Anti-falling unmanned aerial vehicle capable of flying at low altitude

Abstract

The invention belongs to the technical field of unmanned aerial vehicles, and discloses a low-altitude flight anti-falling unmanned aerial vehicle which comprises a vehicle body, rotors, a mounting frame and a visual collection device fixed to the mounting frame, a mounting cavity is formed in the top of the vehicle body, and a pressing assembly is arranged in the mounting cavity in a sleeved mode; the interior of the mounting cavity is elastically connected with an elastic storage assembly, and a parachute body is arranged between the elastic storage assembly and the pressing assembly. According to the parachute, the acceleration sensor senses the falling state, senses the rapidly-increased acceleration value when falling occurs, and cooperates with the control end to control the action of the composite control assembly, so that the clamped pressing assembly is opened, and the parachute body and the pressing assembly are pushed out together in cooperation with the elastic action of the first spring to achieve active elastic reset; rapid parachute opening is completed, falling protection is achieved, the falling speed is reduced, anti-falling protection is achieved, the actual anti-falling effect is good, damage caused by rapid falling is avoided, and the use effect is good.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicles (UAVs), and in particular relates to a low-altitude flying anti-fall UAV. Background Art

[0002] In the application process of drones, they are usually divided into high-altitude flight and medium- and low-altitude flight, which perform different tasks respectively. For common power inspections and land exploration, drones equipped with visual acquisition devices are usually used for flight work.

[0003] Low-altitude flying drones in the existing technology are prone to colliding with some obstacles and falling during such low-altitude flight operations. In addition, when the drone itself malfunctions during low-altitude operations, the drone may also fall, and there is a lack of limited anti-fall treatment after the fall. Usually, the drone relies solely on its own elastic buffer mechanism to achieve protection when it falls. However, although it flies at a low altitude, the actual altitude is still high, and the impact of the fall is relatively large. The current anti-fall capability is average and cannot effectively achieve anti-fall treatment. The drone is basically completely damaged when it falls, and its self-protection is poor. Summary of the Invention

[0004] The purpose of the present invention is to provide a low-altitude flying anti-fall drone to solve the problems raised in the above background technology.

[0005] In order to achieve the above-mentioned purpose, the present invention provides the following technical solutions: a low-altitude anti-fall drone, comprising a body, a rotor, a mounting frame, and a visual acquisition device fixed on the mounting frame, wherein a mounting cavity is provided on the top of the body, a clamping assembly is sleeved inside the mounting cavity, an elastic storage assembly is elastically connected inside the mounting cavity, a parachute body is provided between the elastic storage assembly and the clamping assembly, a connecting rope end of the parachute body is fixed in the mounting cavity, a high-pressure chamber and a communicating airway are provided inside the body, a composite control assembly is provided in the high-pressure chamber and the communicating airway, the composite control assembly simultaneously controls the clamping of the clamping assembly and the communication of the communicating airway, an acceleration sensing assembly is fixed on the top of the body,

[0006] The composite control assembly includes an electric push rod, a sealing head, a clamping block, a rigid rope and a second spring. The electric push rod is fixed in the high-pressure chamber, and the movable end is fixedly connected to the sealing head. The clamping block is movably sleeved in the inner wall of the installation chamber. The second spring is fixed in the communicating air passage through a support frame and is fixedly connected to the clamping block. The rigid rope is fixedly connected between the clamping block and the sealing head.

[0007] Preferably, the rotor is arranged around the outside of the fuselage, the mounting frame is fixed to the bottom of the fuselage, and the visual acquisition device is fixed in the mounting frame. The ascent and takeoff are achieved by utilizing the rotation of the rotor. The visual acquisition device is an existing mechanism for image acquisition to complete low-altitude inspection operations.

[0008] Preferably, the clamping assembly includes a sealing cover, a connecting rod, a pressure plate and a bayonet, the connecting rod is fixed to the bottom surface of the sealing cover, the pressure plate is fixed to the bottom surface of the connecting rod, the bayonet is opened on both sides of the sealing cover, and the sealing cover is movably sleeved inside the installation cavity. The hidden storage of the parachute body and the elastic storage assembly is realized through the clamping assembly, and the elastic potential energy is stored in the compressed spring 1. After the block in the bayonet is removed, the elasticity of the spring 1 is cooperated to realize the release and throwing out outward, and the parachute body is opened and thrown out to complete the anti-fall protection.

