Safety anti-falling device for aerial performance unmanned aerial vehicle

Abstract

This invention belongs to the field of unmanned aerial vehicle (UAV) technology, specifically a safety crash prevention device for a flight performance UAV, including a UAV body; a parachute compartment is provided on the top of the UAV body, a first inner liner plate is connected to the inner bottom of the parachute compartment, a second inner liner plate is provided on the top of the first inner liner plate, multiple sleeves are snapped between the opposing surfaces of the second inner liner plate and the first inner liner plate, and each sleeve corresponding to the opposing surfaces of the second inner liner plate and the first inner liner plate has an arc-shaped groove, and the same arc-shaped shaft is slidably connected in every two mating arc-shaped grooves; in this invention, through the non-contact mutual repulsion triggering of the electromagnet and the permanent magnet block, combined with the stored force release of the second spring, the limit can be quickly released and the parachute ejected at the moment of failure, significantly shortening the response time of the crash prevention system; the third spring and the fifth spring work together to absorb lateral and vertical impact energy respectively, forming a multi-level buffering effect.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) technology, specifically a safety anti-crash device for flight performance UAVs. Background Technology

[0002] Unmanned aerial vehicles, or "drones" for short, are generally more suitable for performing tasks that are too "tedious, dirty, or dangerous" compared to manned aircraft. According to the application field, drones can be divided into two categories: military and civilian. The deep integration of drones with industry applications is where their real demand lies, especially a drone with a flight attitude that can help people complete tasks more efficiently or provide a better quality of life experience.

[0003] Existing technologies disclose several invention patents in the field of unmanned aerial vehicle (UAV) technology. Among them, invention patent CN221718796U discloses a crash protection device for a flight performance UAV, including a UAV body and a controller located inside the UAV body. The top of the UAV body has a vertically extending storage tube, the top of which is connected to a cap. The bottom of the storage tube is connected to an air storage cylinder via a solenoid valve, which is electrically connected to the controller. Inside the storage tube, from top to bottom, are arranged a parachute and a traction seat. The parachute is connected to the traction seat via a rope. The traction seat is slidably connected to the storage tube. The drone body is equipped with a locking mechanism and a triggering mechanism, which can separate from the parachute after the parachute is completed. The safety crash protection devices equipped on existing flight performance drones still have certain deficiencies in actual application. After the drone lands, under the action of natural wind, the parachute that has not yet detached can easily continue to drag the drone body, thereby causing secondary safety accidents. Even if the parachute and the drone are separated, the drone may continue to glide on the ground due to its own inertia, which may cause it to overturn or tilt forward, resulting in damage to the body structure.

[0004] Based on this, the present invention designs a safety anti-crash device for flight performance drones to solve the above problems. Summary of the Invention

[0005] To overcome the shortcomings of existing technologies, this invention proposes a safety crash prevention device for aerobatic display drones. This invention primarily addresses the deficiencies in existing safety crash prevention devices for aerobatic display drones during practical application. After landing, the parachute, still attached, can easily continue to drag the drone under the influence of wind, potentially causing secondary accidents. Even if the parachute separates from the drone, the drone may continue to glide on the ground due to its inertia, leading to rollover or forward tilting and structural damage.

[0006] The technical solution adopted by the present invention to solve its technical problem is: a safety anti-crash device for a flight performance drone, including a drone body; a parachute compartment is opened on the top of the drone body, a first inner liner plate is connected to the inner bottom of the parachute compartment, a second inner liner plate is provided on the top of the first inner liner plate, a plurality of sleeves are snapped between the opposite surfaces of the second inner liner plate and the first inner liner plate, and each sleeve is provided with an arc-shaped groove corresponding to the opposite surfaces of the second inner liner plate and the first inner liner plate, and the same arc-shaped shaft is slidably connected in every two mating arc-shaped grooves; One end of the arc-shaped shaft is connected to a first spring, and the arc-shaped shaft forms an elastic support between the first spring and the inner end faces of the two arc-shaped grooves it is located in. The other end of the arc-shaped shaft is connected to a permanent magnet. The opposing surfaces of the first inner liner plate and the second inner liner plate are respectively provided with magnetic grooves that communicate with the two arc-shaped grooves. The same electromagnet is installed in every two mating magnetic grooves.

[0007] Preferably, each sleeve has a first arc-shaped hole on its outer wall corresponding to the arc-shaped groove, and each sleeve has a sleeve shaft fitted inside. The sleeve shaft has a second arc-shaped hole corresponding to the first arc-shaped hole, and a second spring is also fitted on the sleeve shaft. The top ends of multiple sleeve shafts are connected to a catapult disc. The catapult disc and the opposite surface of the second inner liner plate are elastically supported by multiple second springs. A parachute is provided above the UAV body, and parachute lines are provided between the parachute and the catapult disc.

[0008] Preferably, two first adapter frames are connected to the front and rear sides of the bottom of the drone body. An adapter shaft is rotatably connected to the inner side of each first adapter frame. A third spring is sleeved on the end of the adapter shaft. The adapter shaft is elastically connected to the outer wall of the first adapter frame through the third spring. An adapter joint is rotatably connected to the adapter shaft at the inner side of the first adapter frame. The other ends of the two adapter joints located on the same side of the drone body are provided with a support leg.

