Anti-collision energy absorption structure of unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle anti-collision energy absorption structure which comprises an unmanned aerial vehicle body, one end of the unmanned aerial vehicle body is in transmission connection with a protection energy absorption part, and an anti-collision piece is arranged on the outer side of the protection energy absorption part; the protection energy absorption part comprises a transmission part arranged at one end of the unmanned aerial vehicle main body and a pop-up part arranged on the inner side of the transmission part, and the protection energy absorption part provides elastic support for the anti-collision piece through the transmission part after the unmanned aerial vehicle main body is launched, so that anti-collision protection is provided when the unmanned aerial vehicle main body flies and lands; and when the acceleration in the main axis direction is larger than or equal to 5G, the protection energy absorption part releases the ejection part through the transmission part, the ejection part ejects all the anti-collision pieces and unfolds the anti-collision pieces, and the anti-collision pieces decelerate and recover the unmanned aerial vehicle body through air resistance.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and more specifically, to an energy-absorbing anti-collision structure for an unmanned aerial vehicle. Background Art

[0002] The RY9D unmanned aerial vehicle system is a 5 kg-class tube-launched folding-wing unmanned aerial vehicle system, which consists of an unmanned aerial vehicle flight platform, a portable ground device, and a launch tube system. The portable ground device consists of a portable planning and control terminal, a portable data link device, an external battery, a charger, and a carrying device; the launch tube system consists of a launch tube and its related accessory systems. The RY9D unmanned aerial vehicle system has the convenient tube-launching and efficient loitering functions, with a maximum payload of 1 kg and an electric propulsion power system.

[0003] Tube launching refers to the process of launching the unmanned aerial vehicle in the launch tube and quickly unfolding it into a stable flight state. The tube-launching process is divided into three parts: a boost section, a separation section, and an unfolding section. In the boost section, it is necessary to ensure the launch attitude and flight speed of the unmanned aerial vehicle. In the separation section, it is necessary to ensure the reliability of the separation between the boost piston and the unmanned aerial vehicle and minimize the impact of the separation on the attitude of the unmanned aerial vehicle. In the unfolding section, it is necessary to ensure the flight stability of the aircraft during the unfolding process. Navigation flight means that the loitering unmanned aerial vehicle flies according to the instructions under satellite and inertial combined navigation.

[0004] Referring to the "Technical Specification for the Whole Machine Parachute", the unmanned aerial vehicle needs to trigger the parachute for recovery when any of the following conditions is met: vertical falling speed ≥ 6 m / s; roll angle ≥ 90° or continuous abnormal attitude; power system failure or serious structural damage; the sensor detects an uncontrollable impact acceleration (such as exceeding 5G).

[0005] In the prior art, the head of the tube-launched unmanned aerial vehicle and the electrical components are axially rigidly connected. When a collision occurs, there is no special anti-collision structure for the head of the unmanned aerial vehicle, resulting in the impact energy being directly conducted to the core components such as the main board and the battery through the mechanical structure. When the axial acceleration of the unmanned aerial vehicle body caused by the collision ≥ 5G, the rigid material cannot effectively absorb the impact, easily causing problems such as solder joint fracture and chip de-soldering. Moreover, the 5G acceleration will cause the propeller to instantaneously generate a greater lift force to maintain the attitude, and the sharp change in the motor speed may exceed its rated power range, leading to overheating and even burning, and the propeller itself may undergo plastic deformation or fracture, resulting in uneven lift distribution and increasing the risk of attitude loss of control.

[0006] Therefore, there is a need for an energy-absorbing anti-collision structure for an unmanned aerial vehicle that can protect the head of the unmanned aerial vehicle body from collision and can protect and recover the unmanned aerial vehicle when the axial acceleration of the unmanned aerial vehicle body caused by the collision ≥ 5G. Summary of the Invention

[0007] In view of the problem that the existing tube-launched UAV has an axial rigid connection between the head and electrical components, resulting in the impact energy being directly conducted to the main board, battery and other core components through the mechanical structure, damaging the UAV body, the present application provides an anti-collision energy absorption structure for UAVs.

