Unmanned aerial vehicle with self-rescue function

Abstract

The unmanned aerial vehicle with the self-rescue function comprises a fuselage main body and wing main wings, a power cabin is arranged in the fuselage main body, a driving assembly is arranged in the power cabin, one end of the driving assembly is in driving connection with a driving wing, a self-rescue cabin is arranged on the surface of the fuselage main body, and a launching assembly is arranged in the self-rescue cabin. A parachute is arranged in the launching assembly, the power cabin communicates with the self-rescue cabin, a first supporting plate is arranged on the side, close to the power cabin, of the self-rescue cabin, and a starter for controlling the launching assembly to be turned on and off is arranged on the first supporting plate; when the unmanned aerial vehicle is out of control due to emergencies or improper manipulation, the starter can judge that the whole unmanned aerial vehicle is in an out-of-control state, and then the starter can drive the launching assembly to eject the parachute out and unfold the parachute, so that the whole self-rescue process is completed, and damage to the unmanned aerial vehicle is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a unmanned aerial vehicle with a self-rescue function. Background Art

[0002] UAVs are unmanned aircraft that are controlled by radio remote control equipment and control programs. Since they do not require human pilots, the flight conditions are relaxed, and aerodynamic efficiency and control efficiency can be maximized, they have been widely used.

[0003] If an emergency or improper operation occurs, the drone may crash or explode easily. After an accident, the data inside the drone may be easily lost or damaged. Furthermore, since the aircraft itself and the onboard equipment are expensive, damage will bring certain economic pressure to enterprises or individuals, and it will also pose a certain threat to ground personnel when a faulty landing occurs. Summary of the invention

[0004] The present invention mainly aims at the problems existing in the use of the above-mentioned drone, and invents a drone with a self-rescue function. When the drone encounters an emergency or is improperly operated and loses control, the parameter change of the gyroscope of the controller is too abnormal, which can quickly determine that the entire drone is in an out-of-control state. The controller can drive the launch spindle to slide to the left and release it. When sliding to the left, the clamping claw will gradually slide out of the launch limit groove. After the launch spindle is released, the second spring generates elastic force to push the limit column to the right, so that the entire launch spindle will eject the parachute to the right and unfold it, thereby completing the entire self-rescue process; after the drone loses control, the power battery will cut off the power to the first electromagnet, and the entire wing aileron will be affected by the elastic force of the first spring, so that the wing aileron will rotate around the aileron shaft. After unfolding, the wing aileron can play a role of deceleration, so that a lot of time is saved for the subsequent launch assembly to eject the parachute.

[0005] The inventive objective of the present invention is achieved through the following technical solutions: a drone with a self-rescue function, comprising a fuselage main body, and main wings arranged on both sides of the fuselage main body, a power compartment is arranged inside the fuselage main body, a driving assembly is arranged inside the power compartment, one end of the driving assembly is drivingly connected to a driving wing, a self-rescue compartment is arranged on the surface of the fuselage main body, a launching assembly is arranged inside the self-rescue compartment, a parachute is arranged inside the launching assembly, the power compartment and the self-rescue compartment are connected, a first support plate is arranged on the side of the self-rescue compartment close to the power compartment, and a starter for controlling the launch assembly switch is arranged on the first support plate.

[0006] Preferably, a first notch is provided on one side of each wing, an aileron shaft is provided inside the first notch, and a wing aileron is rotatably connected to the aileron shaft.

[0007] Preferably, a power compartment is further provided inside the power compartment, and a plurality of power batteries are installed inside the power compartment.

[0008] Preferably, a plurality of support columns and fixed blocks are provided on the surface of the wing aileron, the aileron shaft is rotatably connected inside the fixed block, a first spring is provided on the surface of each support column, a metal block is provided on the surface of the wing aileron, a first electromagnet is provided on the side of the wing main wing close to the metal block, the first electromagnet is connected to a power battery inside the fuselage body, and the first spring and the wing aileron are in a state of mutual extrusion.

