of the top block, the inner side of the second rotating rod is rotatably connected to the outer side of the bottom block, and the second rotating rod is rotatably connected to the first rotating rod.

[0010] In order to achieve the effect of improving the support and reinforcement of the V-shaped closing plate, as a preferred emergency landing protection structure for a rotary-wing UAV of the utility model, a V-shaped reinforcing rod is bolted to the bottom of the V-shaped closing plate, and reinforcing ribs are arranged inside the V-shaped reinforcing rod.

[0011] In order to achieve the effect of lifting the parachute and balancing both sides after being ejected, as a preferred emergency landing protection structure for a rotary-wing UAV of the utility model, both sides of the bottom of the parachute are bolted with counterweight beads, and the counterweight beads are made of rubber material.

[0012] In order to achieve the effect of supporting the bottom of the parachute, as a preferred emergency landing protection structure for a rotary-wing UAV of the utility model, support rods are bolted on both sides of the top of the V-shaped closing plate, and the top of the support rods is in contact with the bottom of the parachute.

[0013] In order to achieve the effect of improving the buffering and supporting use of the spring inside the support tube, as a preferred emergency landing protection structure for a rotary-wing UAV of the utility model, a buffer block is provided on the top side of the support tube, and the buffer block is made of elastic cotton material.

[0014] In order to achieve the effect of reducing the buffer rod's use for buffering when rebounding, as a preferred emergency landing protection structure for a rotary-wing UAV of the utility model, a rebound pad is provided on the bottom side of the support tube, and the rebound pad is located on the outside of the buffer rod.

[0015] Compared with the prior art, the beneficial effects of the utility model are:

[0016] The emergency landing protection structure for a rotary-wing UAV is provided with a UAV body, a speed monitor, a storage box, a top plate, a microprocessor, a V-shaped closing plate, a detonator, a sodium azide substance, a speed reduction component, a support tube, a buffer component and a reinforcement component. The storage battery inside the UAV body supplies power to various monitors and electronic components inside, so that the rotor rotates to allow the UAV body to take off. When the UAV body loses power and falls downward, the speed monitor detects it and feeds back to the microprocessor inside the storage box. Then the microprocessor quickly responds and issues an opening command to the detonator located on the top of the bottom plate. Then the detonating end of the detonator ignites the sodium azide substance located on the top of the V-shaped closing plate, and then the sodium azide substance generates nitrogen. , so that the gas it produces quickly impacts upward, and then the parachute located on the top of the sodium azide material impacts the top plate clamped on the top of the storage box upward under the impact of the gas, and causes the top plate to fall off, and then the parachute is immediately deployed in the central part of the drone body, and is pulled by the wire wheel located on the top of the carrier plate in conjunction with the wire rope, thereby quickly reducing the falling speed of the drone body, and then when landing, the buffer component located inside the support tube at the bottom of the drone body contacts the ground and buffers, thereby reducing the impact force generated during the fall, and synchronously through the buffer component and the reinforcement components on both sides of the support tube for auxiliary support and buffering, so as to achieve effective protection of the drone body when the drone body loses power for emergency landing, so as to facilitate the use of the user as a whole. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is an overall structural diagram of the emergency landing protection structure for a rotary-wing UAV of the utility model;

[0018] Figure 2 It is a plan view of the storage box in the utility model;

[0019] Figure 3 It is a plan view of the speed reduction component in the utility model;

[0020] Figure 4 It is a structural schematic diagram of the buffer component in the utility model;

[0021] Figure 5 It is a structural schematic diagram of the reinforcement component in the utility model.

[0022] In the figure, 1. drone body; 2. rotor; 3. storage box; 4. top plate; 5. microprocessor; 6. bottom plate; 7. V-shaped closing plate; 8. detonator; 9. sodium azide substance; 10. deceleration component; 1001. carrier plate; 1002. reel; 1003. wire rope; 1004. parachute; 11. support tube; 12. buffer component; 1201. spring; 1202. buffer rod; 1203. caster; 13. reinforcement component; 1301. top block; 1302. bottom block; 1303. first rotating rod; 1304. second rotating rod; 14. V-shaped reinforcing rod; 15. counterweight beads; 16. support rod; 17. buffer block; 18. return cushion; 19. speed monitor. DETAILED DESCRIPTION

[0023] In order to make the purpose, technical solution and advantages of the utility model more clear, the utility model is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the utility model and are not used to limit the utility model.