[0009] Preferably, the top of the support leg has two buffer grooves, the positions of the two buffer grooves correspond to the two adapters respectively, and a buffer shaft is slidably connected inside each buffer groove. The two buffer shafts are connected by a cross brace, and a fifth spring is connected to the bottom of the buffer shaft. The buffer shaft forms an elastic support with the inner bottom of the buffer groove through the fifth spring. The other end of the buffer shaft is connected to the bottom of the corresponding adapter.

[0010] Preferably, the top of the ejection disc has two symmetrically arranged transmission ports, and the inner wall of each transmission port is provided with a sliding groove. The transmission port on the same side and the sliding groove are slidably connected to a slider. The top of the slider is connected to a bend shaft, and the other end of the bend shaft is connected to a buckle. The two buckles are connected to each other. The end of the paracord passes through the two buckles and is connected to a rope buckle. The top of the rope buckle abuts against the bottom of the two buckles.

[0011] Preferably, each slider is connected to a first wedge plate at its bottom, and a second wedge plate is slidably connected to the inclined surfaces at the bottom of the two first wedge plates. A transmission hole is provided in the inner bottom of the parachute compartment, and a top rod is slidably connected in the transmission hole. The top end of the top rod is connected to the bottom of the second wedge plate, and the bottom end of the top rod is connected to a connecting seat. Two second adapter frames are connected to each of the two cross braces on the connecting seat. A first push-pull rod is rotatably connected to the inner side of each second adapter frame. A third adapter frame is rotatably connected to the other end of the first push-pull rod. An adapter sleeve is connected to the other end of the third adapter frame, and the adapter sleeve is rotatably connected to the cross brace.

[0012] Preferably, a pressure accumulator is connected to the top of the second inner liner, a piston disc is slidably connected inside the pressure accumulator, and multiple piston shafts are slidably passed through the top of the pressure accumulator. The top ends of the multiple piston shafts are connected to the bottom of the ejection disc, and the bottom ends of the multiple piston shafts are connected to the top of the piston disc. The outer wall of the accumulator is threaded with a first sealing plug and a second sealing plug on the upper and lower sides corresponding to the piston disc, respectively. A one-way valve is installed on the outer wall of the accumulator corresponding to the first sealing plug, and a solenoid valve is provided on the outer wall of the accumulator corresponding to the second sealing plug.

[0013] Preferably, the bottom of the drone body is connected to two symmetrically distributed fixed seats, and the opposite surfaces of the two fixed seats are rotatably connected to the same flip shaft. A gear is fixedly sleeved on the flip shaft, and a toothed plate meshes on the tooth surface of the gear. The top of the toothed plate is slidably connected to the bottom of the drone body, and the end of the toothed plate is connected to a fourth adapter frame. The inner side of the fourth adapter frame is rotatably connected to a second push-pull rod, and the other end of the second push-pull rod is rotatably connected to a fifth adapter frame. The fifth adapter frame is connected to the connecting seat. A storage box is also fixedly sleeved on the flip shaft. A slide plate is slidably connected inside the storage box. Multiple sixth springs are connected to one side of the slide plate. The slide plate forms an elastic support with the inner wall of the storage box through the multiple sixth springs. Multiple anchors are connected to the other side of the slide plate. A directional plate is slidably connected to the multiple anchors. The directional plate is snapped into the inner wall of the storage box.

[0014] The beneficial effects of this invention are as follows: 1. In this invention, the non-contact mutual repulsion triggering of the electromagnet and the permanent magnet block, combined with the energy release of the second spring, can quickly release the limit and eject the parachute at the moment of failure, significantly shortening the response time of the crash protection system. The third and fifth springs work together to absorb the lateral and vertical impact energy respectively, forming a multi-level buffer effect, effectively reducing the peak load transmitted to the UAV body and protecting the internal precision equipment.

[0015] 2. In this invention, the support leg automatically extends outward under its own weight, increasing the grounding span. The progressive sinking stroke of the buffer shaft and the fifth spring makes the grounding process stable and controllable, effectively preventing the drone from tipping over.

[0016] 3. In this invention, the mechanical linkage generated by the landing tilt of the support leg is used to simultaneously achieve automatic parachute separation and automatic anchor penetration into the ground, without the need for additional sensors or power sources, thus avoiding secondary damage and the risk of rollover caused by wind drag after landing.

[0017] 4. In this invention, the high-pressure gas accumulated in the accumulator tank during the landing buffer process is used to drive the anchoring system, thereby realizing the recovery and reuse of impact energy and improving the energy utilization efficiency of the system. Attached Figure Description

[0018] The invention will now be further described with reference to the accompanying drawings.

