Propeller retracting and releasing device for anti-falling unmanned aerial vehicle

Abstract

The invention discloses a propeller retracting and releasing device for an anti-falling unmanned aerial vehicle, and particularly relates to the technical field of unmanned aerial vehicles, the propeller retracting and releasing device comprises a fuselage, an elastic parachute structure is arranged at the upper end of the fuselage, and the lower end of the fuselage and the lower end of a battery box are jointly and fixedly connected with a buffer structure; the four corners of the inner surface of the fuselage are fixedly connected with annularly-distributed propeller folding and unfolding structures through bolts correspondingly, and rotor wing structures are arranged at the ends, away from the fuselage, of the multiple propeller folding and unfolding structures correspondingly. According to the propeller folding and unfolding device for the anti-falling unmanned aerial vehicle, the spiral arm is folded through the propeller folding and unfolding structure, the posture adjusting assembly is unfolded in the folding process through cooperation of the propeller folding and unfolding structure and the spiral arm, and the falling posture and speed are subjected to auxiliary adjustment through the posture adjusting assembly; and meanwhile, the falling speed of the unmanned aerial vehicle is further reduced through the action of the parachute structure, and the probability that parts are damaged due to high-altitude falling is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a propeller retracting and deploying device for an anti-falling unmanned aerial vehicle. Background Art

[0002] With the rapid development of drone technology, drones have been widely used in many fields such as aerial photography, agricultural plant protection, logistics distribution, and environmental monitoring. In these application scenarios, the flight safety and stability of drones have become the focus of research and development and users. In particular, multi-rotor drones, due to their unique flight principles, require multiple propellers to provide lift to keep the drone hovering and moving. However, these exposed propellers are not only easily damaged when the drone falls, but may also cause damage to the surrounding environment and personnel.

[0003] Currently, in order to improve the safety of drones, researchers have developed a variety of propeller protection and retraction devices, which reduce storage space by changing the position of the propellers and avoid harm to personnel during ground operations.

[0004] Although existing technologies have improved the safety of drones to a certain extent, there are still some defects and shortcomings. First, many propeller retraction devices cannot retract the propellers into a safe position and cannot provide adequate protection for the propellers when the drone falls. Secondly, some protective devices cannot effectively adjust the posture of the drone during the fall, resulting in the drone still facing a greater risk of damage when it falls. Finally, the existing buffer devices provide limited buffering effects when the impact force of the fall is large, and cannot fully protect the key components of the drone, especially for high-speed falls. Existing technologies still find it difficult to meet safety requirements. Summary of the invention

[0005] The main purpose of the present invention is to provide a propeller retracting and deploying device for preventing a UAV from falling, which can effectively solve the problems that the existing device cannot adjust its posture during a fall and provides insufficient buffering to protect the propeller and the UAV.

[0006] To achieve the above object, the technical solution adopted by the present invention is:

[0007] A propeller retracting and extending device for an anti-falling drone comprises a fuselage, wherein a parachute structure is arranged at the upper end of the fuselage, a battery box is fixedly connected to the lower end of the fuselage, a buffer structure is fixedly connected to the lower end of the fuselage and the lower end of the battery box, and propeller retracting and extending structures distributed in an annular manner are fixedly connected to the four corners of the inner surface of the fuselage by bolts, and a rotor structure is arranged at one end of a plurality of the propeller retracting and extending structures away from the fuselage.

[0008] Preferably, the propeller retracting and extending structure includes an L-shaped base fixedly connected to the inner surface of the fuselage by bolts, a rotating seat is fixedly connected to the middle of an end of the vertical portion of the L-shaped base away from the fuselage, an electric telescopic rod is rotatably connected to the inner surface of the rotating seat, an end of the electric telescopic rod away from the rotating seat is rotatably connected to the rotor structure, an end of the horizontal portion of the L-shaped base away from the fuselage is rotatably connected to the rotor structure, and an L-shaped contact rod is fixedly connected to the upper end of the horizontal portion of the L-shaped base.

[0009] Preferably, the rotor structure includes a swing arm rotatably connected to the horizontal part of the L-shaped base, a drive motor is fixedly installed on the side of the upper end of the swing arm away from the L-shaped base by bolts, the output end of the drive motor is fixedly connected to the propeller component by a connecting shaft, and an attitude adjustment component is provided on the side of the lower end of the swing arm close to the L-shaped base.

