Vertical forced landing protection device for unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicles, and particularly discloses an unmanned aerial vehicle vertical forced landing protection device which comprises an unmanned aerial vehicle, and power cavities are formed in the four corners of the bottom of the unmanned aerial vehicle; the number of the lifting rods is four, the four lifting rods are arranged at the four corners of the bottom end of the unmanned aerial vehicle correspondingly, and the positions of the four lifting rods correspond to the positions of the four power cavities correspondingly. The power mechanism is arranged in an inner cavity of the power cavity; the protection mechanism is arranged at the bottom end of the unmanned aerial vehicle. The device can quickly respond when the power of the paddles fails, effectively maintain the balance of the unmanned aerial vehicle, avoid deflection in the forced landing process and remarkably improve the forced landing success rate, in addition, a protection mechanism is integrated, the descending speed can be slowed down, additional supporting protection can be provided after landing, impact caused by uneven ground is effectively resisted, and the safety of the unmanned aerial vehicle is improved. The integrity of the unmanned aerial vehicle structure is ensured, the economic loss is reduced, and the subsequent task execution capability and the data collection continuity are ensured.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a vertical forced landing protection device for UAVs. Background Art

[0002] As a modern flying device that integrates aviation technology, remote control technology, communication technology, sensor technology and intelligent control technology, UAV has been widely used in both civil and military fields in recent years. With its advantages of strong flexibility, simple operation and low cost, UAV has demonstrated great potential and value in many aspects such as aerial photography, surveying and mapping, environmental monitoring, agricultural plant protection, logistics and transportation, and military reconnaissance. However, drones may encounter various emergencies during flight, which may cause them to be unable to fly normally and require emergency landing measures. These emergencies include but are not limited to power system failure, flight control system failure, severe weather conditions, electromagnetic interference, battery exhaustion, and encountering obstacles. In these cases, the safe landing of drones becomes an urgent problem to be solved; In particular, in the event of a power system failure, one or more of the drone's propellers may stop rotating, causing the drone to lose balance and its ability to fly stably. At this point, if effective forced landing measures are not taken in a timely manner, the drone is likely to crash due to loss of control, causing serious economic losses or even casualties. During a vertical landing, if one of the drone's propeller blades loses power, the lift generated by the remaining blades will no longer be evenly distributed, causing the drone to tilt during descent. This not only increases the difficulty of the forced landing but may also damage the drone due to excessive impact force during landing. Furthermore, even in emergency landing mode, the drone's flight control system can attempt to maintain balance by adjusting the rotational speed of the remaining blades. However, the lack of real-time blade angle of attack adjustment capability makes it difficult to accurately compensate for flight attitude deviations caused by power imbalance, thus limiting the success rate of the forced landing and the drone's survivability. In addition, even if the drone can barely make a vertical landing, due to the lack of necessary buffering and protection mechanisms, factors such as uneven ground may cause the drone to suffer severe impact during landing, which may cause serious damage to the drone structure or even complete scrapping. This will not only cause economic losses, but may also affect the execution capability of subsequent tasks and the continuity of data collection. Summary of the Invention

[0003] The purpose of the present invention is to provide a UAV vertical forced landing protection device to at least solve the problems proposed in the prior art of accurately compensating for flight attitude deviation caused by power imbalance and lacking necessary buffering and protection mechanisms.