[0019] Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 This is a three-dimensional structural diagram of the present invention viewed from below; Figure 3 This is a schematic diagram of the structure of the invention after disassembly; Figure 4 This is a cross-sectional view of the present invention. Figure 5 This is the present invention. Figure 3 Schematic diagram of the middle support leg; Figure 6 In this invention Figure 5 A schematic diagram of the disassembled structure; Figure 7 This is the present invention. Figure 6 A schematic diagram of the three-dimensional structure viewed from below; Figure 8 This is a structural diagram of the storage box and anchor nails separated in this invention; Figure 9 This is the present invention. Figure 6 Enlarged structural diagram at point A; Figure 10 This is the present invention. Figure 2Enlarged structural diagram at point B; Figure 11 This is the present invention. Figure 6 A schematic diagram of the ejection disc structure; Figure 12 This is the present invention. Figure 4 Enlarged structural diagram at point C.

[0020] In the diagram: 1. UAV body; 2. Parachute compartment; 3. First inner liner plate; 4. Second inner liner plate; 5. Arc-shaped groove; 6. Arc-shaped shaft; 7. First spring; 8. Permanent magnet; 9. Magnetic groove; 10. Electromagnet; 11. Sleeve; 12. First arc-shaped hole; 13. Combined hole; 14. Anchor pin; 15. Sleeve shaft; 16. Second arc-shaped hole; 17. Second spring; 18. Ejection disc; 19. Parachute lines; 20. Parachute; 21. First adapter frame; 22. Adapter shaft; 23. Adapter connector; 24. Third spring; 25. Support leg; 26. Slide groove; 27. Slider; 28. Fourth spring; 29. ​​Angle shaft; 30. Buckle; 31. Rope buckle; 32. First wedge plate; 33. 34. Second wedge plate; 35. Top rod; 36. Connecting seat; 37. Second adapter frame; 38. First push-pull rod; 39. Third adapter frame; 40. Adapter sleeve; 41. Buffer groove; 42. Buffer shaft; 43. Fifth spring; 44. Accumulator tank; 45. Piston disc; 46. Piston shaft; 47. First sealing plug; 48. Second sealing plug; 49. Solenoid valve; 50. Check valve; 51. Fixed seat; 52. Tilting shaft; 53. Gear; 54. Tooth plate; 55. Fourth adapter frame; 56. Second push-pull rod; 57. Fifth adapter frame; 58. Slide plate; 59. Sixth spring; 60. Directional plate; 61. Transmission port; 62. Cross brace; 63. Transmission hole; 64. Storage box. Detailed Implementation

[0021] To make the technical means, creative features, objectives and effects of this invention easier to understand, the invention will be further described below in conjunction with specific embodiments.

[0022] like Figures 1 to 12 As shown, a flight performance drone safety crash prevention device includes a drone body 1; a parachute compartment 2 is provided on the top of the drone body 1, a first inner liner plate 3 is connected to the inner bottom of the parachute compartment 2, a second inner liner plate 4 is provided on the top of the first inner liner plate 3, a plurality of sleeves 11 are snapped between the opposite surfaces of the second inner liner plate 4 and the first inner liner plate 3, and each sleeve 11 is provided with an arc-shaped groove 5 corresponding to the opposite surfaces of the second inner liner plate 4 and the first inner liner plate 3, and the same arc-shaped shaft 6 is slidably connected in every two mating arc-shaped grooves 5. One end of the arc-shaped shaft 6 is connected to a first spring 7. The arc-shaped shaft 6 forms an elastic support between the first spring 7 and the inner end faces of the two arc-shaped grooves 5 in which it is located. The other end of the arc-shaped shaft 6 is connected to a permanent magnet 8. The opposing faces of the first inner liner plate 3 and the second inner liner plate 4 correspond to each sleeve 11, which is also provided with a magnetic groove 9 that communicates with the two arc-shaped grooves 5. The same electromagnet 10 is installed in each pair of mating magnetic grooves 9. Each sleeve 11 has a first arc-shaped hole 12 on its outer wall corresponding to the arc-shaped groove 5. Each sleeve 11 has a sleeve shaft 15 inside. The sleeve shaft 15 has a second arc-shaped hole 16 corresponding to the first arc-shaped hole 12. The sleeve shaft 15 is also fitted with a second spring 17. The top ends of multiple sleeve shafts 15 are connected to a catapult disc 18. The catapult disc 18 and the opposite surface of the second inner liner plate 4 are elastically supported by multiple second springs 17. A parachute 20 is set above the UAV body 1. A parachute rope 19 is set between the parachute 20 and the catapult disc 18. The top of the second inner liner plate 4 is connected to a pressure accumulator 43. A piston disc 44 is slidably connected inside the pressure accumulator 43. Multiple piston shafts 45 are slidably passed through the top of the pressure accumulator 43. The top ends of the multiple piston shafts 45 are all connected to the bottom of the ejection disc 18, and the bottom ends of the multiple piston shafts 45 are all connected to the top of the piston disc 44.