[0010] Preferably, the attitude adjustment assembly includes a flap rotatably connected to the inner surface of the swing arm, a folding wing symmetrically fixedly connected to the inner surface of the swing arm is provided on one side of the flap close to the swing arm, and a plurality of oblique guide holes are provided at one end of the flap away from the swing arm, and the inner hole height of the guide hole is lower than the outer hole height when the swing arm is in a vertical state.

[0011] Preferably, the buffer structure includes support legs symmetrically distributed on the left and right and fixedly connected to the lower end of the fuselage, the inner surfaces of the two support legs are provided with buffer components, and the ends of the two support legs close to each other are commonly fixedly connected with an airbag adhered to the lower end of the battery box.

[0012] Preferably, a U-shaped cavity connected to the buffer assembly is formed on the inner surface of the support leg, a connecting hole connected to the inner cavity of the airbag is formed on the side of the U-shaped cavity close to the airbag, and blocks are provided at the junction of the vertical part and the horizontal part of the U-shaped cavity and at the connection between the vertical part and the buffer assembly.

[0013] Preferably, the buffer assembly includes an installation box 2 fixedly connected to the lower end of the supporting leg, the inner surface of the installation box 2 is slidably connected to an elastic pad, the upper end of the elastic pad is symmetrically fixedly connected to a T-shaped connecting block slidably connected to the adjacent U-shaped cavity vertical part, the T-shaped connecting block slides in the U-shaped cavity vertical part between two adjacent groups of blocks, the upper end of the T-shaped connecting block is fixedly connected to a compression spring slidably connected to the inner surface of the U-shaped cavity vertical part, and the outer surface of the compression spring is covered with a rubber layer.

[0014] Preferably, the elastic parachute structure includes an installation box one fixedly connected to the upper end of the fuselage, the upper inner surface of the installation box one is connected to a shielding door which is symmetrically rotatable to the left and right, the ends of the two shielding doors close to each other are symmetrically fixedly connected to electromagnets, the magnetic poles of two adjacent electromagnets are opposite, and the bottom wall of the inner surface of the installation box one is fixedly connected to the elastic parachute assembly.

[0015] Preferably, the parachute assembly includes a cable fixedly connected to the bottom wall of an inner surface of a mounting box, the upper end of the cable is fixedly connected to a limiting block, the lower end of the limiting block and the outer surface of the cable are fixedly connected with an arc-shaped cushion, the lower end of the arc-shaped cushion is fixedly connected with a counterweight block slidably connected to the cable, the inner surface of the counterweight block is slidably connected with a plurality of L-shaped rods fixedly connected to the outer surface of the limiting block in an annular distribution, the upper ends of several of the L-shaped rods are rotatably connected to pressure rods, and the middle parts of several of the pressure rods are rotatably connected to support seats fixedly connected to the inner walls of adjacent counterweight blocks.

[0016] Preferably, the parachute assembly also includes a plurality of connecting ropes fixedly connected to the upper end of the counterweight block, the other ends of the plurality of connecting ropes are commonly and fixedly connected to a parachute bag, the parachute bag is located between a plurality of pressure rods and the limit blocks and is tightly attached to the lower part of the pressure rods, the pressure rods are in an inclined state in the initial state and the distance between the plurality of pressure rods is smaller than the outer diameter of the parachute bag shell.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. The present invention retracts the swivel arm through the propeller retracting and extending structure, and unfolds the attitude adjustment component during the retracting process through the cooperation of the propeller retracting and extending structure and the swivel arm. The attitude adjustment component assists in adjusting the falling attitude and speed to avoid a large impact after landing due to excessive falling speed. At the same time, the parachute structure is opened by controlling the fuselage to further reduce the falling speed of the UAV through the action of the parachute structure, thereby reducing the damage to components caused by falling from a high altitude, reducing the subsequent maintenance and repair costs, and reducing the probability of propeller damage.

[0019] 2. When the UAV falls due to stall or failure, the present invention uses the electric telescopic rod to pull the swing arm from a horizontal state to a vertical state through the cooperation between the electric telescopic rod and the swing arm, and drives the attitude adjustment component to unfold through the cooperation between the L-shaped contact rod and the attitude adjustment component. The diversion effect of the attitude adjustment component is used to adjust the falling attitude of the UAV, so that the buffer structure is at the bottom, and the effect of the folding wings and the diversion holes further increases the resistance, slows down the falling speed, and reduces the probability of damage to the UAV and the propeller.