[0024] In the description of the present invention, it should be understood that the terms "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, in the description of the present invention, "multiple" means two or more, unless otherwise clearly and specifically defined.

[0025] See also Figure 1-5The utility model provides a technical solution: an emergency landing protection structure for a rotary-wing UAV, comprising a UAV body 1, wherein the UAV body 1 is provided with rotors 2 all around, a speed monitor 19 is embedded in the bottom of the front side of the UAV body 1, a storage box 3 is embedded in the inner side of the top of the UAV body 1, a top plate 4 is clamped on the top of the storage box 3, a microprocessor 5 is bolted on the bottom side of the storage box 3, the microprocessor 5 is electrically connected to the speed monitor 19, a bottom plate 6 is bolted on the bottom side of the storage box 3, and a speed monitor 19 is electrically connected to the microprocessor 5. V-shaped closing plate 7, a detonator 8 is bolted to the top of the bottom plate 6, the detonator 8 is electrically connected to the microprocessor 5, the detonating end of the detonator 8 passes through the bottom of the V-shaped closing plate 7, a sodium azide substance 9 is arranged on the top of the V-shaped closing plate 7, a speed reduction component 10 is arranged on the top side of the storage box 3, the bottom of the speed reduction component 10 is bolted and sealed to the V-shaped closing plate 7, a support tube 11 is bolted to the four corners of the bottom of the drone body 1, a buffer component 12 is arranged inside the support tube 11, and reinforcement components 13 are arranged on both sides of the support tube 11 and the buffer component 12;

[0026] The deceleration component 10 includes a carrier plate 1001, a reel 1002, a steel wire rope 1003 and a parachute 1004. The carrier plate 1001 is bolted to two sides of the storage box 3, the reel 1002 is bolted to the top of the carrier plate 1001, the steel wire rope 1003 is wound on the surface of the reel 1002, and the parachute 1004 is arranged inside the carrier plate 1001. The outer side of the parachute 1004 contacts the inner side of the carrier plate 1001, the outer side of the parachute 1004 is bolted to the inner side of the steel wire rope 1003, and the parachute 1004 is located on the top of the sodium azide substance 9.

[0027] In this embodiment: by arranging the drone body 1, the speed monitor 19, the storage box 3, the top plate 4, the microprocessor 5, the V-shaped closing plate 7, the detonator 8, the sodium azide substance 9, the speed reduction component 10, the support tube 11, the buffer component 12 and the reinforcement component 13, the battery inside the drone body 1 supplies power to various monitors and electronic components inside, so that the rotor 2 rotates to make the drone body 1 take off, and then when the drone body 1 loses power and falls downward, its speed monitor 19 detects and feeds back to the microprocessor 5 inside the storage box 3, and then the microprocessor 5 quickly responds and issues an opening command to the detonator 8 located on the top of the bottom plate 6, and then the detonating end of the detonator 8 ignites the sodium azide substance 9 located on the top of the V-shaped closing plate 7, and then the sodium azide substance 9 generates nitrogen, so that the generated The gas impacts upward rapidly, and then the parachute 1004 located on the top of the sodium azide substance 9 impacts the top plate 4 clamped on the top of the storage box 3 upward under the impact of the gas, and causes the top plate 4 to fall off, and then the parachute 1004 is immediately deployed in the central part of the drone body 1, and is pulled by the wire wheel 1002 located on the top of the carrier 1001 in conjunction with the wire rope 1003, thereby quickly reducing the falling speed of the drone body 1, and then when landing, the buffer component 12 located inside the support tube 11 at the bottom of the drone body 1 contacts the ground and buffers, thereby reducing the impact force generated during the fall, and synchronously through the buffer component 12 and the reinforcement components 13 on both sides of the support tube 11 for auxiliary support and buffering, so as to achieve effective protection of the drone body 1 when the drone body 1 loses power for emergency landing, so as to facilitate the use of the user as a whole.

[0028] As a technical optimization solution of the utility model, the buffer assembly 12 includes a spring 1201, a buffer rod 1202 and a caster 1203. The spring 1201 is arranged inside the support tube 11, the buffer rod 1202 is slidably connected to the bottom side of the support tube 11, the top of the buffer rod 1202 contacts the bottom of the spring 1201, and the caster 1203 is bolted to the bottom of the buffer rod 1202.