[0009] Preferably, the elastic storage assembly includes an elastic storage bag, a support plate and an air guide tube, the elastic storage bag is fixed to the top surface of the support plate, the upper end of the air guide tube is fixedly connected to the bottom surface of the support plate and communicated with the elastic storage bag, the lower end of the air guide tube is communicated with the communicating air duct, and a spring 1 is fixedly connected to the interior of the installation cavity, and the spring 1 is fixedly connected to the bottom surface of the support plate. By utilizing the elastic storage assembly to quickly store pressurized air, filling and expansion are achieved, thereby further squeezing and expanding the parachute body, ensuring that the connecting rope of the parachute body is fully separated and opened, avoiding entanglement, and further improving the efficiency and effect of throwing and opening the parachute body, thereby improving anti-fall protection.

[0010] Preferably, the communicating air channel includes an adaptor groove, a bottom hole and a communicating groove. The bottom hole is opened at the bottom of the mounting cavity and is communicated with the mounting cavity. The adaptor groove is opened inside the body. The communicating groove is opened inside the body. Both ends of the communicating groove are communicated with the bottom hole and the adaptor groove respectively. The upper end of the adaptor groove is communicated with the mounting cavity. The card block, rigid rope and spring 2 are all located in the adaptor groove. The lower end of the air guide tube is sleeved in the bottom hole and is communicated with the bottom hole. The pressurized air is directionally discharged by utilizing the communicating air channel and input into the elastic storage assembly to realize the rapid expansion of the elastic storage assembly. The adaptor groove adapts the arrangement of the card block, spring 2 and rigid rope.

[0011] Preferably, a sealing port is provided inside the body, and the two ends of the sealing port are respectively connected to the high-pressure chamber and the adapter groove, and the sealing head is movably sleeved in the sealing port. The sealing port is utilized to realize the conduction between the connecting airway and the high-pressure chamber, thereby completing the output of pressurized air, and the cooperation between the charging component and the connecting chamber realizes the filling process of the pressurized air in the high-pressure chamber, which is connected to the external air pump through the air injection pipe to complete the inflation, and the sealing plug realizes quick sealing.

[0012] Preferably, a communication cavity is opened on one side of the body, a charging assembly is fixedly provided on the front side of the communication cavity, and the communication cavity is connected with the high-pressure cavity.

[0013] Preferably, the charging assembly includes a connecting plate, a connecting pipe, an air injection pipe and a sealing plug. The connecting plate is fixedly sleeved in the connecting cavity, the connecting pipe is fixed on the front side of the connecting plate and connected to the connecting cavity, the air injection pipe is fixedly connected to the bottom of the connecting pipe, and the sealing plug is threadedly sleeved on the end of the connecting pipe.

[0014] Preferably, a side port is provided on the front of the body, and the side port is connected to a high-pressure chamber. A purge assembly is fixedly provided on the front of the side port, and the purge assembly includes a connecting frame, an air jet pipe and a solenoid valve. The connecting frame is fixed on the front of the body and is connected to the side port. The solenoid valve is fixed in the connecting frame and controls the connection between the connecting frame and the side port. The air jet pipe is fixedly connected to the bottom of the connecting frame and is connected to the connecting frame. The air outlet end of the air jet pipe faces the visual acquisition device. By utilizing the side port and the purge assembly, the pressure air is swept, and the stored pressure air in the high-pressure chamber is used again to guide the end face of the visual acquisition device to be purged and cleaned when needed.

[0015] Preferably, the acceleration control component includes an acceleration sensor, a power supply and a control end. An assembly cavity is opened on the top of the body, and the acceleration sensor, power supply and control end are all fixed in the assembly cavity. By utilizing the acceleration sensor to sense the occurrence of a fall, the power supply and control end are cooperated to independently control the systems other than the UAV flight to complete the control of the anti-fall system, including the start-up control of the purge, the release of the pressurized air and the release of the parachute body, etc. When the power supply of the UAV flight system fails, the anti-fall processing can still be achieved independently.