[0023] Specifically, in this implementation, if the UAV body 1 loses lift due to a malfunction during a flight performance, the system controls the UAV body 1 to quickly open the parachute compartment 2 door, and then supplies power to multiple electromagnets 10. After being energized, the electromagnets 10 have the same magnetic poles on the opposite side of the corresponding permanent magnet block 8, generating a magnetic repulsion force. This force, through the permanent magnet block 8, pushes the arc-shaped shaft 6 to slide within the arc-shaped groove 5, and compresses the first spring 7 to cause elastic deformation. During this process, the permanent magnet block 8 also pushes the arc-shaped shaft 6 to slide along the first arc-shaped hole 12 and the second arc-shaped hole 16. After the permanent magnet block 8 has completely slid out of the second arc-shaped hole 16, the limiting effect of the arc-shaped shaft 6 on the sleeve shaft 15 is released, and the initial state is restored. In this state, multiple second springs 17 are in a compressed, stored state. Therefore, when the sleeve shaft 15 loses the obstruction of the arc-shaped shaft 6, the second springs 17 begin to perform elastic reset motion, pushing the multiple sleeve shafts 15 to slide upwards within the multiple sleeves 11 respectively. Under the joint push of the multiple sleeve shafts 15, the ejection disc 18 quickly slides towards the hatch of the parachute compartment 2, ejecting the parachute 20 from the parachute compartment 2. During the upward movement of the ejection disc 18 within the parachute compartment 2, it also pulls the piston disc 44 upwards within the pressure tank 43 via multiple piston shafts 45. At this time, the space above the piston disc 44 inside the pressure tank 43 is compressed, the pressure below the piston disc 44 decreases, and the one-way valve 49 is triggered to open. Upon activation, air enters the accumulator tank 43 through the one-way valve 49. When the parachute 20 deploys, the instantaneous speed of the UAV body 1 changes drastically due to the resistance of the parachute 20. The instantaneous pulling force of the ejection disc 18 on the piston disc 44 increases accordingly. Since the flow rate of the one-way valve 49 is constant, that is, the amount of air drawn in through the one-way valve 49 per unit time is constant, the pressure variation effect of the air pressure in the accumulator tank 43 can be used to achieve buffering. Non-contact triggering is achieved through the mutual repulsion between the electromagnet 10 and the permanent magnet 8. With the release of the stored force of the second spring 17, the limit can be quickly released and the parachute 20 can be ejected in the instant of a malfunction of the UAV body 1, effectively shortening the response time of the crash protection system. The arc-shaped shaft 6 simultaneously performs multiple functions, including limiting, sliding guidance, and triggering unlocking, enabling the mechanical triggering and pneumatic buffering system to work together organically. This reduces additional actuators and improves system integration. By utilizing the cooperation of the accumulator tank 43, piston disc 44, and fixed flow one-way valve 49, a pneumatic damping effect is automatically generated under the large pulling impact generated at the moment the parachute 20 unfolds. This prevents damage to the connection between the ejection disc 18 and the parachute rope 19 due to impact overload. Through the pneumatic buffering mechanism, the impact speed of the ejection disc 18 at the end of its stroke is reduced, making the attitude of the parachute 20 more stable after it is ejected. This facilitates the smooth and orderly unfolding of the parachute 20 and reduces the risk of entanglement or failure.

[0024] Preferably, two first adapter frames 21 are connected to the front and rear sides of the bottom of the UAV body 1. An adapter shaft 22 is rotatably connected to the inner side of each first adapter frame 21. A third spring 24 is sleeved at the end of the adapter shaft 22. The adapter shaft 22 and the outer wall of the first adapter frame 21 are elastically connected through the third spring 24. An adapter 23 is rotatably connected to the adapter shaft 22 at the inner side of the first adapter frame 21. The other ends of the two adapters 23 located on the same side of the UAV body 1 are provided with a support leg 25.

[0025] Specifically, in this embodiment: the UAV body 1 lands at a low speed under the traction of the parachute 20. Under the weight of the UAV body 1, the two support legs 25 tilt outwards at the moment of landing. During this process, each support leg 25 rotates inside its corresponding first adapter frame 21 via two adapters 23. While the adapters 23 rotate inside the first adapter frame 21 via the adapter shaft 22, they also drive the adapter shaft 22 to twist the third spring 24, forcing the third spring 24 to undergo elastic deformation. This provides an effective buffering effect when the UAV body 1 lands. Through the passive deformation mechanism of the support legs 25 tilting outwards, combined with the torsional deformation of the third spring 24, the vertical and lateral impact energy of the UAV body 1 during landing can be effectively absorbed. The impact load transmitted to the drone body is reduced. The support leg 25 automatically extends outward under its own weight, increasing the ground support span and improving the static stability of the drone body 1 during landing, preventing tipping. The torsional buffer structure composed of the adapter 23, adapter shaft 22 and third spring 24 gives the movement of the support leg 25 a progressive damping characteristic, making the landing process smoother and avoiding damage to precision equipment from rigid impacts. The entire buffering action is triggered entirely by the gravity of the drone body 1 and the landing reaction force, without relying on sensors or active control systems, which improves the reliability and environmental adaptability of the device. The third spring 24 only undergoes elastic deformation during landing and can automatically or manually reset after landing. The support leg 25 structure has the ability to be reused, which helps to reduce the overall maintenance cost of the device.