[0020] 3. The present invention optimizes the fall protection mechanism of the drone. Specifically, through the cooperation of the buffer assembly installed at the bottom of the drone and the supporting legs, during the fall, part of the impact force is absorbed by the elastic pad, and further the cooperation of the T-shaped connecting block and the U-shaped cavity causes the airbag to be converted from a deflated state to a saturated state. The air accumulated inside the airbag provides protection for the battery box, thereby further reducing the impact force when the drone lands, avoiding the stability of the battery in the battery box being affected by falling from a height or battery damage caused by the impact of foreign objects.

[0021] 4. The present invention adds an emergency buffer system through the parachute structure. When the UAV loses control or falls due to a serious malfunction, the shielding door will open automatically, and the falling speed will be slowed down by the resistance of the released parachute assembly. The parachute bag will be ejected by the cooperation of the cable, arc-shaped cushion and counterweight, and its deployment is promoted by the action of the parachute bag and the connecting rope. The action of the parachute bag increases the resistance of the UAV to fall, slows down the descent speed, and ensures that the UAV can land safely. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0023] Figure 2 It is a bottom view schematic diagram of the overall structure of the present invention;

[0024] Figure 3 It is a structural schematic diagram of the rotor structure of the present invention;

[0025] Figure 4 It is a structural schematic diagram of the propeller retracting and extending structure of the present invention;

[0026] Figure 5 It is a schematic diagram of the normal structure of the posture adjustment component of the present invention;

[0027] Figure 6 It is a schematic diagram of the posture adjustment assembly of the present invention in a folded state;

[0028] Figure 7 It is a structural schematic diagram of the buffer structure of the present invention;

[0029] Figure 8 is a schematic cross-sectional structure diagram of the buffer structure of the present invention;

[0030] Fig. 9 It is a structural schematic diagram of the elastic parachute structure of the present invention;

[0031] Fig.10 It is a schematic structural diagram of the parachute assembly of the present invention.

[0032] In the figure: 1, fuselage; 2, rotor structure; 21, swing arm; 22, propeller component; 23, drive motor; 24, attitude adjustment component; 241, flap; 242, folding wing; 243, diversion hole; 3, parachute structure; 31, installation box 1; 32, shielding door; 33, electromagnet; 34, parachute component; 341, cable; 342, counterweight; 343, arc cushion; 344, limit block; 345, L-shaped rod; 346, support Seat; 347, pressure rod; 348, connecting rope; 349, parachute bag; 4, buffer structure; 41, support leg; 411, U-shaped cavity; 412, connecting hole; 42, buffer assembly; 421, installation box 2; 422, elastic pad; 423, T-shaped connecting block; 424, compression spring; 43, airbag; 5, propeller retracting and extending structure; 51, L-shaped base; 52, L-shaped contact rod; 53, rotating seat; 54, electric telescopic rod; 6, battery box. DETAILED DESCRIPTION

[0033] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further explained below in conjunction with specific implementation methods.

[0034] Embodiment 1, as Figure 1 and Figure 2 As shown, a propeller retracting and extending device for anti-falling UAV comprises a fuselage 1, a parachute structure 3 is arranged on the upper end of the fuselage 1, a battery box 6 is fixedly connected to the lower end of the fuselage 1, a buffer structure 4 is fixedly connected to the lower end of the fuselage 1 and the lower end of the battery box 6, and propeller retracting and extending structures 5 distributed in an annular manner are fixedly connected to the four corners of the inner surface of the fuselage 1 by bolts, and a rotor structure 2 is arranged on the end of each of the propeller retracting and extending structures 5 away from the fuselage 1.

[0035] It should be noted that the above-mentioned fuselage 1 is a conventional UAV base, which contains a control module and an acceleration sensor inside, and can control the movement of the rotor structure 2 and the propeller retractable structure 5. This structure has been widely used in the prior art. In the present invention, it is only used to realize the function of controlling the movement of the rotor structure 2 and the propeller retractable structure 5, and its internal structure, operating principle, wiring, and control method will not be described in detail.