[0009] The driving assembly includes a motor fixing plate, a driving motor, a rotating shaft transmission plate, a rotating shaft locking ring and an angle adjustment piece. A motor fixing plate is provided inside the power compartment, and a driving motor is provided inside the motor fixing plate. The end of the rotating shaft of the driving motor is connected to one end of the rotating shaft transmission plate. The rotating shaft transmission plate and the rotating shaft of the driving motor are fixed by a rotating shaft locking ring. The other end of the rotating shaft transmission plate is connected to the angle adjustment piece, and the end of the angle adjustment piece is connected to the driving wing.

[0010] The angle adjustment member includes a first U-shaped member, a second U-shaped member and a cross shaft. The other end of the rotating shaft transmission plate is connected to the first U-shaped member. The end of the first U-shaped member is connected to the cross shaft. The cross shaft is also connected to the second U-shaped member. The end of the second U-shaped member is connected to the driving wing.

[0011] The launching assembly comprises a launching channel, a launching spindle, a launching support block, a claw, an elastic buckle and a parachute. The launching channel is slidably connected to the inside of the launching spindle. A limiting column is provided at one end of the launching spindle. A launching limiting groove is provided on the surface of the limiting column. A launching support block is provided on one side of the limiting column. A first channel and a second channel are provided inside the launching support block. The first channel is rotatably connected to the inside of the claw. A second spring is provided inside the second channel. The claw is clamped in the launching limiting groove on the surface of the limiting column. A limiting shaft is provided on the surface of the launching support block on the side away from the limiting column. An elastic buckle is provided on the surface of the limiting shaft. One end of the elastic buckle limits the claw from shaking up and down. A parachute is provided on the other side of the launching spindle.

[0012] Preferably, the starter comprises a second electromagnet and a backup battery, the second electromagnet is provided with a controller, a gyroscope is provided in the controller, and the backup battery circuit is connected to the second electromagnet and the controller.

[0013] Preferably, a plurality of support rods are provided on the bottom surface of the fuselage body, and the end of each support rod is rotatably connected to a roller, and a windshield is rotatably provided at the exit of the self-rescue cabin.

[0014] Preferably, a camera mounting slot is further provided on the bottom surface of the fuselage main body, and a high-definition camera is rotatably mounted inside the camera mounting slot.

[0015] Compared with the prior art, the present invention has the following beneficial effects: 1. When the UAV encounters an emergency or is out of control due to improper operation, the abnormal change in the parameters of the controller's gyroscope can quickly determine that the entire UAV is out of control, and the controller can drive the launch spindle to slide to the left and release it. When sliding to the left, the claw will gradually slide out of the launch limit slot. After the launch spindle is released, the second spring generates elastic force to push the limit column to the right, so that the entire launch spindle will eject the parachute to the right and unfold it, thereby completing the entire self-rescue process, thereby reducing damage to the UAV and reducing 1. It reduces the economic pressure on enterprises or individuals, and greatly reduces the threat to ground personnel after a faulty landing; 2. After the UAV loses control, the power battery will cut off the power to the first electromagnet, and the entire wing aileron will be affected by the elastic force of the first spring. Therefore, the wing aileron will rotate around the aileron axis. After unfolding, the wing aileron can slow down the vehicle, thereby buying a lot of time for the subsequent launch assembly to eject the parachute, further ensuring the smooth implementation of the entire self-rescue process, and if the parachute cannot be ejected, the deceleration effect of the wing aileron also reduces the damage after the UAV is forced to land. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 A perspective view of the present invention;

[0017] Figure 2 It is a three-dimensional diagram of the fuselage body of the present invention after sectioning;

[0018] Figure 3 It is a partial stereogram of the present invention;

[0019] Figure 4 It is a partial enlarged view of the present invention;

[0020] Figure 5 It is a partial enlarged view of the present invention;

[0021] Figure 6 A three-dimensional diagram of the launch assembly area of ​​the present invention;

[0022] Figure 7 It is a three-dimensional diagram of the launch channel of the present invention after sectioning;

[0023] Figure 8 is a cross-sectional view of the transmitting assembly area of ​​the present invention;

[0024] Fig. 9 It is a schematic diagram of the self-rescue state of the present invention.