[0008] The technical solution of the present invention is: an anti-collision energy absorption structure for UAVs, including a UAV body, one end of the UAV body is drivingly connected with a protective energy absorption part, and an anti-collision part is arranged outside the protective energy absorption part; the protective energy absorption part includes a transmission part arranged at one end of the UAV body and a pop-up part arranged inside the transmission part, which provides elastic support for the anti-collision part after the UAV body is launched through the transmission part, provides anti-collision protection during the flight and landing of the UAV body, and when the UAV body is hit, when the acceleration in the main axis direction is greater than or equal to 5G, the protective energy absorption part releases the pop-up part through the transmission part, and the pop-up part pops out and unfolds all the anti-collision parts, and the anti-collision parts decelerate and recover the UAV body by using air resistance.

[0009] Further, the UAV body includes a torso, one end of the torso is drivingly connected with a propeller, the bottom of the torso is drivingly connected with a rear wing, the top of the torso is drivingly connected with a front wing, both sides of the torso are drivingly connected with side wings, and a parachute pack is arranged inside the torso.

[0010] Further, the center of gravity of the UAV body is located on one side of the middle of the torso close to the propeller.

[0011] Further, the transmission part includes a movable block, one end of the movable block is fixed with an elastic part, the other end of the elastic part is fixed inside the torso, the other end of the movable block is fixed with a four-tail plate, a support ring is fixed inside the four-tail plate, limiting grooves are opened on the four ends of the four-tail plate far from the torso side, four groups of support blocks are fixed on the outside of the end of the torso far from the propeller, and two support blocks are in a group. A plastic part is fixed on the outside of the support ring, and the plastic part is fixedly connected with the four-tail plate.

[0012] Further, sliders are fixed on the four ends of the four-tail plate close to the torso side, and slide rods are fixed on the outside of the end of the torso far from the propeller, and the sliders are slidably clamped on the outside of the slide rods.

[0013] Further, a locking part is fixed inside the end of the torso far from the propeller, and the output end of the locking part is located inside the movable block.

[0014] Further, the anti-collision part includes an umbrella top and an umbrella skirt. The umbrella top is pushed by the pop-up part to be smooth on the surface. The umbrella skirt is folded and the umbrella skirt is located inside the sleeve. The sleeve is fixed on the outside of the torso, and the sleeve is located on the side of the four-tail plate close to the propeller.

[0015] Further, the pop-up part includes a first elastic member and a second elastic member. The sliding end of the first elastic member is slidably clamped inside the limiting groove. The sliding end of the first elastic member is located on the side of the support block away from the propeller. The fixed end of the first elastic member is fixedly connected to the inside of the side of the umbrella top close to the propeller. The fixed end of the second elastic member is fixedly connected to the inside of the side of the umbrella skirt close to the propeller. The movable end of the second elastic member is rotatably connected to a parachute cord. The other end of the parachute cord is rotatably connected to a fixing rod. The fixing rod is fixed to the outside of the torso through a connecting member.

[0016] The beneficial effects of the present invention are as follows:

[0017] (1) For an anti-collision energy absorption structure of a drone according to the present invention, the drone body is provided with a protective energy absorption part. When the head of the drone is hit during flight, the anti-collision member first contacts the collision object. It can deform when being hit, absorb the energy generated by the impact and convert it into other forms of energy, such as mechanical energy required for deformation, thereby reducing the energy transmitted to the drone body, playing a buffering role, protecting the electronic devices and mechanical structures inside the drone, and can provide protection for the drone in time at the moment of collision, avoiding the drone directly bearing the impact force.

[0018] (2) On the basis of the beneficial effect (1), when the acceleration received by the drone body axially due to the collision is greater than or equal to 5G, first, the energy absorption effect of the anti-collision member greatly reduces the possibility of damage to the key components of the drone caused by the collision. Then, the protective energy absorption part can quickly pop up the anti-collision member. At the same time, the processor controls the propulsion motor to shut down. After losing the forward driving power, due to the center of gravity position, the tail of the drone body will move towards the side close to the ground first compared to the head. After the anti-collision member is popped up, the anti-collision member opens to use air resistance for deceleration. At the same time, the propulsion motor can be restarted to drive the drone for auxiliary deceleration, and finally reach the landing standard. Description of the Drawings

[0019] The present invention will be further described below with reference to the drawings and embodiments.