[0036] Further, in order to realize the basic flight function and cooperate with the propeller retracting structure 5 to retract the propeller, refer to Figure 3 and Figure 4 The rotor structure 2 includes a swing arm 21 rotatably connected to the horizontal part of the L-shaped base 51, a driving motor 23 is fixedly installed by bolts on the side of the upper end of the swing arm 21 away from the L-shaped base 51, and the output end of the driving motor 23 is fixedly connected to the propeller component 22 through a connecting shaft, and an attitude adjustment component 24 is provided on the side of the lower end of the swing arm 21 close to the L-shaped base 51.

[0037] During the operation of this embodiment, when the drone falls, the propeller retracting and extending structure 5 is used to retract the swing arm 21, and the attitude adjustment component 24 is deployed during the retraction process through the cooperation of the propeller retracting and extending structure 5 and the swing arm 21. The attitude adjustment component 24 is used to assist in adjusting the falling attitude and speed to avoid a large impact after landing due to excessive falling speed. At the same time, the fuselage 1 is used to control the parachute structure 3 to open, and the parachute structure 3 is used to further reduce the falling speed of the drone, thereby reducing the damage to components caused by falling from a high altitude, reducing subsequent maintenance and repair costs, and reducing the probability of propeller damage.

[0038] Embodiment 2. Based on embodiment 1, this embodiment uses the electric telescopic rod 54 to cooperate with the swing arm 21. When the UAV falls due to stall or failure, the swing arm 21 is pulled from a horizontal state to a vertical state by the electric telescopic rod 54. The attitude adjustment component 24 is driven to unfold by the cooperation of the L-shaped contact rod 52 and the attitude adjustment component 24. The diversion effect of the attitude adjustment component 24 is used to adjust the falling attitude of the UAV, so that the buffer structure 4 is at the bottom, and the resistance is further increased by the action of the folding wing 242 and the diversion hole 243, thereby slowing down the falling speed and reducing the probability of damage to the UAV and the propeller.

[0039] Specifically, to achieve the recovery of the rotor, refer to Figure 4 The propeller retracting and extending structure 5 includes an L-shaped base 51 fixedly connected to the inner surface of the fuselage 1 by bolts, a rotating seat 53 is fixedly connected to the middle of the end of the vertical part of the L-shaped base 51 away from the fuselage 1, an electric telescopic rod 54 is rotatably connected to the inner surface of the rotating seat 53, the end of the electric telescopic rod 54 away from the rotating seat 53 is rotatably connected to the rotor structure 2, the end of the horizontal part of the L-shaped base 51 away from the fuselage 1 is rotatably connected to the rotor structure 2, and an L-shaped contact rod 52 is fixedly connected to the upper end of the horizontal part of the L-shaped base 51.

[0040] During the contraction of the electric telescopic rod 54, the swing arm 21 will be driven to change from a horizontal state to a vertical state. At this time, the drive motor 23 and the propeller component 22 will be folded to the upper part of the fuselage 1, and the buffer structure 4 will be kept at the bottom under the action of the attitude adjustment component 24 and the parachute structure 3, so as to prevent the propeller from being subjected to a large impact after falling and causing additional damage due to falling to the ground and rolling.

[0041] Further, to adjust the falling posture of the drone, refer to Figure 5 and Figure 6 The attitude adjustment component 24 includes a flap 241 rotatably connected to the inner surface of the swing arm 21, and a folding wing 242 fixedly connected to the inner surface of the swing arm 21 is symmetrically fixedly connected to the side of the flap 241 close to the swing arm 21. A plurality of oblique guide holes 243 are opened at the end of the flap 241 away from the swing arm 21. The inner hole height of the guide hole 243 is lower than the outer hole height when the swing arm 21 is in the vertical state.

[0042] When the swing arm 21 is in a vertical state, air enters from below the flap 241 and flows upward due to the guiding effect of the folded wing 242. Due to the effect of the guide hole 243, the air circulation is not smooth, which can provide a larger upward resistance for the UAV, thereby slowing down the descent speed of the UAV. In addition, through the resistance on all sides, the falling posture of the UAV can be adjusted in cooperation with the parachute structure 3, and the buffer structure 4 can be kept in the lowest posture for falling, further reducing the probability of damage to the propeller.