[0004] To achieve the above-mentioned object, the present invention provides the following technical solution: a vertical forced landing protection device for a UAV, comprising: a UAV, wherein each of the four corners of the bottom of the UAV is provided with a power chamber; four lifting rods, which are respectively arranged at the four corners of the bottom of the UAV, and the positions of the four lifting rods respectively correspond to the positions of the four power chambers; a power mechanism, which is arranged in the inner cavity of the power chamber; and a protection mechanism, which is arranged at the bottom of the UAV; Preferably, the power mechanism includes: a first rotating rod, the bottom of the outer wall of the first rotating rod is rotatably arranged on the outside of the top end of the inner cavity of the power chamber through a bearing, the top end of the first rotating rod is rotatably extended out of the top end of the drone, and the inner wall of the first rotating rod is provided with a plurality of first sliding grooves equidistant from top to bottom along the circumferential direction; the first gear is sleeved on the bottom of the outer wall of the first rotating rod and locked by a top screw, and the first gear is located in the inner cavity of the power chamber; the mounting seat is arranged at the top end of the first rotating rod; the number of rotating rods is two, and the middle of the outer walls of the two rotating rods are rotatably arranged on the middle of the front and rear sides of the inner wall of the mounting seat through bearings, and the outer end of the rotating rod is rotatably extended out of the outer wall of the mounting seat; the blade is arranged at the outer end of the rotating rod; the motor is screwed to the inner side of the bottom end of the inner cavity of the power chamber; the first connecting rod is screwed to the output end of the motor; the third gear is sleeved on the outer wall of the first connecting rod and locked by a top screw, and the third gear is meshed with the first gear.

[0005] Preferably, in order to adjust the angle of attack of the blades, the power mechanism includes: a push rod, the middle portion of the outer wall of the push rod is slidably adapted and inserted into the inner cavity of the first rotating rod, and the upper and lower ends of the push rod are respectively slidably extended from the upper and lower ends of the first rotating rod; the number of first sliders is several, and the several first sliders are respectively arranged on the outer wall of the push rod at equal intervals along the circumference, and the first sliders are slidably adapted and inserted into the inner cavity of the first slide groove; the base is rotatably arranged at the bottom end of the push rod through a bearing; the first electric telescopic rod is arranged in the inner cavity of the lifting rod, and the top end of the first electric telescopic rod is slidably extended into the inner cavity of the power cavity corresponding to its position, and the bottom end of the base is arranged at the top end of the first electric telescopic rod; the support plate is arranged at the top end of the push rod; the number of first racks is two, and the two first racks are respectively arranged at the front left side and the rear right side of the bottom end of the support plate, and the first rack is slidably embedded in the inner cavity of the mounting seat; the second gear is sleeved on the inner side of the outer wall of the rotating rod and locked by a top screw, and the two second gears are respectively engaged with the two first racks.

[0006] Preferably, in order to monitor the rotation of the blades, the power mechanism includes: a signal disk, which is sleeved on the bottom end of the outer wall of the first rotating rod and locked by a top screw, and the signal disk is located in the inner cavity of the power cavity; a Hall-type speed sensor is arranged on the inner wall of the power cavity, and the position of the Hall-type speed sensor corresponds to the position of the signal disk.

[0007] Preferably, in order to protect the drone, the protection mechanism includes: a second rotating rod, the number of the second rotating rods is eight, the eight second rotating rods are divided into four groups, two of each group is divided into four groups, the four groups of second rotating rods are rotatably arranged at the four corners of the bottom end of the drone through bearings, and the two second rotating rods in each group are respectively located on both sides of the lifting rod; one end of the first connecting rod is fixedly sleeved on the outer wall of the second rotating rod; the first guide rod is arranged in the inner cavity of the first connecting rod; the spring is sleeved on the outer wall of the first guide rod, and one end of the spring is clamped on the inner wall of the first connecting rod; one end of the second connecting rod is slidably embedded in the inner cavity of the first connecting rod, and the other end of the spring is clamped on the outer wall of the second connecting rod, and the other end of the second connecting rod is rotatably connected to the other end of the adjacent second connecting rod through a pin shaft.

[0008] Preferably, in order to promote the first connecting rod and the second connecting rod to rotate, the protection mechanism also includes: a storage plate, the storage plate is arranged at the bottom end of the drone, and a second slide groove is opened at the four corners of the bottom end of the storage plate; the two ends of the second guide rod are respectively arranged on the inner and outer sides of the inner cavity of the second slide groove; a second slider, the second slider can be slidably adapted and inserted into the outer side of the inner cavity of the second slide groove, and the second slider can be slidably sleeved on the outer wall of the second guide rod; the second rack is arranged at the bottom end of the second slider; the fourth gear is sleeved on the bottom end of the outer wall of the second rotating rod and locked by a top screw, and the fourth gear is meshed with the second rack; the number of the second electric telescopic rods is four, and the four second electric telescopic rods are respectively arranged at the four corners of the bottom end of the storage plate, and the inner middle sides of the four second racks are respectively arranged at the outer ends of the four second electric telescopic rods.