[0020] Figure 1 Schematic diagram of the folded state of the drone provided by the present invention;

[0021] Figure 2 Schematic diagram of the overall structure provided by the present invention;

[0022] Figure 3 Schematic diagram of the housing structure provided by the present invention Figure 1 ;

[0023] Figure 4 Schematic diagram of the head structure of the torso provided by the present invention;

[0024] Figure 5 For Figure 4 the enlarged view at A of

[0025] Figure 6 Schematic diagram of the cross-sectional structure of the housing provided by the present invention Figure 1 ;

[0026] Figure 7 is Figure 6 an enlarged view of the F part of;

[0027] Figure 8 Schematic diagram of the cross-sectional structure of the housing provided by the present invention Figure 2 ;

[0028] Figure 9 Schematic diagram of the anti-collision member structure provided by the present invention;

[0029] Figure 10 Schematic diagram of the pop-up part structure provided by the present invention Figure 1 ;

[0030] Figure 11 Schematic diagram of the four-tail plate structure provided by the present invention;

[0031] Figure 12 is Figure 11 an enlarged view of the B part of;

[0032] Figure 13 Schematic diagram of the plastic part structure provided by the present invention;

[0033] Figure 14 Schematic diagram of the pop-up part structure provided by the present invention Figure 2 ;

[0034] Figure 15 Schematic diagram of the second elastic member structure provided by the present invention;

[0035] Figure 16 is Figure 15 an enlarged view of the B part of;

[0036] Figure 17 is Figure 15 an enlarged view of the D part of;

[0037] Figure 18 Schematic diagram of the first elastic member structure provided by the present invention;

[0038] Figure 19 Schematic diagram of the cross-section of the first elastic member provided by the present invention;

[0039] Figure 20 is Figure 19 an enlarged view of the E part of.

[0040] In the figure: 1. UAV body; 11. Trunk; 12. Front wing; 13. Rear wing; 14. Parachute pack; 15. Propeller; 16. Flank; 2. Sheath; 3. Anti-collision part; 31. Umbrella top; 32. Umbrella skirt; 4. Transmission part; 41. Movable block; 42. Four-tail plate; 43. Limit groove; 44. Slide block; 45. Support ring; 46. Slide rod; 47. Support block; 48. Plastic part; 5. Locking part; 6. Ejection part; 61. First elastic part; 611. Fixed cylinder; 612. Movable rod; 62. Second elastic part; 621. Outer cylinder; 622. Middle cylinder; 623. Inner rod; 63. Parachute rope; 64. Fixed rod. Detailed implementation manner

[0041] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the present invention in combination with the drawings and the descriptions of the embodiments or the prior art. Obviously, the following descriptions of the structures of the drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings. It should be noted here that the descriptions of these embodiments are used to help understand the present invention, but do not constitute a limitation to the present invention.

[0042] Embodiment: As Figure 1-20 shown, an anti-collision and energy-absorbing structure for a UAV includes a UAV body 1. One end of the UAV body 1 is drivingly connected to a protective energy-absorbing part, and an anti-collision part 3 is arranged outside the protective energy-absorbing part; the protective energy-absorbing part includes a transmission part 4 arranged at one end of the UAV body 1 and an ejection part 6 arranged inside the transmission part 4. It provides elastic support for the anti-collision part 3 after the UAV body 1 is launched through the transmission part 4, and provides anti-collision protection during the flight and landing of the UAV body 1. When the UAV body 1 is impacted and the acceleration in the main axis direction is greater than or equal to 5G, the protective energy-absorbing part releases the ejection part 6 through the transmission part 4, and the ejection part 6 ejects and unfolds the anti-collision part 3 completely. The anti-collision part 3 decelerates and recovers the UAV body 1 by using air resistance. The center of gravity of the UAV body 1 is located on one side of the middle of the trunk 11 close to the propeller 15.