[0043] Embodiment 3. This embodiment further optimizes the fall protection mechanism of the drone on the basis of embodiment 2. Specifically, through the cooperation of the buffer assembly 42 installed at the bottom of the drone and the support leg 41, during the fall, part of the impact force is absorbed by the elastic pad 422, and further through the cooperation of the T-shaped connecting block 423 and the U-shaped cavity 411, the airbag 43 is caused to be converted from a deflated state to a saturated state, and the air accumulated inside the airbag 43 is used to provide protection for the battery box 6, thereby further reducing the impact force when the drone lands, avoiding the stability of the battery in the battery box 6 due to falling from a height or battery damage due to impact from foreign objects.

[0044] Specifically, to provide buffering for the battery, refer to Figure 7 The buffer structure 4 includes support legs 41 symmetrically distributed on the left and right and fixedly connected to the lower end of the fuselage 1. The inner surfaces of the two support legs 41 are provided with buffer components 42. The ends of the two support legs 41 close to each other are commonly fixedly connected with an airbag 43 pasted on the lower end of the battery box 6.

[0045] Further, in order to realize the inflating of the airbag 43 with the buffer assembly 42, refer to Figure 8 A U-shaped cavity 411 connected to the buffer assembly 42 is formed on the inner surface of the support leg 41, a connecting hole 412 connected to the inner cavity of the airbag 43 is formed on the side of the U-shaped cavity 411 close to the airbag 43, and blocks are provided at the junction of the vertical part and the horizontal part of the U-shaped cavity 411 and at the connection between the vertical part and the buffer assembly 42.

[0046] Further, in order to absorb the impact force and cooperate with the U-shaped cavity 411 to inflate the airbag 43, refer to Figure 8 The buffer assembly 42 includes an installation box 421 fixedly connected to the lower end of the support leg 41, and an elastic pad 422 is slidably connected to the inner surface of the installation box 421. The upper end of the elastic pad 422 is symmetrically fixedly connected to a T-shaped connecting block 423 slidably connected to the vertical part of the adjacent U-shaped cavity 411. The T-shaped connecting block 423 slides in the vertical part of the U-shaped cavity 411 between the two adjacent groups of blocks. The upper end of the T-shaped connecting block 423 is fixedly connected to a compression spring 424 slidably connected to the inner surface of the vertical part of the U-shaped cavity 411, and the outer surface of the compression spring 424 is covered with a rubber layer.

[0047] After contacting the ground, the elastic pad 422 absorbs the impact and feeds it back to the compression spring 424. At the same time, the T-shaped connecting block 423 slides upward in the U-shaped cavity 411. The air in the U-shaped cavity 411 is pressed into the airbag 43 through the connecting hole 412 by the T-shaped connecting block 423, so that the airbag 43 is in a saturated state, avoiding external impact on the battery box 6 and the battery therein, reducing additional damage.

[0048] Embodiment 4. Based on embodiment 3, this embodiment adds an emergency buffer system through the parachute structure 3. When the drone loses control or a serious malfunction occurs and falls, the shielding door 32 will automatically open, and the falling speed will be slowed down by the resistance of the released parachute assembly 34. The parachute bag 349 is ejected by the cooperation of the cable 341, the arc-shaped cushion 343 and the counterweight block 342, and its deployment is promoted by the action of the parachute bag 349 and the connecting rope 348. The action of the parachute bag 349 increases the resistance of the drone to fall, slows down the descent speed, and ensures that the drone can land safely.

[0049] Specifically, to realize the automatic release of the parachute assembly 34, refer to Fig. 9 The parachute structure 3 includes a mounting box 31 fixedly connected to the upper end of the fuselage 1, and a shielding door 32 is symmetrically connected to the upper inner surface of the mounting box 31 for rotation. The two shielding doors 32 are symmetrically fixedly connected to the ends close to each other with electromagnets 33, and the magnetic poles of the two adjacent electromagnets 33 are opposite. The bottom wall of the inner surface of the mounting box 31 is fixedly connected to a parachute assembly 34.

[0050] The electromagnet 33 is controlled by a module in the fuselage 1. When the acceleration sensor in the fuselage 1 detects a rapid fall, the electromagnet 33 is controlled to separate, thereby opening the shielding door 32. The electromagnet 33 is a conventional electromagnetic part, which has magnetism when powered on and has no magnetism when powered off. It is a conventional and mature device. In the present invention, it is only used to realize the stall opening function, and its specific principle, structure and control method are not displayed and explained.