[0026] Preferably, the top of the support leg 25 has two buffer grooves 40, the positions of the two buffer grooves 40 are respectively corresponding to the two adapters 23, and a buffer shaft 41 is slidably connected inside each buffer groove 40. The two buffer shafts 41 are connected by a cross brace 61. The bottom end of the buffer shaft 41 is connected to a fifth spring 42. The buffer shaft 41 forms an elastic support with the inner bottom of the buffer groove 40 through the fifth spring 42. The other end of the buffer shaft 41 is connected to the bottom of the corresponding adapter 23.

[0027] Specifically, in this embodiment, when the UAV body 1 lands via two support legs 25, the two buffer shafts 41 associated with each support leg 25 will retract inward along their respective buffer grooves 40 and compress the fifth spring 42 to cause it to undergo elastic deformation. Based on the outward tilt of the support legs 25, the axial buffering mechanism formed by the buffer shafts 41 and the fifth spring 42 can further absorb the vertical impact energy at the moment of landing, forming a multi-level buffering effect, reducing the peak load transmitted to the UAV body 1. The elastic compression of the fifth spring 42 allows the support legs 25 to have a gradual downward stroke after touching the ground, avoiding instantaneous recoil caused by rigid contact, improving the smoothness and controllability of the landing process. By absorbing and dissipating the impact energy through the fifth spring 42, the vibration and overload of the frame, parachute compartment 2 and internal precision electronic equipment are effectively reduced, improving the landing safety of the entire aircraft.

[0028] Preferably, the top of the ejection disc 18 has two symmetrically arranged transmission ports 60. The inner wall of each transmission port 60 is provided with a groove 26. The transmission port 60 on the same side and the groove 26 are slidably connected to a slider 27. The top of the slider 27 is connected to a bend shaft 29. The other end of the bend shaft 29 is connected to a buckle 30. The two buckles 30 are connected to each other. The end of the parachute rope 19 passes through the two buckles 30 and is connected to a rope buckle 31. The top of the rope buckle 31 abuts against the bottom of the two buckles 30. Each slider 27 has a first wedge plate 32 connected to its bottom. A second wedge plate 33 is slidably connected to the inclined surface at the bottom of the two first wedge plates 32. A transmission hole 62 is opened in the inner bottom of the umbrella compartment 2. A top rod 34 is slidably connected in the transmission hole 62. The top end of the top rod 34 is connected to the bottom of the second wedge plate 33. A connecting seat 35 is connected to the bottom end of the top rod 34. Two second adapter frames 36 are connected to each of the two cross braces 61 on the connecting seat 35. A first push-pull rod 37 is rotatably connected to the inner side of each second adapter frame 36. A third adapter frame 38 is rotatably connected to the other end of the first push-pull rod 37. An adapter sleeve 39 is connected to the other end of the third adapter frame 38. The adapter sleeve 39 is rotatably connected to the cross brace 61.

[0029] Specifically, in this embodiment: when the two support legs 25 tilt outwards at the moment of landing, they will simultaneously drive the two cross braces 61 to tilt outwards. During this process, the adapter sleeve 39 rotates on the cross brace 61, and generates a pulling force on one end of the second push-pull rod 55 through the third adapter frame 38 connected to the adapter sleeve 39. One end of the second push-pull rod 55 rotates inside the third adapter frame 38, and its other end transmits the pulling force towards the connecting seat 35, while simultaneously rotating inside the second adapter frame 36. 5. Under the combined action of the two pulling forces, the push rod 34 is pushed upward within the transmission port 60. The top of the push rod 34 pushes the second wedge plate 33, causing it to slide simultaneously on the inclined surface at the bottom of the two first wedge plates 32, generating a lateral thrust on the two first wedge plates 32. Under the action of the lateral thrust, the first wedge plates 32 drive the slider 27 to slide within the corresponding transmission port 60. The two sliders 27 pull the two buckles 30 away from each other through the two bent shafts 29, thereby releasing the restriction on the rope buckle 31. The parachute 20 is separated from the drone body 1 by a binding mechanism. This prevents the drone body 1 from being dragged uncontrollably on the ground by the parachute 20 after landing due to natural wind forces. Utilizing the mechanical linkage generated by the tilting of the support legs 25 upon landing, the parachute 20 and the drone body 1 can be reliably separated automatically without additional sensors or power sources, improving the system's intelligence and automation level. The timely release of the parachute 20 from the drone body after landing effectively prevents the parachute 20 from dragging the drone body 1, causing it to roll, collide, or scrape the ground in strong winds, reducing the risk of secondary damage. Through the inclined cooperation of the two first wedge plates 32 and the second wedge plate 33, the vertical movement of the top rod 34 is converted into the synchronous lateral movement of the two sliders 27, achieving the synchronous opening of the two latches 30. The unlocking process is symmetrical and stable, preventing the drone body 1 from being blown by the wind after landing and causing uncontrollable displacement, reducing the possibility of it colliding with surrounding personnel, vehicles, or performance equipment, and improving the overall safety of the flight performance site.