[0043] In this embodiment, when the front wing 12, rear wing 13 and flank 16 of the UAV are impacted and cause the fuselage to swing, the processor inside the trunk 11 controls the UAV body 1 to adjust its own attitude. If it can be adjusted to the normal flight attitude, it will continue to fly. If it cannot be adjusted, the processor opens the parachute pack 14 to recover the UAV body 1;

[0044] When the head of the UAV body 1 is axially impacted, the protective energy-absorbing part performs anti-collision energy absorption or recovery according to the impact situation;

[0045] Partial parameter data of the UAV body 1: The mass is 5.5 kg, the ejection speed from the tube is less than 79.2 km / h, the cruising speed is 90 km / h, the maximum speed is 130 km / h, and the head diameter is 0.153 m. Trigger condition of the protective energy-absorbing part: It is required to meet the axial acceleration ≥ 5G (49 m / s 2 ), corresponding spring force:

[0046] F trigger = m × 5G = 5.5 kg × 49 m / s 2 ≈ 269.5 N. When the spring force reaches this threshold, the sensor inside the movable block 41 detects a signal, and the front wing 12, rear wing 13, and side wings 16 are recovered;

[0047] According to the aerodynamic formula: F 空气 = 1 / 2ρv 2 C d A

[0048] Where: ρ (air density) = 1.225 kg / m 3 (standard sea level);

[0049] v (speed) = 36.11 m / s;

[0050] C d (drag coefficient): Take a typical value C d ≈ 0.3;

[0051] A (cross-sectional area): The diameter of the cross-section of the umbrella top 31 is about 0.2 m, A ≈ 0.0184 m 2 .

[0052] Substitute into the calculation:

[0053] F 空气 = 0.5 × 1.225 × (36.11) 2 × 0.3 × 0.0314 ≈ 7.4 N

[0054] This air resistance is much lower than 270 N (the spring force threshold), accounting for only about 2.7%, and can be considered negligible.

[0055] Specifically, the UAV body 1 includes a torso 11. One end of the torso 11 is drivingly connected to a propeller 15. The bottom of the torso 11 is drivingly connected to a rear wing 13. The top of the torso 11 is drivingly connected to a front wing 12. The two sides of the torso 11 are drivingly connected to side wings 16. An umbrella pack 14 is arranged inside the torso 11.

[0056] In this embodiment, the tube-mounted folding UAV uses a portable launch tube to encapsulate a folding UAV; to meet the requirements of being loaded into the tube, the front wing 12, rear wing 13, side wings 16, and propeller 15 of the UAV body 1 have folding functions (such as Figure 1As shown in the figure, before launch, the UAV is in a folded state. After launch, the front wing 12, rear wing 13, side wing 16 and propeller 15 of the UAV body 1 are deployed (as shown in Figure 2 ). The motor is started and the UAV enters the loitering mode. The parachute pack 14 will pop out when recovering the UAV body 1 (this is the prior art and will not be elaborated here) to provide a reverse force for the UAV body 1.

[0057] Specifically, a locking member 5 is fixedly installed inside one end of the torso 11 away from the propeller 15, and the output end of the locking member 5 is located inside the movable block 41.

[0058] In this embodiment, the locking member 5 is assembled to fix the movable block 41. It can be a telescopic rod, a cylinder or an electric valve, etc., which can restrict the movement of the movable block 41 through the expansion and contraction of the output end. In this embodiment, a cylinder is taken as an example. After launch, when the UAV body 1 shoots out from the inside of the launch tube, the output end of the cylinder contracts and moves out from the inside of the movable block 41, releasing the restriction on the movable block 41, preventing the axial acceleration of the elastic member connected to the movable block 41 during launch from being greater than 5G and causing the anti-collision member 3 to pop out.