[0009] Preferably, in order to slow down the landing speed of the drone, the protection mechanism also includes: a windshield cloth, the number of which is four, one side of the four windshield cloths are respectively arranged at the four corners of the inner cavity of the storage plate, and the other side of the four windshield cloths are respectively arranged on the inner side of the second connecting rod and the first connecting rod connected by four groups of pins.

[0010] Preferably, the number of teeth on the second rack is greater than one-fourth the number of teeth on the outer wall of the fourth gear.

[0011] The invention proposes a UAV vertical forced landing protection device, which has the following beneficial effects: 1. The present invention can support the drone through the lifting rod. By starting the motor, the third gear can be driven to rotate through the first connecting rod. The rotation of the third gear can drive the first rotating rod to rotate through the first gear. The rotation of the first rotating rod can drive the mounting base to rotate. The cooperation between the first slide groove and the first slider can drive the push rod to rotate synchronously with the first rotating rod. The rotation of the mounting base can drive the blades to rotate with the mounting base through the rotating rod, so that the rotating blades can be used to drive the drone to fly.

[0012] 2. The present invention drives the signal disk to rotate by the first rotating rod, and then uses the Hall-type speed sensor to monitor the signal disk, thereby monitoring the rotation speed and rotation state of the blades. When one group of blades stops rotating due to a fault or other reasons, the corresponding Hall-type speed sensor transmits a signal to the main controller of the drone, so that the main controller of the drone adjusts the rotation speed of the remaining intact blades and starts the first electric telescopic rod to push the push rod upward. The upward movement of the push rod can drive the first rack to move upward through the support plate. The upward movement of the first rack can prompt the second gear to drive the blades to rotate through the rotating rod, thereby adjusting the angle of attack of the blades, and then changing the direction of the lift generated when the blades cut the air. Additional lift can be generated to offset the lift lost by the failed blades, thereby maintaining the vertical stability of the drone.

[0013] 3. When the present invention is landing, the second electric telescopic rod can be started to push the second rack to move outward, and then the second rack can be used to prompt the fourth gear to drive the first connecting rod to rotate through the second rotating rod. The rotation of the first connecting rod can drive the second connecting rod to rotate. At the same time, the first connecting rod and the second connecting rod rotate, and the second connecting rod can be prompted to slide toward the inner cavity of the first connecting rod and squeeze the spring to elastically deform until the first connecting rod rotates 45 degrees. Continuing to rotate will prompt the second connecting rod to gradually move out of the inner cavity of the first connecting rod and prompt the spring to gradually return to its initial state until the first connecting rod rotates 45 degrees again. At this time, the spring returns to its initial state. During the rotation of the second connecting rod and the first connecting rod, the windshield cloth will be gradually stretched open, and then the windshield cloth can be used to reduce the landing speed of the drone, and the protruding second connecting rod can be used to shield the drone to prevent the drone from contacting the ground and causing damage to the drone when it tilts.

[0014] 4. This device can respond quickly when the blade power fails, effectively maintaining the balance of the drone and avoiding tilting during the forced landing, significantly improving the success rate of the forced landing. In addition, the integrated protection mechanism can not only slow down the descent speed, but also provide additional support and protection after landing, effectively resisting the impact caused by uneven ground, ensuring the integrity of the drone structure, reducing economic losses, and ensuring the subsequent mission execution capability and the continuity of data collection, greatly enhancing the safety and reliability of the drone in vertical forced landing situations. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the structure of the present invention; Figure 2 It is a schematic diagram of the structure of the protection mechanism; Figure 3 An exploded view of the present invention; Figure 4 Exploded diagram to protect the organization; Figure 5 It is a structural diagram of the power mechanism; Figure 6 This is the exploded diagram of the power mechanism; Figure 7 for Figure 3 A magnified view of point A; Figure 8 for Figure 4 Enlarged view of point B; Figure 9 for Figure 4 Enlarged view of point C; Figure 10 for Figure 4 Enlarged view of point D; Figure 11 for Figure 6 Enlarged view of point E.