[0030] Preferably, a first sealing plug 46 and a second sealing plug 47 are threadedly connected to the outer wall of the accumulator 43 on the upper and lower sides corresponding to the piston disc 44, respectively. A one-way valve 49 is installed on the outer wall of the accumulator 43 corresponding to the first sealing plug 46, and a solenoid valve 48 is provided on the outer wall of the accumulator 43 corresponding to the second sealing plug 47.

[0031] Specifically, in this embodiment: the support leg 25 tilts outward at the moment of landing, causing the connecting seat 35 to rise. During this process, the connecting seat 35 applies thrust to the second push-pull rod 55 through the second adapter frame 36 on it. One end of the second push-pull rod 55 rotates inside the second adapter frame 36, and the other end transmits the thrust to the toothed plate 53 through the fourth adapter frame 54. The toothed plate 53 slides on the bottom of the drone body 1 and drives the flip shaft 51 to rotate through the gear 52 meshing with it. Driven by the flip shaft 51, the opening of the storage box 63 gradually tends to be vertically downward.

[0032] Preferably, the bottom of the UAV body 1 is connected to two symmetrically distributed fixed seats 50. The opposite surfaces of the two fixed seats 50 are rotatably connected to the same flip shaft 51. A gear 52 is fixedly sleeved on the flip shaft 51. A toothed plate 53 meshes on the tooth surface of the gear 52. The top of the toothed plate 53 is slidably connected to the bottom of the UAV body 1. The end of the toothed plate 53 is connected to a fourth adapter frame 54. The inner side of the fourth adapter frame 54 is rotatably connected to a second push-pull rod 55. The other end of the second push-pull rod 55 is rotatably connected to a fifth adapter frame 56. The fifth adapter frame 56 is connected to the connecting seat 35. A storage box 63 is also fixedly sleeved on the flip shaft 51. A slide plate 57 is slidably connected inside the storage box 63. Multiple sixth springs 58 are connected to one side of the slide plate 57. The slide plate 57 forms an elastic support with the inner wall of the storage box 63 through the multiple sixth springs 58. Multiple anchors 14 are connected to the other side of the slide plate 57. A guide plate 59 is slidably connected to the multiple anchors 14. The guide plate 59 is snapped into the inner wall of the storage box 63.

[0033] Specifically, in this embodiment: the pressure tank 43 and the storage box 63 are connected by a pipe. The system controls the opening of the solenoid valve 48. Previously, during the buffering process, the pressure tank 43 increased its internal air pressure by utilizing air pressure changes. After the solenoid valve 48 opens, the high-pressure airflow quickly flows into the storage box 63 through the pipe, thereby rapidly pushing the slide plate 57 to slide within the storage box 63. The slide plate 57 drives multiple anchors 14 to pierce the ground. Since the drone body 1 is prone to lateral movement after landing due to the dragging effect of the parachute 20, there is a risk of tipping over. Anchoring the anchors 14 into the ground can effectively prevent the drone body 1 from tipping over. The mechanical linkage generated by the tilting of the support leg 25 triggers the high-pressure gas stored in the pressure tank 43 to drive the anchors 14 into the ground, without the need for an additional power source. Automatic anchoring after landing is achieved. After the anchor 14 penetrates the ground, it provides reliable lateral force restraint for the UAV body 1, solving the problem of disordered movement and overturning caused by the parachute 20 dragging, and significantly improving the stability after landing. The high-pressure gas accumulated in the accumulator 43 during the landing buffer process is used to drive the anchoring actuator, realizing the recovery and reuse of impact energy and improving the energy utilization efficiency of the system. The process of the flipping shaft 51 driving the storage box 63 to change from a horizontal storage posture to a vertical downward working posture is coordinated with the action of the anchor 14 penetrating, ensuring that the anchor 14 penetrates the ground in the correct direction. In the case of strong winds or low ground adhesion, the anchor 14 can provide additional fixing force to ensure that the UAV body 1 maintains a stable attitude after landing.