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

[0017] (1) The present invention senses the falling state through an acceleration sensor. When a fall occurs, it senses the rapidly increasing acceleration value and cooperates with the control end to control the action of the composite control component, thereby opening the clamping component, cooperating with the elastic action of spring 1, actively elastically resetting, and pushing the parachute body and the clamping component outward together, completing the rapid opening of the parachute, realizing fall protection, slowing down the falling speed, and realizing anti-fall protection. The actual anti-fall effect is good, and damage caused by rapid falling is avoided, and the use effect is good.

[0018] (2) The present invention cooperates with the action of the composite control component to realize the opening of the parachute at the same time as the high-pressure chamber is opened, the pre-stored compressed air is released, and the released compressed air is filled into the elastic storage component, and the expanded elastic storage component is further used to increase the opening speed of the parachute body. At the same time, the elastic storage component is cooperated with the expansion effect to open the connecting rope part of the parachute body, thereby avoiding the occurrence of entanglement, improving the opening speed and effect of the parachute, ensuring effective opening of the parachute to prevent falling, and further improving the anti-fall effect.

[0019] (3) The present invention reuses the pre-stored compressed air and cooperates with the short opening and closing of the purge component to input the stored compressed air into the purge component, and performs high-pressure mirror purge on the visual acquisition equipment for inspection through the air jet pipe, thereby completing effective and rapid self-cleaning, maintaining good inspection and acquisition effects, and ensuring the subsequent completion of stable and high-quality inspection tasks. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a structural schematic diagram of the present invention;

[0021] Figure 2 It is a cross-sectional schematic diagram of the present invention;

[0022] Figure 3 It is a cross-sectional schematic diagram of the body of the present invention;

[0023] Figure 4 is a schematic diagram of a compression assembly of the present invention;

[0024] Figure 5 Schematic diagram of an explosion of the elastic storage assembly of the present invention;

[0025] Figure 6 This is a schematic diagram of the composite control assembly of the present invention;

[0026] Figure 7 It is a cross-sectional schematic diagram of the body and assembly cavity of the present invention;

[0027] Figure 8 is a schematic cross-sectional view of the purge assembly of the present invention;

[0028] Figure 9 Schematic diagram of the explosion of the body and pressurized components of the present invention;

[0029] Figure 10 Schematic diagram of the explosion of the pressurized component of the present invention.

[0030] In the figure: 1. Airframe; 2. Visual acquisition device; 3. Mounting cavity; 4. Pressing assembly; 41. Sealing cover; 42. Connecting rod; 43. Pressing plate; 44. Bayonet; 5. Elastic storage assembly; 51. Elastic storage capsule; 52. Support plate; 53. Air guide tube; 6. Parachute body; 7. Spring 1; 8. Adapter slot; 9. Bottom hole; 10. Connecting slot; 11. High-pressure chamber; 12. Sealing port; 13. Side port; 14. Purge assembly 141. Connecting frame; 142. Injection pipe; 143. Solenoid valve; 15. Assembly chamber; 16. Acceleration sensor; 17. Power supply; 18. Control terminal; 19. Connecting chamber; 20. Pressurization assembly; 201. Connecting plate; 202. Connecting pipe; 203. Gas injection pipe; 204. Sealing plug; 21. Composite control assembly; 211. Electric push rod; 212. Sealing head; 213. Block; 214. Rigid rope; 215. Spring 2. DETAILED DESCRIPTION

[0031] 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.

[0032] like Figures 1 to 10 As shown, an embodiment of the present invention provides a low-altitude anti-fall drone, including a body 1, a rotor, a mounting frame, and a visual acquisition device 2 fixed to the mounting frame. A mounting cavity 3 is provided on the top of the body 1, a pressing component 4 is provided inside the mounting cavity 3, an elastic storage component 5 is elastically connected to the inside of the mounting cavity 3, a parachute body 6 is provided between the elastic storage component 5 and the pressing component 4, and the connecting rope end of the parachute body 6 is fixed in the mounting cavity 3. A high-pressure chamber 11 and a communicating airway are provided inside the body 1, and a composite control component 21 is provided in the high-pressure chamber 11 and the communicating airway. The composite control component 2 1 simultaneously controls the clamping of the pressing assembly 4 and the communication of the communicating airway. An acceleration sensing assembly is fixedly provided on the top of the body 1. The composite control assembly 21 includes an electric push rod 211, a sealing head 212, a clamping block 213, a rigid rope 214, and a second spring 215. The electric push rod 211 is fixed in the high-pressure chamber 11, and its movable end is fixedly connected to the sealing head 212. The clamping block 213 is movably sleeved in the inner wall of the installation chamber 3. The second spring 215 is fixed in the communicating airway through a support frame and is fixedly connected to the clamping block 213. The rigid rope 214 is fixedly connected between the clamping block 213 and the sealing head 212.