[0025] Markings in the figure: 1. fuselage body; 11. power compartment; 12. self-rescue compartment; 121. windshield; 13. first support plate; 14. power compartment; 15. power battery; 16. support rod; 17. roller; 18. camera installation slot; 19. high-definition camera; 2. main wing; 21. first missing slot; 22. aileron shaft; 23. first electromagnet; 3. drive assembly; 31. motor fixing plate; 32. drive motor; 33. shaft transmission plate; 34. shaft locking ring; 35. angle adjustment member; 351. first U-shaped member; 3 52. Second U-shaped member; 353. Cross axis; 4. Drive wing; 5. Launch assembly; 51. Launch channel; 52. Launch main axis; 53. Launch support block; 54. Claw; 55. Elastic buckle; 56. Parachute; 521. Limit column; 522. Launch limit groove; 531. First channel; 532. Second channel; 533. Limit axis; 6. Starter; 61. Second electromagnet; 62. Backup battery; 63. Controller; 7. Wing aileron; 71. Support column; 72. Fixing block; 73. First spring; 74. Metal block. DETAILED DESCRIPTION

[0026] The present invention will be further described below with reference to the embodiments shown in the accompanying drawings:

[0027] like Figures 1 to 9As shown, a drone with a self-rescue function comprises a fuselage body 1, wing main wings 2 arranged on both sides of the fuselage body 1, a power compartment 11 is arranged inside the fuselage body 1, a driving assembly 3 is arranged inside the power compartment 11, a power compartment 14 is also arranged inside the power compartment 11, a plurality of power batteries 15 are installed inside the power compartment 14, and the power batteries 15 generate electricity for the entire driving assembly 3. Specifically, one end of the driving assembly 3 is connected to the driving wing 4. Specifically, the driving assembly 3 is connected to the driving wing 4. The dynamic component 3 includes a motor fixing plate 31, a driving motor 32, a rotating shaft transmission plate 33, a rotating shaft locking ring 34 and an angle adjustment member 35. The motor fixing plate 31 is fixedly arranged inside the power compartment 11, and the driving motor 32 is fixedly installed inside the motor fixing plate 31. The end of the rotating shaft of the driving motor 32 is connected to the left end of the rotating shaft transmission plate 33. The rotating shaft transmission plate 33 and the rotating shaft of the driving motor 32 are fixed by the rotating shaft locking ring 34. The left end of the rotating shaft transmission plate 33 is connected to the angle adjustment member 35. Specifically, the angle adjustment member 35 includes a first U-shaped member 351, a second U-shaped member 352 and a cross shaft 353. The left end of the rotating shaft transmission plate 33 is connected to the first U-shaped member 351, the left end of the first U-shaped member 351 is connected to the cross shaft 353, the cross shaft 353 is also connected to the second U-shaped member 352, and the end of the second U-shaped member 352 is connected to the driving wing 4. After such a configuration, the rotating shaft of the driving motor 32 can drive the rotating shaft transmission plate 33, and the rotating shaft transmission plate 33 can drive the first U-shaped When the first U-shaped member 351 rotates, the second U-shaped member 352 can be driven to rotate through the cross shaft 353. When the second U-shaped member 352 rotates, the driving wing 4 will rotate to generate thrust. Driven by the driving wing 4, the entire UAV can glide. It should be noted that the driving wing 4 of the UAV may be hit by strong winds or other birds during the gliding process. At this time, the second U-shaped member 352 connected to the driving wing 4 will fine-tune the angle on the cross shaft 353 to avoid excessive hard damage to the driving wing 4.