[0034] During operation, if the drone body 1 loses lift due to a malfunction during a flight performance, the system controls the drone body 1 to quickly open the parachute compartment 2 door, and then supplies power to multiple electromagnets 10. After the electromagnets 10 are energized, their magnetic poles are the same as the opposite face of the corresponding permanent magnet block 8, generating a magnetic repulsion force. This force, in turn, pushes the arc-shaped shaft 6 to slide in the arc-shaped groove 5 through the permanent magnet block 8, and compresses the first spring 7 to cause it to undergo elastic deformation. During this process, the permanent magnet 8 also pushes the arc-shaped shaft 6 to slide along the first arc-shaped hole 12 and the second arc-shaped hole 16. After the permanent magnet 8 slides out completely from the second arc-shaped hole 16, the limiting effect of the arc-shaped shaft 6 on the sleeve shaft 15 is released. In the initial state, the multiple second springs 17 are in a compressed and stored state. Therefore, when the sleeve shaft 15 loses the obstruction of the arc-shaped shaft 6, the second springs 17 begin to perform elastic reset movement, pushing the multiple sleeve shafts 15 to slide upward in the multiple sleeves 11 respectively. Under the joint push of the multiple sleeve shafts 15, the ejection disc 18 slides quickly towards the hatch of the parachute compartment 2 and ejects the parachute 20 from the parachute compartment 2. As the ejection disc 18 ascends within the parachute compartment 2, it also pulls the piston disc 44 upwards within the accumulator tank 43 via multiple piston shafts 45. At this time, the space above the piston disc 44 inside the accumulator tank 43 is compressed, and the pressure below the piston disc 44 decreases. The one-way valve 49 is triggered and opened, allowing air to enter the accumulator tank 43 through the one-way valve 49. When the parachute 20 deploys, the instantaneous speed of the UAV body 1 changes drastically due to the resistance of the parachute 20. The instantaneous pulling force of the ejection disc 18 on the piston disc 44 increases accordingly. Since the flow rate of the one-way valve 49 remains constant, i.e., the amount of air drawn in through the one-way valve 49 per unit time is constant, the pressure variation effect of the air pressure inside the accumulator tank 43 can be used to achieve buffering. The UAV body 1 lands at a low speed under the traction of the parachute 20. Under the action of the weight of the UAV body 1, the two support legs 25 tilt outward at the moment of landing. During this process, the two ends of each support leg 25 rotate inside the corresponding first adapter frame 21 through two adapters 23. While the adapter 23 rotates inside the first adapter frame 21 through the adapter shaft 22, it drives the adapter shaft 22 to twist the third spring 24, forcing the third spring 24 to undergo elastic deformation, thereby generating an effective buffering effect when the UAV body 1 lands. When the drone body 1 lands via two support legs 25, the two buffer shafts 41 associated with each support leg 25 will retract inward along their respective buffer grooves 40 and compress the fifth spring 42 to cause it to undergo elastic deformation. When the two support legs 25 tilt outwards at the moment of landing, they simultaneously cause the two cross braces 61 to tilt outwards. During this process, the adapter sleeve 39 rotates on the cross brace 61, and through the third adapter frame 38 connected to the adapter sleeve 39, it generates a pulling force on one end of the second push-pull rod 55. One end of the second push-pull rod 55 rotates inside the third adapter frame 38, and its other end transmits the pulling force towards the connecting seat 35, while simultaneously rotating inside the second adapter frame 36. Under the combined action of the two pulling forces, the connecting seat 35 pushes... The moving push rod 34 slides upward within the transmission port 60. The top of the push rod 34 pushes the second wedge plate 33, causing it to slide simultaneously on the inclined surface at the bottom of the two first wedge plates 32, and generating a lateral thrust on the two first wedge plates 32. Under the action of the lateral thrust, the first wedge plates 32 drive the slider 27 to slide within the corresponding transmission port 60. The two sliders 27 pull the two buckles 30 away from each other through the two bent shafts 29, thereby releasing the limiting constraint on the rope buckle 31 and enabling the parachute 20 to separate from the UAV body 1. At the same time, as the support leg 25 drives the connecting seat 35 to rise, the connecting seat 35 applies a thrust to the second push-pull rod 55 through the second adapter 36 on it. One end of the second push-pull rod 55 rotates inside the second adapter 36, and the other end transmits the thrust to the toothed plate 53 through the fourth adapter 54. The toothed plate 53 slides at the bottom of the drone body 1 and drives the flip shaft 51 to rotate through the gear 52 that meshes with it. Under the drive of the flip shaft 51, the opening of the storage box 63 gradually tends to be vertically downward. The accumulator tank 43 and the storage box 63 are connected by a pipe. The system controls the solenoid valve 48 to open. Previously, the accumulator tank 43 increased its internal air pressure by using air pressure changes during the buffering process. After the solenoid valve 48 is opened, the high-pressure airflow flows into the storage box 63 through the pipe, which in turn quickly pushes the slide plate 57 to slide inside the storage box 63. The slide plate 57 drives multiple anchors 14 to pierce the ground. Since the drone body 1 is prone to lateral movement under the drag of the parachute 20 after landing, there is a risk of tipping over. Anchoring the anchors 14 into the ground can effectively prevent the drone body 1 from tipping over.

[0035] The embodiments of the present invention have been described above with reference to the accompanying drawings. However, the present invention is not limited to the specific embodiments described above. The specific embodiments described above are merely illustrative and not restrictive. Those skilled in the art can make many other forms under the guidance of the present invention without departing from the spirit and scope of the claims. All of these forms are within the protection scope of the present invention.

Claims

1. A safety crash prevention device for a flight performance drone, comprising the drone body; characterized in that: The top of the drone body is provided with a parachute compartment, the bottom of the parachute compartment is connected to a first inner liner plate, the top of the first inner liner plate is provided with a second inner liner plate, and multiple sleeves are snapped between the opposite surfaces of the second inner liner plate and the first inner liner plate. Each sleeve is provided with an arc-shaped groove corresponding to the opposite surfaces of the second inner liner plate and the first inner liner plate, and the same arc-shaped shaft is slidably connected in every two mating arc-shaped grooves. One end of the arc-shaped shaft is connected to a first spring, and the arc-shaped shaft forms an elastic support between the first spring and the inner end faces of the two arc-shaped grooves it is located in. The other end of the arc-shaped shaft is connected to a permanent magnet. The opposing surfaces of the first inner liner plate and the second inner liner plate are respectively provided with magnetic grooves that communicate with the two arc-shaped grooves. The same electromagnet is installed in every two mating magnetic grooves.