[0016] In the figure: 1. UAV; 2. power chamber; 3. lifting rod; 4. power mechanism; 41. first rotating rod; 42. first slide; 43. first gear; 44. first slider; 45. push rod; 46. base; 47. first electric telescopic rod; 48. support plate; 49. first rack; 410. mounting base; 411. rotating rod; 412. second gear; 413. propeller; 414. motor; 415. first connecting rod; 416. third gear; 417. signal disk; 418. Hall-type speed sensor; 5. protection mechanism; 51. second rotating rod; 52. first connecting rod; 53. first guide rod; 54. spring; 55. second connecting rod; 56. fourth gear; 57. storage plate; 58. second slide; 59. second guide rod; 510. second slider; 511. second rack; 512. second electric telescopic rod; 513. windshield cloth DETAILED DESCRIPTION

[0017] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0018] See also Figures 1-11The present invention provides a technical solution for a vertical forced landing protection device for a drone, comprising: a drone 1, a power chamber 2, a lifting rod 3, a power mechanism 4 and a protection mechanism 5. The four corners of the bottom of the drone 1 are each provided with a power chamber 2. The drone 1 is of existing technology and has a built-in gyroscope. No further details will be given herein. There are four lifting rods 3, which are respectively arranged at the four corners of the bottom end of the drone 1. The positions of the four lifting rods 3 correspond to the positions of the four power chambers 2. The lifting rods 3 are used to support the drone 1. The power mechanism 4 is arranged in the inner cavity of the power chamber 2. The power mechanism 4 is used to provide power for the drone 1 to fly. The protection mechanism 5 is arranged at the bottom end of the drone 1 and is used to protect the drone 1.

[0019] As a preferred solution, further, the power mechanism 4 includes: a first rotating rod 41, a first slide 42, a first gear 43, a first slider 44, a push rod 45, a base 46, a first electric telescopic rod 47, a support plate 48, a first rack 49, a mounting seat 410, a rotating rod 411, a second gear 412, a blade 413, a motor 414, a first connecting rod 415, a third gear 416, a signal disk 417 and a Hall-type speed sensor 418. The bottom of the outer wall of the first rotating rod 41 is rotatably arranged on the outside of the top end of the inner cavity of the power cavity 2 through a bearing, and the top end of the first rotating rod 41 is rotatably extended out of the top end of the drone 1. The inner wall of the first rotating rod 41 is provided with a plurality of first slides 42 equidistantly from top to bottom along the circumferential direction. The gear 43 is sleeved on the bottom of the outer wall of the first rotating rod 41 and is locked by a top screw. The first gear 43 is located in the inner cavity of the power chamber 2. The rotation of the first gear 43 can drive the first rotating rod 41 to rotate. The mounting seat 410 is set at the top of the first rotating rod 41. There are two rotating rods 411. The middle of the outer wall of the two rotating rods 411 are rotatably set at the middle of the front and back sides of the inner wall of the mounting seat 410 through bearings respectively. The outer end of the rotating rod 411 can rotatably extend out of the outer wall of the mounting seat 410. The rotating rod 411 is used to install the blade 413. The blade 413 is set at the outer end of the rotating rod 411. The rotation of the blade 413 can provide power for the flight of the drone 1. The motor 414 is screwed to the inner side of the bottom end of the inner cavity of the power chamber 2. The motor 414 is In the prior art, the motor 414 is a servo motor, and the motor 414 is connected to a servo controller. I will not elaborate on this here. The motor 414 is used to drive the third gear 416 to rotate through the first connecting rod 415. The first connecting rod 415 is screwed to the output end of the motor 414. The third gear 416 is sleeved on the outer wall of the first connecting rod 415 and locked by a top screw. The third gear 416 is engaged with the first gear 43. The rotation of the third gear 416 can drive the first rotating rod 41 to rotate through the first gear 43. The middle part of the outer wall of the push rod 45 can be slidably adapted and inserted into the inner cavity of the first rotating rod 41. The upper and lower ends of the push rod 45 can respectively slidably extend out of the upper and lower ends of the first rotating rod 41. The push rod 45 is used to push the support plate 48 drives the first rack 49 to move up and down. There are several first sliders 44, and several first sliders 44 are respectively arranged on the outer wall of the push rod 45 at equal distances along the circumferential direction. The first slider 44 can be slidably adapted to be inserted into the inner cavity of the first slide groove 42. The base 46 is rotatably arranged at the bottom end of the push rod 45 through a bearing. The first electric telescopic rod 47 is arranged in the inner cavity of the lifting rod 3. The top end of the first electric telescopic rod 47 can slidably extend into the inner cavity of the power cavity 2 corresponding to its position. The bottom end of the base 46 is arranged at the top end of the first electric telescopic rod 47. The first electric telescopic rod 47 is a prior art and will not be described in detail here. The first electric telescopic rod 47 is used here to push the push rod 45 to move up and down. The support plate 48 is arranged at the top end of the push rod 45.There are two first racks 49, and the two first racks 49 are respectively arranged at the front left side and the rear right side of the bottom end of the support plate 48. The first rack 49 is slidably embedded in the inner cavity of the mounting seat 410. The first rack 49 moves up and down and can drive the rotating rod 411 to rotate through the second gear 412. The second gear 412 is sleeved on the inner side of the outer wall of the rotating rod 411 and locked by the top screw. The two second gears 412 are respectively engaged with the two first racks 49, and the signal disk 417 is sleeved on the first rotating rod 41 The bottom end of the outer wall of the power chamber 2 is locked by a top screw. The signal disk 417 is located in the inner cavity of the power chamber 2. The signal disk 417 is a prior art and will not be described in detail here. The Hall-type speed sensor 418 is set on the inner wall of the power chamber 2. The position of the Hall-type speed sensor 418 corresponds to the position of the signal disk 417. The Hall-type speed sensor 418 is a prior art and will not be described in detail here. The Hall-type speed sensor 418 is used here to monitor the rotation speed and rotation state of the blade 413 by monitoring the rotation speed of the signal disk 417.