[0029] In this embodiment: by providing a spring 1201, a buffer rod 1202 and a caster 1203, when the falling speed of the drone body 1 is reduced and the drone body 1 is landed, the caster 1203 located at the bottom of the buffer rod 1202 in the support tube 11 contacts the ground, and then cooperates with the spring 1201 inside the support tube 11 to buffer the buffer rod 1202, thereby reducing the impact force generated when the drone body 1 falls.

[0030] As a technical optimization solution of the utility model, the reinforcement component 13 includes a top block 1301, a bottom block 1302, a first rotating rod 1303 and a second rotating rod 1304. The top block 1301 is bolted to both sides of the support tube 11, and the bottom block 1302 is respectively bolted to both sides of the caster 1203. The inner side of the first rotating rod 1303 is rotatably connected to the outer side of the top block 1301, and the inner side of the second rotating rod 1304 is rotatably connected to the outer side of the bottom block 1302. The second rotating rod 1304 is rotatably connected to the first rotating rod 1303.

[0031] In this embodiment: by setting a top block 1301, a bottom block 1302, a first rotating rod 1303 and a second rotating rod 1304, the top block 1301 and the bottom block 1302 located on both sides of the caster 1203 and the support tube 11 cooperate with the first rotating rod 1303 and the second rotating rod 1304 rotatably connected on their outer sides to assist the caster 1203 in reinforcement and buffering to avoid damage caused by excessive impact.

[0032] As a technical optimization solution of the present invention, a V-shaped reinforcing rod 14 is bolted to the bottom of the V-shaped closing plate 7 , and reinforcing ribs are arranged inside the V-shaped reinforcing rod 14 .

[0033] In this embodiment, by providing a V-shaped reinforcing rod 14, the effect of supporting and reinforcing the V-shaped closing plate 7 can be improved to increase practicality.

[0034] As a technical optimization solution of the present invention, both sides of the bottom of the parachute 1004 are bolted with weight beads 15, and the weight beads 15 are made of rubber material.

[0035] In this embodiment, by providing the counterweight beads 15, the parachute 1004 can be lifted and balanced on both sides after being ejected, thereby increasing practicality.

[0036] As a technical optimization solution of the present invention, support rods 16 are bolted to both sides of the top of the V-shaped closing plate 7 , and the top of the support rods 16 is in contact with the bottom of the parachute 1004 .

[0037] In this embodiment, by providing a support rod 16, the bottom of the parachute 1004 can be supported to increase practicality.

[0038] As a technical optimization solution of the present invention, a buffer block 17 is provided on the top side of the support tube 11, and the buffer block 17 is made of elastic cotton material.

[0039] In this embodiment, by providing a buffer block 17, the effect of buffering and receiving the spring 1201 inside the support tube 11 can be improved to increase practicality.

[0040] As a technical optimization solution of the present invention, a buffer pad 18 is provided on the bottom side of the support tube 11 , and the buffer pad 18 is located on the outside of the buffer rod 1202 .

[0041] In this embodiment, by providing the rebound cushion 18, the effect of reducing the buffer rod 1202 for buffering during rebound can be achieved, thereby increasing practicality.

[0042] Working principle: First, the battery inside the drone body 1 supplies power to various monitors and electronic components inside, so that the rotor 2 rotates to allow the drone body 1 to take off. Then, when the drone body 1 loses power and falls downward, its speed monitor 19 detects it and feeds back to the microprocessor 5 inside the rear storage box 3. Then the microprocessor 5 quickly responds and issues an opening command to the detonator 8 located on the top of the bottom plate 6. Then the detonating end of the detonator 8 ignites the sodium azide substance 9 located on the top of the V-shaped closing plate 7, and then the sodium azide substance 9 generates nitrogen, so that the generated gas quickly impacts upward, and then the parachute 1004 located on the top of the sodium azide substance 9 impacts the top plate 4 clamped on the top of the storage box 3 upward under the impact of the gas, and causes the top plate 4 to fall off, and then the parachute 1004 falls in the middle. The central part of the drone body 1 is then unfolded and pulled by the wire wheel 1002 located on the top of the carrier 1001 in cooperation with the wire rope 1003, thereby quickly reducing the falling speed of the drone body 1. When landing, the caster 1203 located at the bottom of the buffer rod 1202 in the support tube 11 contacts the ground, and then cooperates with the spring 1201 inside the support tube 11 to buffer the buffer rod 1202, thereby reducing the impact force generated when the drone body 1 falls. At the same time, the top block 1301 and the bottom block 1302 located on both sides of the caster 1203 and the support tube 11 cooperate with the first rotating rod 1303 and the second rotating rod 1304 connected to the outside to assist the caster 1203 in reinforcement and buffering, so as to avoid damage caused by excessive impact, and effectively protect the drone body 1 as a whole, so as to facilitate the use of the user.