[0033] Example 1: During use, when the drone malfunctions and falls, the body 1 falls rapidly, the acceleration sensor 16 senses the acceleration change, and under the power supply of the independent power supply 17, the control end 18 receives the sensing signal of the acceleration sensor 16 and controls the action of the composite control component 21. The electric push rod 211 drives the sealing head 212 to move out of the sealing port 12 and open the sealing port 12. As the sealing head 212 moves toward the inside of the high-pressure chamber 11, the rigid rope 214 is driven to move and pull the card block 213. The card block 213 compresses the spring 215. The spring 215 is compressed on the support frame in the adapter groove 8, and the card block 213 is released from the pressing component 4. The spring 7 in the mounting cavity 3 loses compression and recovers elastically, pushing the elastic storage assembly 5 and the parachute body 6 outward quickly, and the pressing assembly 4 pops out from the UAV, and the parachute body 6 pops outward and opens, realizing the parachute opening in the air. As the sealing head 212 in the composite control assembly 21 moves and opens, the pressurized air in the high-pressure chamber 11 is input into the elastic storage bag 51 of the elastic storage assembly 5 through the connecting groove 10 and the bottom hole 9. The elastic storage bag 51 expands rapidly, stretching the connecting rope of the outer parachute body 6, and the parachute body 6 quickly and fully opens, completing the anti-fall protection in the falling state, and the UAV gradually and smoothly lands through the parachute body 6.

[0034] First, the falling state is sensed by the acceleration sensor 16. When the fall occurs, the rapidly increasing acceleration value is sensed, and the control end 18 is cooperated to control the action of the composite control component 21, thereby opening the clamping component 4, cooperating with the elastic action of the spring 7, actively elastically resetting, and pushing the parachute body 6 and the clamping component 4 outward together, completing the rapid opening of the parachute, realizing fall protection, slowing down the falling speed, and realizing anti-fall protection. The actual anti-fall effect is good, avoiding damage caused by rapid falling, and having a good use effect.

[0035] In addition, by coordinating the action of the composite control component 21, the parachute is opened at the same time, the high-pressure chamber 11 is opened, the pre-stored compressed air is released, and the released pressurized air is filled into the elastic storage component 5, and the expanded elastic storage component 5 is further utilized to increase the opening speed of the parachute body 6. At the same time, in conjunction with the expansion effect of the elastic storage component 5, the connecting rope part of the parachute body 6 is stretched to avoid entanglement, thereby increasing the opening speed and effect of the parachute, ensuring effective opening of the parachute to prevent falling, and further improving the anti-fall effect.

[0036] Example 2: After performing a flight mission, the mirror surface of the visual acquisition device 2 is dirty, and the solenoid valve 143 in the purge assembly 14 is started, so that the side port 13 and the connecting frame 141 are briefly connected, so that the compressed air in the corresponding high-pressure chamber 11 is quickly released and filled into the connecting frame 141, and is blown toward the mirror surface of the visual acquisition device 2 through the jet pipe 142 to complete the self-cleaning process.

[0037] First, the pre-stored compressed air is used again, and the short opening and closing of the purge component 14 is coordinated to input the stored compressed air into the purge component 14, and the mirror surface of the inspection visual acquisition device 2 is purged with high pressure through the jet pipe 142 to complete effective and rapid self-cleaning, maintain good inspection and acquisition effects, and ensure the subsequent completion of stable and high-quality inspection tasks.

[0038] The rotor is arranged around the outside of the body 1, the mounting frame is fixed to the bottom of the body 1, and the visual acquisition device 2 is fixed in the mounting frame.

[0039] The takeoff is achieved by utilizing the rotation of the rotor. The visual acquisition device 2 is an existing mechanism for collecting images and completing low-altitude inspection operations.