[0051] Further, to realize automatic release of the parachute bag 349 after release, refer to Fig.10 The parachute assembly 34 includes a cable 341 fixedly connected to the bottom wall of the inner surface of the installation box 31, the upper end of the cable 341 is fixedly connected to a limiting block 344, the lower end of the limiting block 344 and the outer surface of the cable 341 are fixedly connected with an arc-shaped cushion 343, the lower end of the arc-shaped cushion 343 is fixedly connected with a counterweight block 342 slidably connected to the cable 341, the inner surface of the counterweight block 342 is annularly distributed and slidably connected with a plurality of L-shaped rods 345 fixedly connected to the outer surface of the limiting block 344, the upper ends of the plurality of L-shaped rods 345 are rotatably connected with pressure rods 347, and the middle parts of the plurality of pressure rods 347 are rotatably connected with support seats 346 fixedly connected to the inner walls of adjacent counterweight blocks 342.

[0052] Further, to achieve rapid deployment of the parachute bag 349, refer to Fig.10 The parachute assembly 34 also includes a plurality of connecting ropes 348 fixedly connected to the upper end of the counterweight block 342. The other ends of the plurality of connecting ropes 348 are commonly and fixedly connected to a parachute bag 349. The parachute bag 349 is located between the plurality of pressure rods 347 and the limit block 344 and is tightly attached to the lower part of the pressure rod 347. The pressure rod 347 is in an inclined state in the initial state and the distance between the plurality of pressure rods 347 is smaller than the outer diameter of the parachute bag 349 shell.

[0053] When falling, the shielding door 32 opens, and the counterweight block 342 will detach from the installation box 31 under the action of gravity until the cable 341 reaches the maximum length. At this time, the counterweight block 342 continues to move upward and folds the arc-shaped cushion 343, while driving the limit block 344 to move downward relative to the counterweight block 342. At this time, the L-shaped rod 345 slides downward along the inner wall of the counterweight block 342, and drives the pressure rod 347 to rotate around the support seat 346. The pressure rod 347 is converted from an inclined state to a horizontal state and separated from the upper part of the parachute bag 349. At this time, the parachute bag 349 will detach from the inner cavity of the counterweight block 342 under the action of gravity, and will be unfolded due to the traction of the connecting rope 348, providing a buffer for the counterweight block 342 and the fuselage 1 to which the counterweight block 342 is connected via the cable 341 and the installation box 31.

[0054] The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments. The above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention to be protected. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A propeller retracting and deploying device for an anti-fall UAV, comprising a fuselage (1), characterized in that: The upper end of the fuselage (1) is provided with a parachute structure (3), the lower end of the fuselage (1) is fixedly connected to a battery box (6), the lower end of the fuselage (1) and the lower end of the battery box (6) are jointly fixedly connected to a buffer structure (4), the four corners of the inner surface of the fuselage (1) are fixedly connected to annularly distributed propeller retractable structures (5) by bolts, and a plurality of propeller retractable structures (5) are provided with a rotor structure (2) at one end away from the fuselage (1).

2. The propeller retracting and deploying device for an anti-falling UAV according to claim 1, characterized in that: The propeller retracting and extending structure (5) comprises an L-shaped base (51) fixedly connected to the inner surface of the fuselage (1) by bolts; a rotating seat (53) is fixedly connected to the middle of one end of the vertical portion of the L-shaped base (51) away from the fuselage (1); an electric telescopic rod (54) is rotatably connected to the inner surface of the rotating seat (53); one end of the electric telescopic rod (54) away from the rotating seat (53) is rotatably connected to the rotor structure (2); one end of the horizontal portion of the L-shaped base (51) away from the fuselage (1) is rotatably connected to the rotor structure (2); and an L-shaped contact rod (52) is fixedly connected to the upper end of the horizontal portion of the L-shaped base (51).

3. The propeller retracting and deploying device for an anti-falling UAV according to claim 2 is characterized in that: The rotor structure (2) comprises a swing arm (21) rotatably connected to the horizontal part of the L-shaped base (51); a drive motor (23) is fixedly mounted on the upper end of the swing arm (21) away from the L-shaped base (51) via bolts; an output end of the drive motor (23) is fixedly connected to a propeller component (22) via a connecting shaft; and a posture adjustment component (24) is provided on the lower end of the swing arm (21) close to the L-shaped base (51).