[0028] In this embodiment, a self-rescue chamber 12 is provided on the surface of the fuselage body 1, and a launching assembly 5 is fixedly installed inside the self-rescue chamber 12, and a parachute 56 is arranged inside the launching assembly 5. Specifically, the launching assembly 5 includes a launching channel 51, a launching main shaft 52, a launching support block 53, a claw 54, an elastic buckle 55 and a parachute 56. The launching main shaft 52 is slidably connected inside the launching channel 51, and metal plates are installed at both ends of the launching main shaft 52. A limiting column 521 is provided to the left on the metal plate at the right end of the launching main shaft 52, and a launching limiting groove 522 is provided on the surface of the limiting column 521. A launching support block 53 is fixedly installed on the left side of the limiting column 521 and inside the launching channel 51. A first channel 531 and a second channel 532 are arranged inside the launching support block 53, and a claw 54 is rotatably connected inside the first channel 531, and a second spring 57 is arranged inside the second channel 532. The claw 54 is clamped on the surface of the limiting column 521. A limiting shaft 533 is provided on the left side surface of the launch support block 53 away from the limiting column 521, and an elastic buckle 55 is provided on the surface of the limiting shaft 533. The elastic buckle 55 has a certain elasticity and its top can limit the up and down shaking of the claw 54. A parachute 56 is provided on the other side of the launch main shaft 52, and a windshield 121 can be rotatably provided at the exit of the self-rescue cabin 12. After such arrangement, whenever the parachute needs to be launched, the launch main shaft 52 slides to the left. The clamping claw 54 will gradually slide out of the launch limit groove 522. At this time, the launch shaft 52 is released, and the second spring 57 inside the second channel 532 will generate elastic force to push the limit column 521 to the right. In this way, the entire launch shaft 52 will slide to the right until the entire parachute 56 located inside the launch channel 51 is ejected and unfolded. It should be noted that before the clamping claw 54 is separated from the launch limit groove 522, it is squeezed downward by the elastic buckle 55 so that it is firmly stuck in the launch limit groove 522.

[0029] In this embodiment, the power compartment 11 and the self-rescue compartment 12 are connected, and a first support plate 13 is fixedly installed on one side of the self-rescue compartment 12 close to the power compartment 11. A starter 6 for controlling the switch of the launch assembly 5 is provided on the first support plate 13. Specifically, the starter 6 includes a second electromagnet 61 and a backup battery 62. The second electromagnet 61 is provided with a controller 63, and a gyroscope is provided in the controller 63. The backup battery 62 circuit is connected to the second electromagnet 61 and the controller 63. The controller 63 determines that the entire drone is out of control by judging that the parameters of the gyroscope change abnormally. Then the controller 63 energizes the second electromagnet 61. After the second electromagnet 61 is energized, it will attract the launch spindle 52 and move it to the left. After the attraction lasts for a few seconds, the second electromagnet 61 will fail, and the launch spindle 52 can proceed to the next step normally.

[0030] In this embodiment, a plurality of support rods 16 are provided on the bottom surface of the fuselage body 1, and the end of each support rod 16 can be rotatably connected to a roller 17. A camera mounting groove 18 is also provided on the bottom surface of the fuselage body 1, and a high-definition camera 19 is rotatably installed inside the camera mounting groove 18. A first notch 21 is provided on one side of each wing, and an aileron shaft 22 is fixedly installed inside the first notch 21. The aileron shaft 22 can be rotatably connected to a wing aileron 7. A plurality of support columns 71 and fixed blocks 72 are provided on the surface of the wing aileron 7, and the aileron shaft 22 can be rotatably connected inside the fixed block 72. A first spring 73 is provided on the surface of each support column 71, and a metal block 74 is provided on the surface of the wing aileron 7. A first electromagnet is provided on the side of the wing main wing 2 close to the metal block 74. 23, the first electromagnet 23 is connected to the power battery 15 inside the fuselage body 1, and when the first electromagnet 23 is energized, the first spring 73 and the wing aileron 7 are in a mutually squeezed state. After being set in this way, the first electromagnet 23 is in a energized state in daily flight, and the first electromagnet 23 will firmly absorb the metal block 74 on the surface of the wing aileron 7, so that the entire wing aileron 7 will move closer to the inside of the first notch 21 on the wing main wing 2. After moving closer, the wing aileron 7 will not affect the gliding of the entire UAV. If the UAV loses control, the power battery 15 will cut off the power supply to the first electromagnet 23, and the entire wing aileron 7 will be subject to the elastic force of the first spring 73, so that the entire wing aileron 7 will rotate around the aileron shaft 22. After unfolding, the wing aileron 7 plays a role of deceleration, which buys time for the subsequent launch assembly 5 to eject the parachute 56.