[0059] Specifically, the transmission part 4 includes a movable block 41. One end of the movable block 41 is fixed with an elastic member, and the other end of the elastic member is fixed inside the torso 11. The other end of the movable block 41 is fixed with a four-tail plate 42. A support ring 45 is fixedly installed inside the four-tail plate 42. Limiting grooves 43 are formed on the sides of the four ends of the four-tail plate 42 away from the torso 11. Four groups of support blocks 47 are fixedly installed on the outside of one end of the torso 11 away from the propeller 15, and two support blocks 47 are in a group. A plastic member 48 is fixedly installed on the outside of the support ring 45, and the plastic member 48 is fixedly connected to the four-tail plate 42. Sliders 44 are fixedly installed on the sides of the four ends of the four-tail plate 42 close to the torso 11. A sliding rod 46 is fixedly installed on the outside of one end of the torso 11 away from the propeller 15, and the slider 44 is slidably clamped on the outside of the sliding rod 46.

[0060] In this embodiment, the elastic member can be a spring, an air spring system or a leaf spring, etc. It has elasticity and can withstand a certain amount of bending or stretching, and realizes the resilience function through its own elastic deformation. In this embodiment, a spring is taken as an example. The plastic member has the ability of plastic elastic deformation. When the UAV body 1 is flying, when the head of the UAV body 1 is axially impacted and the axial acceleration of the UAV body 1 is less than 5G, the impact object contacts the anti-collision member 3, causing the anti-collision member 3 and the plastic member 48 to be indented. The anti-collision member 3 and the plastic member 48 withstand and absorb the kinetic energy brought by the impact through their own plastic deformation and bounce the impact object away through the resilience force;

[0061] If the head of the drone body 1 is subjected to an axial impact force during flight, resulting in an axial acceleration of the drone body 1 greater than or equal to 5G, the impactor causes the four-tail plate 42 to move toward the side close to the propeller 15, and the four-tail plate 42 drives the movable block 41 to move toward the side close to the propeller 15, and the movable block 41 squeezes the spring, and the movable block 41 drives the pressure sensor disposed inside the movable block to move toward the side close to the trunk 11. When the pressure sensor detects that the movable block 41 is in contact and squeezed with the trunk 11, the motor that propels the drone body 1 to fly is turned off, the propeller 15 stops working, and the parachute bag 14 does not pop out. The front wing 12, rear wing 13, and side wing 16 of the human-machine body 1 move to a folded position. Since the center of gravity of the drone body 1 is located on the side of the trunk 11 close to the propeller 15, the tail of the drone body 1 will move closer to the ground than the head after losing the forward propulsion power, and the four tail plates 42 move closer to the propeller 15. During this process, the slider 44 moves along the outside of the slide rod 46 to limit the moving direction of the four ends of the four tail plates 42. When the movable block 41 contacts the inner wall of the trunk 11 on the side close to the propeller 15, the elastic member 61 moves out from the inside of the limiting groove 43 to release the restriction on the elastic member 61.

[0062] Specifically, the anti-collision component 3 includes an umbrella top 31 and an umbrella skirt 32. The umbrella top 31 is supported by the pop-up part 6 until the surface is smooth. The umbrella skirt 32 is folded and located on the inner side of the shell 2. The shell 2 is fixed to the outer side of the trunk 11, and the shell 2 is located on the side of the four-tail plate 42 close to the propeller 15.

[0063] In this embodiment, the anti-collision member 3 has a smooth surface and a certain degree of elasticity. The anti-collision member 3 is divided into an umbrella top 31 and an umbrella skirt 32. The umbrella top 31 is held open by the plastic member 48 and the four tail plates 42, and the umbrella skirt 32 is folded and placed inside the shell 2.

[0064] Specifically, the pop-up part 6 includes an elastic member 61 and an elastic member 62. The sliding end of the elastic member 61 is slidably engaged with the inner side of the limiting groove 43. The sliding end of the elastic member 61 is located on the side of the support block 47 away from the propeller 15. The fixed end of the elastic member 61 is fixedly connected to the inside of the side of the umbrella top 31 close to the propeller 15. The fixed end of the elastic member 62 is fixedly connected to the inside of the side of the umbrella skirt 32 close to the propeller 15. The movable end of the elastic member 62 is rotatably connected to the umbrella rope 63. The other end of the umbrella rope 63 is rotatably connected to the fixing rod 64. The fixing rod 64 is fixed to the outside of the trunk 11 through a connecting component.