[0020] As a preferred solution, further, the protection mechanism 5 includes: a second rotating rod 51, a first connecting rod 52, a first guide rod 53, a spring 54, a second connecting rod 55, a fourth gear 56, a storage plate 57, a second slide groove 58, a second guide rod 59, a second slider 510, a second rack 511, a second electric telescopic rod 512 and a windshield cloth 513. The number of second rotating rods 51 is eight, and the eight second rotating rods 51 are divided into four groups, two by two. The four groups of second rotating rods 51 are rotatably arranged at the four corners of the bottom end of the drone 1 through bearings. The two second rotating rods 51 in each group are respectively located on both sides of the lifting rod 3. One end of the first connecting rod 52 is fixedly sleeved on the outer wall of the second rotating rod 51. The first guide rod 53 is arranged on the first The inner cavity of the connecting rod 52, the spring 54 is sleeved on the outer wall of the first guide rod 53, and one end of the spring 54 is clamped on the inner wall of the first connecting rod 52. The spring 54 is a rotation spring. It elastically deforms after being squeezed or stretched by external force, and returns to its initial state after the external force is removed. The spring 54 is used to push the second connecting rod 55 to move out of the inner cavity of the first connecting rod 52. One end of the second connecting rod 55 is slidably embedded in the inner cavity of the first connecting rod 52, and the other end of the spring 54 is clamped on the outer wall of the second connecting rod 55. The other end of the second connecting rod 55 is rotatably connected to the other end of the second connecting rod 55 adjacent to it through a pin shaft. The storage plate 57 is arranged at the bottom end of the drone 1, and the four corners of the bottom end of the storage plate 57 are provided with second sliding grooves 58. The storage plate 57 is used The windshield cloth 513 is fixed and stored. The two ends of the second guide rod 59 are respectively arranged on the inner and outer sides of the inner cavity of the second slide groove 58. The second slider 510 can be slidably adapted and inserted into the outer side of the inner cavity of the second slide groove 58. The second slider 510 can be slidably sleeved on the outer wall of the second guide rod 59. The second rack 511 is arranged at the bottom end of the second slider 510. The movement of the second rack 511 can cause the fourth gear 56 to rotate. The fourth gear 56 is sleeved on the bottom end of the outer wall of the second rotating rod 51 and locked by a top screw. The fourth gear 56 is meshed with the second rack 511. The number of teeth on the second rack 511 is greater than one-fourth of the number of teeth on the outer wall of the fourth gear 56, ensuring that the fourth gear 56 can drive the first gear 56 through the second rotating rod 51 The connecting rod 52 rotates 90 degrees, and the number of the second electric telescopic rods 512 is four. The four second electric telescopic rods 512 are respectively arranged at the four corners of the bottom end of the storage plate 57, and the inner middle parts of the four second racks 511 are respectively arranged at the outer ends of the four second electric telescopic rods 512. The second electric telescopic rod 512 is the existing technology and will not be described in detail here. The second electric telescopic rod 512 is used here to push the second rack 511 to move. The number of the windshield cloths 513 is four, and one side of the four windshield cloths 513 are respectively arranged at the four corners of the inner cavity of the storage plate 57, and the other side of the four windshield cloths 513 are respectively arranged on the inner sides of the second connecting rod 55 and the first connecting rod 52 connected by four groups of pins. The windshield cloths 513 are used to reduce the landing speed of the drone 1.