[0031] Working principle and use method of the present invention:

[0032] During takeoff, the shaft of the driving motor 32 can drive the shaft transmission plate 33. When the shaft transmission plate 33 rotates, it can drive the first U-shaped member 351 to rotate. When the first U-shaped member 351 rotates, it can drive the second U-shaped member 352 to rotate through the cross shaft 353. When the second U-shaped member 352 rotates, the driving wing 4 will rotate to generate thrust. Driven by the driving wing 4, the entire UAV can glide. During the gliding process, if the driving wing 4 is hit by strong winds or other birds, the second U-shaped member 352 connected to the driving wing 4 will fine-tune the angle on the cross shaft 353 to avoid excessive hard damage to the driving wing 4. If the UAV encounters an emergency or is improperly operated and loses control, the controller 63 determines that the entire UAV is out of control through the abnormal changes in the gyroscope parameters, and the power battery 15 will The power supply to the first electromagnet 23 will be cut off, and the entire wing aileron 7 will be subjected to the elastic force of the first spring 73, so that the entire wing aileron 7 will rotate and unfold around the aileron shaft 22. After unfolding, the wing aileron 7 will play a role of deceleration, and then the controller 63 will energize the second electromagnet 61. After being energized, the second electromagnet 61 will attract the launch shaft 52 and move it to the left. After the attraction continues for a few seconds, the second electromagnet 61 will fail. When the launch shaft 52 slides to the left, the claw 54 will gradually slide out of the launch limit groove 522. After releasing the launch shaft 52, the second spring 57 inside the second channel 532 will generate elastic force to push the limit column 521 to the right, so that the entire launch shaft 52 will slide to the right until the entire parachute 56 located inside the launch channel 51 is ejected and unfolded, thereby completing the entire self-rescue process.

[0033] The specific embodiments described herein are merely examples of the spirit of the present invention. Those skilled in the art may make various modifications or additions to the specific embodiments described or replace them in similar ways, but they will not deviate from the spirit of the present invention or exceed the scope defined by the appended claims.

Claims

1. A drone with a self-rescue function, comprising a fuselage body (1), and wings (2) arranged on both sides of the fuselage body (1), characterized in that: A power compartment (11) is provided inside the fuselage body (1), a driving assembly (3) is provided inside the power compartment (11), one end of the driving assembly (3) is drivingly connected to a driving wing (4), a self-rescue compartment (12) is provided on the surface of the fuselage body (1), a launching assembly (5) is provided inside the self-rescue compartment (12), a parachute (56) is provided inside the launching assembly (5), the power compartment (11) and the self-rescue compartment (12) are connected, a first support plate (13) is provided on a side of the self-rescue compartment (12) close to the power compartment (11), and a starter (6) for controlling the switch of the launching assembly (5) is provided on the first support plate (13).

2. The drone with self-rescue function according to claim 1, characterized in that: A first notch (21) is provided on one side of each wing, an aileron shaft (22) is provided inside the first notch (21), and a wing aileron (7) is rotatably connected to the aileron shaft (22).