2. The safety crash prevention device for a flight performance drone according to claim 1, characterized in that: Each sleeve has a first arc-shaped hole on its outer wall corresponding to the arc-shaped groove. Each sleeve has a sleeve shaft inside, and the sleeve shaft has a second arc-shaped hole corresponding to the first arc-shaped hole. The sleeve shaft is also fitted with a second spring. The top ends of multiple sleeve shafts are connected to a catapult disc. The catapult disc and the opposite surface of the second inner liner are elastically supported by multiple second springs. A parachute is provided above the drone body, and parachute lines are provided between the parachute and the catapult disc.

3. The safety anti-crash device for a flight performance drone according to claim 2, characterized in that: Two first adapter frames are connected to the front and rear sides of the bottom of the drone body. An adapter shaft is rotatably connected to the inner side of each first adapter frame. A third spring is sleeved on the end of the adapter shaft. The adapter shaft is elastically connected to the outer wall of the first adapter frame through the third spring. An adapter is rotatably connected to the adapter shaft at the inner side of the first adapter frame. The other ends of the two adapters located on the same side of the drone body are provided with a support leg.

4. The safety anti-crash device for a flight performance drone according to claim 3, characterized in that: The top of the support leg has two buffer grooves, and the positions of the two buffer grooves correspond to the two adapters respectively. A buffer shaft is slidably connected inside each buffer groove. The two buffer shafts are connected by a cross brace. A fifth spring is connected to the bottom of the buffer shaft. The buffer shaft forms an elastic support with the inner bottom of the buffer groove through the fifth spring. The other end of the buffer shaft is connected to the bottom of the corresponding adapter.

5. A safety crash prevention device for a flight performance drone according to claim 4, characterized in that: The top of the ejection disc has two symmetrically arranged transmission ports. The inner wall of each transmission port is provided with a sliding groove. The transmission port on the same side and the sliding groove are slidably connected to a slider. The top of the slider is connected to a bend shaft, and the other end of the bend shaft is connected to a buckle. The two buckles are connected to each other. The end of the paracord passes through the two buckles and is connected to a rope buckle. The top of the rope buckle abuts against the bottom of the two buckles.

6. The safety crash prevention device for a flight performance drone according to claim 5, characterized in that: Each slider is connected to a first wedge plate at its bottom. A second wedge plate is slidably connected to the inclined surfaces at the bottom of the two first wedge plates. A transmission hole is provided in the inner bottom of the parachute compartment. A top rod is slidably connected in the transmission hole. The top end of the top rod is connected to the bottom of the second wedge plate. A connecting seat is connected to the bottom end of the top rod. Two second adapter frames are connected to each of the two cross braces on the connecting seat. A first push-pull rod is rotatably connected to the inner side of each second adapter frame. A third adapter frame is rotatably connected to the other end of the first push-pull rod. An adapter sleeve is connected to the other end of the third adapter frame. The adapter sleeve is rotatably connected to the cross brace.

7. A safety crash prevention device for a flight performance drone according to claim 6, characterized in that: The top of the second inner liner is connected to a pressure tank, and a piston disc is slidably connected inside the pressure tank. Multiple piston shafts are slidably passed through the top of the pressure tank, the top ends of the multiple piston shafts are connected to the bottom of the ejection disc, and the bottom ends of the multiple piston shafts are connected to the top of the piston disc. The outer wall of the accumulator is threaded with a first sealing plug and a second sealing plug on the upper and lower sides corresponding to the piston disc, respectively. A one-way valve is installed on the outer wall of the accumulator corresponding to the first sealing plug, and a solenoid valve is provided on the outer wall of the accumulator corresponding to the second sealing plug.

8. The safety crash prevention device for a flight performance drone according to claim 7, characterized in that: The bottom of the drone body is connected to two symmetrically distributed fixed seats. The two fixed seats are rotatably connected to the same flip shaft between their opposite surfaces. A gear is fixedly sleeved on the flip shaft. A toothed plate meshes with the tooth surface of the gear. The top of the toothed plate is slidably connected to the bottom of the drone body. The end of the toothed plate is connected to a fourth adapter frame. The inner side of the fourth adapter frame is rotatably connected to a second push-pull rod. The other end of the second push-pull rod is rotatably connected to a fifth adapter frame. The fifth adapter frame is connected to the connecting seat. A storage box is also fixedly sleeved on the flip shaft. A slide plate is slidably connected inside the storage box. Multiple sixth springs are connected to one side of the slide plate. The slide plate forms an elastic support with the inner wall of the storage box through the multiple sixth springs. Multiple anchors are connected to the other side of the slide plate. A directional plate is slidably connected to the multiple anchors. The directional plate is snapped into the inner wall of the storage box.

Images