[0021] The detailed connection means are well-known technologies in this field. The following mainly introduces the working principle and process. The specific work is as follows.

[0022] This device can support the drone 1 by using the lifting rod 3, and the starting motor 414 drives the third gear 416 to rotate through the first connecting rod 415. The rotation of the third gear 416 can drive the first rotating rod 41 to rotate through the first gear 43, and the rotation of the first rotating rod 41 can drive the mounting base 410 to rotate, and the cooperation between the first slide groove 42 and the first slider 44 can drive the push rod 45 to rotate synchronously with the first rotating rod 41. The rotation of the mounting base 410 can drive the blade 413 to rotate along with the mounting base 410 through the rotating rod 411, so that the rotating blade 413 can be used to drive the drone to fly. In the process of the drone 1 flying, the rotation of the first rotating rod 41 can drive the signal disk 417 to rotate. The rotation speed and rotation state of the signal disk 417 can be monitored by the Hall-type speed sensor 418, thereby monitoring the rotation speed and rotation state of the blades 413. When one group of blades 413 stops rotating due to a fault or other reasons, the first rotating rod 41 corresponding to its position stops rotating, and the corresponding Hall-type speed sensor 418 transmits a signal to the main controller of the drone 1, thereby adjusting the rotation speed of the remaining intact blades 413 by the main controller of the drone 1, and starting the first electric telescopic rod 47 to push the push rod 45 upward. The upward movement of the push rod 45 can drive the first rack 49 to move upward through the support plate 48, and the upward movement of the first rack 49 can prompt the second gear 412 to move through the rotating rod 411 The blades 413 are driven to rotate, so that the angle of attack of the blades 413 can be adjusted, and the direction of the lift generated when the blades 413 cut the air can be changed, and additional lift can be generated to offset the lift lost by the failed blades 413, thereby maintaining the vertical landing stability of the drone 1. At the same time, during vertical landing, the second electric telescopic rod 512 can be started to push the second rack 511 to move outward, and then the second rack 511 can be used to prompt the fourth gear 56 to drive the first connecting rod 52 to rotate through the second rotating rod 51. The rotation of the first connecting rod 52 can drive the second connecting rod 55 to rotate. When the first connecting rod 52 and the second connecting rod 55 rotate, the second connecting rod 55 can be prompted to slide toward the inner cavity of the first connecting rod 52 and squeeze the spring to generate The windshield 513 is gradually stretched open during the rotation of the second link 55 and the first link 52, and the landing speed of the drone can be reduced by the windshield 513 until the first link 52 rotates 45 degrees. Continuing to rotate will cause the second link 55 to gradually move out of the inner cavity of the first link 52, and cause the spring 54 to gradually return to its initial state until the first link 52 rotates 45 degrees again. At this time, the spring 54 returns to its initial state, and the protruding second link 55 can be used to shield the drone 1 to prevent the drone 1 from tilting when landing on uneven ground, causing the drone 1 to contact the ground and causing damage to the drone 1. This device can respond quickly when the power of the blade 413 fails, and effectively maintain the balance of the drone 1.This prevents tilting during forced landing, significantly improving the success rate of forced landings. Furthermore, the integrated protection mechanism 5 not only slows down the descent speed but also provides additional support and protection after landing, effectively resisting the impact of uneven ground. This ensures the structural integrity of the drone 1, reduces economic losses, and ensures the ability to execute subsequent missions and the continuity of data collection, significantly enhancing the safety and reliability of the drone 1 in vertical forced landing situations.