[0065] In this embodiment, the first elastic member 61 can be arranged in an implementation manner as shown in FIGS. (18 - 20). It includes four fixed cylinders 611 and four movable rods 612. The middle part of the outer side of each fixed cylinder 611 is fixed to the inner side of the umbrella top 31 of the anti - collision member 3. Each movable rod 612 is slidably connected to the inner sides of two adjacent fixed cylinders 611. The middle part of the movable rod 612 is slidably clamped inside the limiting groove 43, and the middle part of the movable rod 612 contacts the support block 47;

[0066] The second elastic member 62 can be arranged in an implementation manner as shown in FIGS. (15 - 17). It includes an outer cylinder 621, a middle cylinder 622 and an inner rod 623. The middle part of the outer side of each outer cylinder 621 is fixed to the inner side of the umbrella skirt 32 of the anti - collision member 3. Two middle cylinders 622 are slidably clamped inside each outer cylinder 621. One inner rod 623 is slidably clamped inside each middle cylinder 622. One end of the adjacent two inner rods 623 located outside the middle cylinder 622 is rotatably connected to the umbrella rope 63 through a connecting member;

[0067] After the umbrella skirt 32 is opened, both ends of the movable rod 612 will not move out of the fixed cylinder 611 due to the effect of the umbrella top 31. Since one end of the middle cylinder 622 and the inner rod 623 is designed as a sphere, they will not move out of the inner sides of the outer cylinder 621 and the middle cylinder 622 either;

[0068] When the side of the movable block 41 close to the propeller 15 contacts the inner wall of the torso 11, the movable rod 612 moves out of the inner side of the limiting groove 43. The movable rod 612 and the fixed rod 64 rebound from bending to straight due to their own elastic deformation, thereby driving the anti - collision member 3 to open. The opening of the umbrella top 31 drives the umbrella skirt 32 to move out of the inner side of the housing 2. The umbrella skirt 32 drives the outer cylinder 621 to move out of the inner side of the housing 2. The outer cylinder 621, the middle cylinder 622 and the inner rod 623 rebound from bending to straight due to their own elastic deformation. The middle cylinder 622 slides inside the outer cylinder 621, and the inner rod 623 slides inside the middle cylinder 622 to open the umbrella skirt 32, and the umbrella skirt 32 will accelerate to open due to air resistance;

[0069] The umbrella skirt 32 decelerates the UAV main body 1 under the action of air resistance. If the motor for propelling the UAV flight inside the torso 11 can still work, it will continue to propel to assist the anti - collision member 3 to decelerate the UAV main body 1, so that the UAV main body 1 meets the landing standard when landing on the ground.

[0070] Working principle: The initial state is as Figures 2-20As shown, before launch, the UAV is in a folded state. After launch, the front wing 12, rear wing 13, side wing 16 and propeller 15 of the UAV body 1 are deployed. The output end of the cylinder contracts and moves out from the inside of the movable block 41, releasing the restriction on the movable block 41. During flight, when the front wing 12, rear wing 13 and side wing 16 of the UAV are impacted and cause the fuselage to swing, the UAV body 1 adjusts its own attitude. If it can be adjusted to the normal flight attitude, it will continue to fly. If it cannot be adjusted, the UAV body 1 will be recovered by the parachute pack 14;

[0071] When the head of the UAV body 1 is axially impacted, the anti-collision energy absorption or recovery is carried out by the protective energy absorption part according to the impact situation;

[0072] When the head of the UAV body 1 is axially impacted and the front wing 12, rear wing 13 or side wing 16 is simultaneously impacted, when the axial acceleration of the UAV body 1 caused by the axial impact on the head is greater than or equal to 5G, the UAV body 1 is recovered by the protective energy absorption part, and the processor does not adjust the flight attitude. When the axial acceleration of the UAV body 1 caused by the axial impact on the head is less than 5G, the processor first adjusts the attitude. When the flight attitude cannot be restored, the parachute pack 14 is opened for recovery.