[0040] Among them, the clamping assembly 4 includes a sealing cover 41, a connecting rod 42, a pressure plate 43 and a bayonet 44. The connecting rod 42 is fixed on the bottom surface of the sealing cover 41, the pressure plate 43 is fixed on the bottom surface of the connecting rod 42, the bayonet 44 is opened on both sides of the sealing cover 41, and the sealing cover 41 is movably sleeved inside the installation cavity 3. The elastic storage assembly 5 includes an elastic storage bag 51, a support plate 52 and an air guide tube 53. The elastic storage bag 51 is fixed on the top surface of the support plate 52, the upper end of the air guide tube 53 is fixedly connected to the bottom surface of the support plate 52, and is connected to the elastic storage bag 51. The lower end of the air guide tube 53 is connected to the connecting airway. The interior of the installation cavity 3 is fixedly connected with a spring 7, and the spring 7 is fixedly connected to the bottom surface of the support plate 52.

[0041] The compression assembly 4 is used to realize hidden storage of the parachute body 6 and the elastic storage assembly 5, and the spring 1 7 is compressed to store elastic potential energy. After the block 213 in the bayonet 44 is moved out, the elasticity of the spring 1 7 is cooperated to realize outward release and throwing, and the parachute body 6 is opened and thrown to complete the anti-fall protection. By utilizing the elastic storage assembly 5 to quickly store pressurized air, filling and expansion are realized, thereby further squeezing and expanding the parachute body 6, ensuring that the connecting rope of the parachute body 6 is fully separated and opened, avoiding entanglement, and further improving the efficiency and effect of throwing and opening the parachute body 6, thereby improving the anti-fall protection.

[0042] Among them, the communicating air duct includes an adaptor groove 8, a bottom hole 9 and a communicating groove 10. The bottom hole 9 is opened at the bottom of the installation cavity 3 and is communicated with the installation cavity 3. The adaptor groove 8 is opened inside the body 1. The communicating groove 10 is opened inside the body 1. The two ends of the communicating groove 10 are respectively communicated with the bottom hole 9 and the adaptor groove 8. The upper end of the adaptor groove 8 is communicated with the installation cavity 3. The block 213, the rigid rope 214 and the spring 215 are all located in the adaptor groove 8. The lower end of the air guide tube 53 is sleeved in the bottom hole 9 and is communicated with the bottom hole 9.

[0043] By utilizing the connecting air channel to realize the directional derivation of the pressurized air and inputting it into the elastic storage component 5, the rapid expansion of the elastic storage component 5 is realized, and the adaption groove 8 adapts the arrangement processing of the card block 213, the spring 215 and the rigid rope 214.

[0044] Among them, a sealing port 12 is opened inside the body 1, and the two ends of the sealing port 12 are respectively connected to the high-pressure chamber 11 and the adapter groove 8, and the sealing head 212 is movably sleeved in the sealing port 12. A connecting chamber 19 is opened on one side of the body 1, and a charging assembly 20 is fixedly provided on the front of the connecting chamber 19. The connecting chamber 19 is connected to the high-pressure chamber 11. The charging assembly 20 includes a connecting plate 201, a connecting pipe 202, an air injection pipe 203 and a sealing plug 204. The connecting plate 201 is fixedly sleeved in the connecting chamber 19, the connecting pipe 202 is fixed on the front of the connecting plate 201 and is connected to the connecting chamber 19, the air injection pipe 203 is fixedly connected to the bottom of the connecting pipe 202, and the sealing plug 204 is threadedly sleeved on the end of the connecting pipe 202.

[0045] By utilizing the sealing port 12 to achieve conduction between the communicating airway and the high-pressure chamber 11, the output of pressurized air is completed, and the cooperation between the charging component 20 and the communicating chamber 19 realizes the filling process of the pressurized air in the high-pressure chamber 11. The air is connected to the external air pump through the air injection pipe 203 to complete the inflation, and the sealing plug 204 realizes quick sealing.

[0046] Among them, a side port 13 is opened on the front of the body 1, and the side port 13 is connected to a high-pressure chamber 11. A purge assembly 14 is fixed on the front of the side port 13. The purge assembly 14 includes a connecting frame 141, an injection pipe 142 and a solenoid valve 143. The connecting frame 141 is fixed on the front of the body 1 and is connected to the side port 13. The solenoid valve 143 is fixed in the connecting frame 141 and controls the connection between the connecting frame 141 and the side port 13. The injection pipe 142 is fixedly connected to the bottom of the connecting frame 141 and is connected to the connecting frame 141. The air outlet end of the injection pipe 142 faces the visual acquisition device.