[0043] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An emergency landing protection structure for a rotary-wing UAV, comprising a UAV body (1), characterized in that: The drone body (1) is provided with rotors (2) on all sides, a speed monitor (19) is embedded in the bottom of the front side of the drone body (1), a storage box (3) is embedded in the inner side of the top of the drone body (1), a top plate (4) is clamped on the top of the storage box (3), a microprocessor (5) is bolted to the bottom side of the storage box (3), the microprocessor (5) is electrically connected to the speed monitor (19), a bottom plate (6) is bolted to the bottom side of the storage box (3), a V-shaped closing plate (7) is provided on the top of the storage box (3), and a detonator (19) is bolted to the top of the bottom plate (6). 8), the detonator (8) is electrically connected to the microprocessor (5), the detonating end of the detonator (8) passes through the bottom of the V-shaped closing plate (7), the top of the V-shaped closing plate (7) is provided with a sodium azide substance (9), a speed reduction component (10) is provided on the top side of the storage box (3), the bottom of the speed reduction component (10) is bolted to and sealed with the V-shaped closing plate (7), the four corners of the bottom of the drone body (1) are bolted with support tubes (11), a buffer component (12) is provided inside the support tube (11), and reinforcement components (13) are provided on both sides of the support tube (11) and the buffer component (12); The deceleration component (10) comprises a carrier plate (1001), a wire wheel (1002), a steel wire rope (1003) and a parachute (1004); the carrier plate (1001) is bolted to two sides of the interior of the storage box (3), respectively; the wire wheel (1002) is bolted to the top of the carrier plate (1001); the steel wire rope (1003) is wound around the surface of the wire wheel (1002); the parachute (1004) is arranged inside the carrier plate (1001); the outer side of the parachute (1004) contacts the inner side of the carrier plate (1001); the outer side of the parachute (1004) is bolted to the inner side of the steel wire rope (1003); and the parachute (1004) is located on top of the sodium azide substance (9).

2. The emergency landing protection structure for a rotary wing UAV according to claim 1, characterized in that: The buffer assembly (12) comprises a spring (1201), a buffer rod (1202) and a caster (1203); the spring (1201) is arranged inside the support tube (11); the buffer rod (1202) is slidably connected to the bottom side of the support tube (11); the top of the buffer rod (1202) contacts the bottom of the spring (1201); and the caster (1203) is bolted to the bottom of the buffer rod (1202).

3. The emergency landing protection structure for a rotary wing UAV according to claim 2, characterized in that: The reinforcement assembly (13) comprises a top block (1301), a bottom block (1302), a first rotating rod (1303) and a second rotating rod (1304); the top block (1301) is bolted to both sides of the support tube (11); the bottom block (1302) is respectively bolted to both sides of the caster (1203); the inner side of the first rotating rod (1303) is rotatably connected to the outer side of the top block (1301); the inner side of the second rotating rod (1304) is rotatably connected to the outer side of the bottom block (1302); and the second rotating rod (1304) is rotatably connected to the first rotating rod (1303).

4. The emergency landing protection structure for a rotary wing UAV according to claim 1, characterized in that: A V-shaped reinforcing rod (14) is bolted to the bottom of the V-shaped closing plate (7), and reinforcing ribs are arranged inside the V-shaped reinforcing rod (14).

5. The emergency landing protection structure for a rotary wing UAV according to claim 1, characterized in that: Both sides of the bottom of the parachute (1004) are bolted with weight beads (15), and the weight beads (15) are made of rubber material.

6. The emergency landing protection structure for a rotary wing UAV according to claim 1, characterized in that: Support rods (16) are bolted to both sides of the top of the V-shaped closing plate (7), and the top of the support rod (16) is in contact with the bottom of the parachute (1004).

7. The emergency landing protection structure for a rotary wing UAV according to claim 1, characterized in that: A buffer block (17) is provided on the top side of the support tube (11), and the buffer block (17) is made of elastic cotton material.

8. The emergency landing protection structure for a rotary wing UAV according to claim 1, characterized in that: A buffer pad (18) is provided on the bottom side of the support tube (11), and the buffer pad (18) is located on the outside of the buffer rod (1202).

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