[0073] Finally, it should be noted that the above are only the preferred embodiments of the present invention and are not used to limit the protection scope of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An energy-absorbing structure for a drone to resist collision, comprising a drone main body (1), characterized in that: One end of the UAV body (1) is drivingly connected to a protective energy-absorbing part, and an anti-collision member (3) is arranged on the outer side of the protective energy-absorbing part; The protective energy-absorbing part includes a transmission part (4) arranged at one end of the UAV body (1) and a pop-up part (6) arranged inside the transmission part (4). It provides elastic support for the anti-collision member (3) through the transmission part (4) after the UAV body (1) is launched, so as to provide anti-collision protection during the flight and landing of the UAV body (1). When the acceleration in the main axis direction of the UAV body (1) caused by impact is greater than or equal to 5G, the protective energy-absorbing part releases the pop-up part (6) through the transmission part (4), and the pop-up part (6) pops out and unfolds the anti-collision member (3) completely. The anti-collision member (3) decelerates and recovers the UAV body (1) by using air resistance.

2. The anti-collision energy-absorbing structure of the drone according to claim 1, characterized in that: The UAV body (1) includes a torso (11). One end of the torso (11) is drivingly connected to a propeller (15), the bottom of the torso (11) is drivingly connected to a rear wing (13), the top of the torso (11) is drivingly connected to a front wing (12), both sides of the torso (11) are drivingly connected to side wings (16), and a parachute pack (14) is arranged inside the torso (11).

3. The anti-collision energy-absorbing structure of the drone according to claim 2, characterized in that: The center of gravity of the UAV body (1) is located on one side of the middle of the torso (11) close to the propeller (15).

4. The anti-collision energy-absorbing structure of the drone according to claim 2, characterized in that: The transmission part (4) includes a movable block (41). One end of the movable block (41) is fixed with an elastic member, the other end of the elastic member is fixed inside the torso (11). The other end of the movable block (41) is fixed with a four-tail plate (42). A support ring (45) is fixed inside the four-tail plate (42). Limit slots (43) are opened on the outer sides of the four ends of the four-tail plate (42) away from the torso (11). Four groups of support blocks (47) are fixed on the outer side of one end of the torso (11) away from the propeller (15), and two support blocks (47) are in a group. A plastic member (48) is fixed on the outer side of the support ring (45), and the plastic member (48) is fixedly connected to the four-tail plate (42).

5. The anti-collision energy-absorbing structure of the drone according to claim 4, characterized in that: Sliders (44) are fixed on the inner sides of the four ends of the four-tail plate (42) close to the torso (11). Slide rods (46) are fixed on the outer side of one end of the torso (11) away from the propeller (15), and the sliders (44) are slidably clamped on the outer sides of the slide rods (46).

6. The anti-collision energy-absorbing structure of the drone according to claim 4, characterized in that: A locking member (5) is fixed inside one end of the torso (11) away from the propeller (15), and the output end of the locking member (5) is located inside the movable block (41).

7. The anti-collision energy-absorbing structure of the drone according to claim 6, characterized in that: The anti-collision member (3) includes an umbrella top (31) and an umbrella skirt (32). The umbrella top (31) is propped up by the pop-up part (6) to be smooth on the surface. The umbrella skirt (32) is folded and the umbrella skirt (32) is located inside the housing (2). The housing (2) is fixed on the outer side of the torso (11), and the housing (2) is located on the side of the four-tail plate (42) close to the propeller (15).

8. The anti-collision energy-absorbing structure of the drone according to claim 3, wherein: The pop-up part (6) includes a first elastic member (61) and a second elastic member (62). The sliding end of the first elastic member (61) is slidably clamped inside the limiting groove (43). The sliding end of the first elastic member (61) is located on the side of the support block (47) away from the propeller (15). The fixed end of the first elastic member (61) is fixedly connected to the inside of the side of the umbrella top (31) close to the propeller (15). The fixed end of the second elastic member (62) is fixedly connected to the inside of the side of the umbrella skirt (32) close to the propeller (15). The movable end of the second elastic member (62) is rotatably connected to an umbrella rope (63). The other end of the umbrella rope (63) is rotatably connected to a fixing rod (64). The fixing rod (64) is fixed to the outside of the torso (11) through a connecting component.

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