3. The drone with self-rescue function according to claim 2, characterized in that: A power supply compartment (14) is also provided inside the power compartment (11), and a plurality of power batteries (15) are installed inside the power supply compartment (14).

4. The drone with self-rescue function according to claim 3, characterized in that: The surface of the wing aileron (7) is provided with a plurality of support columns (71) and a fixed block (72); the aileron shaft (22) is rotatably connected inside the fixed block (72); the surface of each support column (71) is provided with a first spring (73); the surface of the wing aileron (7) is provided with a metal block (74); a first electromagnet (23) is provided on a side of the wing main wing (2) close to the metal block (74); the first electromagnet (23) is connected to a power battery (15) inside the fuselage body (1); and the first spring (73) and the wing aileron (7) are in a mutually squeezed state.

5. The drone with self-rescue function according to claim 4, characterized in that: The driving assembly (3) comprises a motor fixing plate (31), a driving motor (32), a rotating shaft transmission plate (33), a rotating shaft locking ring (34) and an angle adjustment member (35). The motor fixing plate (31) is arranged inside the power compartment (11), the driving motor (32) is arranged inside the motor fixing plate (31), the rotating shaft end of the driving motor (32) is connected to one end of the rotating shaft transmission plate (33), the rotating shaft transmission plate (33) and the rotating shaft of the driving motor (32) are fixed by a rotating shaft locking ring (34), the other end of the rotating shaft transmission plate (33) is connected to the angle adjustment member (35), and the end of the angle adjustment member (35) is connected to the driving wing (4).

6. The drone with self-rescue function according to claim 5, characterized in that: The angle adjustment member (35) comprises a first U-shaped member (351), a second U-shaped member (352) and a cross shaft (353); the other end of the rotating shaft transmission plate (33) is connected to the first U-shaped member (351); the end of the first U-shaped member (351) is connected to the cross shaft (353); the cross shaft (353) is also connected to the second U-shaped member (352); the end of the second U-shaped member (352) is connected to the driving wing (4).

7. The drone with self-rescue function according to claim 1, characterized in that: The launching assembly (5) comprises a launching channel (51), a launching spindle (52), a launching support block (53), a claw (54), an elastic buckle (55) and a parachute (56); the launching spindle (52) is slidably connected inside the launching channel (51); a limiting column (521) is provided at one end of the launching spindle (52); a launching limiting groove (522) is provided on the surface of the limiting column (521); a launching support block (53) is provided on one side of the limiting column (521); a first channel (531) and a second channel (532) are provided inside the launching support block (53); 2), a claw (54) is rotatably connected inside the first channel (531), a second spring (57) is provided inside the second channel (532), the claw (54) is clamped in the launch limit groove (522) on the surface of the limit column (521), a limit shaft (533) is provided on the surface of the launch support block (53) away from the limit column (521), an elastic buckle (55) is provided on the surface of the limit shaft (533), one end of the elastic buckle (55) limits the claw (54) from shaking up and down, and a parachute (56) is provided on the other side of the launch main shaft (52).

8. The drone with self-rescue function according to claim 7, characterized in that: The starter (6) comprises a second electromagnet (61) and a backup battery (62); the second electromagnet (61) is provided with a controller (63); a gyroscope is provided in the controller (63); and the backup battery (62) is connected to the second electromagnet (61) and the controller (63) in a circuit.

9. The drone with self-rescue function according to claim 8, characterized in that: The bottom surface of the fuselage body (1) is provided with a plurality of support rods (16), the end of each support rod (16) is rotatably connected to a roller (17), and a windshield (121) is rotatably provided at the exit of the self-rescue chamber (12).

10. The drone with self-rescue function according to any one of claims 1 to 9, characterized in that: The bottom surface of the fuselage main body (1) is also provided with a camera installation slot (18), and a high-definition camera (19) is rotatably installed inside the camera installation slot (18).

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