[0023] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A UAV vertical forced landing protection device, characterized in that: include: An unmanned aerial vehicle (1), wherein the four corners of the bottom of the unmanned aerial vehicle (1) are each provided with a power chamber (2); Lifting rods (3), the number of the lifting rods (3) being four, the four lifting rods (3) being respectively arranged at four corners of the bottom end of the drone (1), and the positions of the four lifting rods (3) corresponding to the positions of the four power chambers (2); A power mechanism (4), wherein the power mechanism (4) is arranged in the inner cavity of the power cavity (2); A protection mechanism (5), wherein the protection mechanism (5) is arranged at the bottom end of the drone (1); The power mechanism (4) comprises: A first rotating rod (41), the bottom of the outer wall of the first rotating rod (41) being rotatably arranged on the outer side of the top end of the inner cavity of the power cavity (2) via a bearing, the top end of the first rotating rod (41) being rotatably extended out of the top end of the drone (1), and the inner wall of the first rotating rod (41) being provided with a plurality of first sliding grooves (42) equidistantly from top to bottom along the circumferential direction; a first gear (43), the first gear (43) being sleeved on the bottom of the outer wall of the first rotating rod (41) and being locked by a top screw, the first gear (43) being located in the inner cavity of the power cavity (2); A mounting seat (410), wherein the mounting seat (410) is arranged at the top end of the first rotating rod (41); A rotating rod (411), wherein the number of the rotating rods (411) is two, and the middle portions of the outer walls of the two rotating rods (411) are rotatably arranged at the middle portions of the front and rear sides of the inner wall of the mounting seat (410) via bearings, respectively, and the outer ends of the rotating rods (411) are rotatably extended out of the outer wall of the mounting seat (410); A paddle (413), wherein the paddle (413) is arranged at the outer end of the rotating rod (411); A motor (414), wherein the motor (414) is screw-connected to the inner side of the bottom end of the inner cavity of the power cavity (2); A first connecting rod (415), the first connecting rod (415) being screw-connected to an output end of the motor (414); The third gear (416) is sleeved on the outer wall of the first connecting rod (415) and is locked by a top screw. The third gear (416) is meshed with the first gear (43).

2. The UAV vertical forced landing protection device according to claim 1, characterized in that: The power mechanism (4) comprises: A push rod (45), wherein the middle portion of the outer wall of the push rod (45) is slidably adapted to be inserted into the inner cavity of the first rotating rod (41), and the upper and lower ends of the push rod (45) are slidably extended out of the upper and lower ends of the first rotating rod (41); A first sliding block (44), the number of the first sliding blocks (44) being multiple, the multiple first sliding blocks (44) being respectively arranged on the outer wall of the push rod (45) at equal intervals along the circumferential direction, the first sliding blocks (44) being slidably adapted to be inserted into the inner cavity of the first sliding groove (42); A base (46), the base (46) being rotatably disposed on the bottom end of the push rod (45) via a bearing; a first electric telescopic rod (47), the first electric telescopic rod (47) being arranged in the inner cavity of the lifting rod (3), the top end of the first electric telescopic rod (47) being slidably extended into the inner cavity of the power cavity (2) corresponding to its position, and the bottom end of the base (46) being arranged at the top end of the first electric telescopic rod (47); A support plate (48), wherein the support plate (48) is arranged at the top end of the push rod (45); A first rack (49), the number of the first racks (49) being two, the two first racks (49) being respectively arranged at the front end on the left side of the bottom end and the rear end on the right side of the bottom end of the support plate (48), the first racks (49) being slidably embedded in the inner cavity of the mounting seat (410); The second gear (412) is sleeved on the inner side of the outer wall of the rotating rod (411) and is locked by a top screw. The two second gears (412) are respectively meshed with the two first racks (49).