4. The propeller retracting and deploying device for an anti-falling UAV according to claim 3 is characterized in that: The attitude adjustment component (24) comprises a flap (241) rotatably connected to the inner surface of the swing arm (21); a folding wing (242) fixedly connected to the inner surface of the swing arm (21) is symmetrically fixedly connected to one side of the flap (241) close to the swing arm (21); a plurality of oblique guide holes (243) are formed at one end of the flap (241) away from the swing arm (21); and the inner hole height of the guide hole (243) is lower than the outer hole height when the swing arm (21) is in a vertical state.

5. The propeller retracting and deploying device for anti-falling UAV according to claim 1, characterized in that: The buffer structure (4) comprises support legs (41) symmetrically distributed on the left and right and fixedly connected to the lower end of the fuselage (1), the inner surfaces of the two support legs (41) are each provided with a buffer assembly (42), and the ends of the two support legs (41) close to each other are commonly fixedly connected to an air bag (43) adhered to the lower end of the battery box (6).

6. The propeller retracting and deploying device for an anti-falling UAV according to claim 5, characterized in that: The inner surface of the support leg (41) is provided with a U-shaped cavity (411) connected to the buffer assembly (42); a connecting hole (412) connected to the inner cavity of the airbag (43) is provided on a side of the U-shaped cavity (411) close to the airbag (43); and a block is provided at the junction of the vertical part and the horizontal part of the U-shaped cavity (411) and at the connection between the vertical part and the buffer assembly (42).

7. The propeller retracting and deploying device for an anti-falling UAV according to claim 6, characterized in that: The buffer assembly (42) comprises a second installation box (421) fixedly connected to the lower end of the support leg (41); an elastic pad (422) is slidably connected to the inner surface of the second installation box (421); a T-shaped connecting block (423) slidably connected to the vertical part of the adjacent U-shaped cavity (411) is symmetrically fixedly connected to the upper end of the elastic pad (422); the T-shaped connecting block (423) slides in the vertical part of the U-shaped cavity (411) between two adjacent groups of blocks; a compression spring (424) is fixedly connected to the upper end of the T-shaped connecting block (423) slidably connected to the inner surface of the vertical part of the U-shaped cavity (411); and the outer surface of the compression spring (424) is covered with a rubber layer.

8. The propeller retracting and deploying device for an anti-falling UAV according to claim 1, characterized in that: The elastic parachute structure (3) comprises an installation box (31) fixedly connected to the upper end of the fuselage (1); a shielding door (32) is symmetrically rotatably connected to the upper part of the inner surface of the installation box (31); two ends of the shielding doors (32) close to each other are symmetrically fixedly connected to electromagnets (33); the magnetic poles of two adjacent electromagnets (33) are opposite; and an elastic parachute assembly (34) is fixedly connected to the bottom wall of the inner surface of the installation box (31).

9. The propeller retracting and deploying device for an anti-falling UAV according to claim 8, characterized in that: The parachute assembly (34) comprises a cable (341) fixedly connected to the bottom wall of the inner surface of the installation box (31); the upper end of the cable (341) is fixedly connected to a limit block (344); the lower end of the limit block (344) and the outer surface of the cable (341) are fixedly connected to an arc-shaped cushion (343); the lower end of the arc-shaped cushion (343) is fixedly connected to a counterweight block (342) slidably connected to the cable (341); the inner surface of the counterweight block (342) is slidably connected to a plurality of L-shaped rods (345) fixedly connected to the outer surface of the limit block (344) in an annular shape; the upper ends of the plurality of L-shaped rods (345) are rotatably connected to pressure rods (347); the middle parts of the plurality of pressure rods (347) are rotatably connected to support seats (346) fixedly connected to the inner walls of adjacent counterweight blocks (342).

10. The propeller retracting and deploying device for an anti-falling UAV according to claim 9, characterized in that: The parachute assembly (34) also includes a plurality of connecting ropes (348) fixedly connected to the upper end of the counterweight block (342), and the other ends of the plurality of connecting ropes (348) are commonly fixedly connected to an umbrella bag (349). The umbrella bag (349) is located between the plurality of pressure rods (347) and the limit block (344) and is tightly attached to the lower part of the pressure rod (347). The pressure rod (347) is in an inclined state in an initial state and the distance between the plurality of pressure rods (347) is smaller than the outer diameter of the shell of the umbrella bag (349).

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