3. The UAV vertical forced landing protection device according to claim 2 is characterized in that: The power mechanism (4) comprises: A signal disk (417), the signal disk (417) being sleeved on the bottom end of the outer wall of the first rotating rod (41) and locked by a top screw, the signal disk (417) being located in the inner cavity of the power cavity (2); A Hall-type rotation speed sensor (418), wherein the Hall-type rotation speed sensor (418) is arranged on the inner wall of the power chamber (2), and the position of the Hall-type rotation speed sensor (418) corresponds to the position of the signal disk (417).

4. The UAV vertical forced landing protection device according to claim 3 is characterized by: The protection mechanism (5) comprises: Second rotating rods (51), the number of the second rotating rods (51) is eight, the eight second rotating rods (51) are grouped in pairs and divided into four groups, the four groups of second rotating rods (51) are rotatably arranged at the four corners of the bottom of the drone (1) via bearings, and the two second rotating rods (51) in each group are respectively located on both sides of the lifting rod (3); A first connecting rod (52), one end of the first connecting rod (52) being fixedly sleeved on the outer wall of the second rotating rod (51); A first guide rod (53), the first guide rod (53) being arranged in the inner cavity of the first connecting rod (52); A spring (54), wherein the spring (54) is sleeved on the outer wall of the first guide rod (53), and one end of the spring (54) is clamped on the inner wall of the first connecting rod (52); A second connecting rod (55), one end of which is slidably embedded in the inner cavity of the first connecting rod (52), the other end of the spring (54) is clamped on the outer wall of the second connecting rod (55), and the other end of the second connecting rod (55) is rotatably connected to the other end of the adjacent second connecting rod (55) via a pin.

5. The UAV vertical forced landing protection device according to claim 4, characterized in that: The protection mechanism (5) further comprises: A storage plate (57), the storage plate (57) being arranged at the bottom end of the drone (1), and second slide grooves (58) being provided at four corners of the bottom end of the storage plate (57); a second guide rod (59), wherein two ends of the second guide rod (59) are respectively arranged at both sides of the inner and outer sides of the inner cavity of the second slide groove (58); A second sliding block (510), the second sliding block (510) can be slidably adapted to be inserted into the outer side of the inner cavity of the second sliding groove (58), and the second sliding block (510) can be slidably sleeved on the outer wall of the second guide rod (59); a second rack (511), the second rack (511) being arranged at the bottom end of the second sliding block (510); a fourth gear (56), the fourth gear (56) being sleeved on the bottom end of the outer wall of the second rotating rod (51) and being locked by a top screw, the fourth gear (56) being meshed with the second rack (511); A second electric telescopic rod (512), wherein the number of the second electric telescopic rods (512) is four, the four second electric telescopic rods (512) are respectively arranged at the four corners of the bottom end of the storage plate (57), and the inner middle parts of the four second racks (511) are respectively arranged at the outer ends of the four second electric telescopic rods (512).

6. The UAV vertical forced landing protection device according to claim 5, characterized in that: The protection mechanism (5) further comprises: Windshield cloths (513), the number of the windshield cloths (513) is four, one side of the four windshield cloths (513) is respectively arranged at the four corners of the inner cavity of the storage plate (57), and the other side of the four windshield cloths (513) is respectively arranged at the inner side of the second connecting rod (55) and the first connecting rod (52) connected by four groups of pins.

7. The UAV vertical forced landing protection device according to claim 6, characterized in that: The number of teeth on the second rack (511) is greater than one quarter of the number of teeth on the outer wall of the fourth gear (56).

Images