[0047] By utilizing the side port 13 and the purge assembly 14 to achieve the purge of pressurized air, the stored pressurized air in the high-pressure chamber 11 is used again to guide the purge and cleaning of the end face of the visual acquisition device 2 when needed.

[0048] Among them, the acceleration control component includes an acceleration sensor 16 (existing sensor, specific model is LSM303D), a power supply 17 and a control terminal 18. An assembly cavity 15 is opened on the top of the body 1, and the acceleration sensor 16, power supply 17 and control terminal 18 are all fixed in the assembly cavity 15.

[0049] By utilizing the acceleration sensor 16 to sense the occurrence of a fall, and cooperating with the power supply 17 and the control terminal 18 to independently control the systems other than the UAV flight, the anti-fall system is controlled, including the start-up control of the purge, the release of the pressurized air, and the release of the parachute body 6, etc. When the UAV flight system fails in power supply, the anti-fall processing can still be achieved independently.

[0050] The working principle and use process of the present invention are as follows: During use, when the drone malfunctions and falls, the body 1 falls rapidly, the acceleration sensor 16 senses the acceleration change, and under the power supply of the independent power supply 17, the control end 18 receives the sensing signal of the acceleration sensor 16 and controls the action of the composite control component 21, and the electric push rod 211 drives the sealing head 212 to move out of the sealing port 12 and open the sealing port 12. As the sealing head 212 moves toward the inside of the high-pressure chamber 11, it drives the rigid rope 214 to move and pulls the card block 213, and the card block 213 compresses the spring 215. The spring 215 is compressed on the support frame in the adapter groove 8, and the card block 213 is moved out of the card port 44 of the clamping component 4. The spring 1 7 in the installation chamber 3 loses compression and recovers elastically, quickly pushing the elastic storage component 5 and the parachute body 6 outward, and the clamping component 4 is released from The parachute body 6 pops out from the drone and opens, realizing the parachute opening in the air. As the sealing head 212 in the composite control component 21 moves and opens, the pressurized air in the high-pressure chamber 11 is input into the elastic storage bag 51 of the elastic storage component 5 through the connecting groove 10 and the bottom hole 9. The elastic storage bag 51 expands rapidly, stretching the connecting rope of the outer parachute body 6, and the parachute body 6 quickly and fully opens, completing the anti-fall protection in the falling state, and the drone gradually and smoothly lands through the parachute body 6; after performing the flight mission, the mirror surface of the visual acquisition device 2 is dirty, and the solenoid valve 143 in the purge component 14 is started, so that the side port 13 and the connecting frame 141 are briefly connected, so that the compressed air in the corresponding high-pressure chamber 11 is quickly released and filled into the connecting frame 141, and is blown toward the mirror surface of the visual acquisition device 2 through the jet pipe 142 to complete the self-cleaning process.

[0051] 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 low-altitude anti-fall drone, comprising a body (1), a rotor, a mounting frame, and a visual acquisition device (2) fixed to the mounting frame, characterized in that: The top of the body (1) is provided with an installation cavity (3), the interior of the installation cavity (3) is provided with a pressing assembly (4), the interior of the installation cavity (3) is elastically connected with an elastic storage assembly (5), a parachute body (6) is provided between the elastic storage assembly (5) and the pressing assembly (4), the connecting rope end of the parachute body (6) is fixed in the installation cavity (3), the interior of the body (1) is provided with a high-pressure cavity (11) and a communicating airway, the high-pressure cavity (11) and the communicating airway are provided with a composite control assembly (21), the composite control assembly (21) simultaneously controls the clamping of the pressing assembly (4) and the communication of the communicating airway, and an acceleration sensing assembly is fixedly provided on the top of the body (1). The composite control assembly (21) comprises an electric push rod (211), a sealing head (212), a clamping block (213), a rigid rope (214) and a second spring (215). The electric push rod (211) is fixed in the high-pressure chamber (11), and the movable end is fixedly connected to the sealing head (212). The clamping block (213) is movably sleeved in the inner wall of the installation chamber (3). The second spring (215) is fixed in the communicating air passage through a support frame and is fixedly connected to the clamping block (213). The rigid rope (214) is fixedly connected between the clamping block (213) and the sealing head (212).

2. The low-altitude anti-fall UAV according to claim 1, characterized in that: The rotor is arranged around the outside of the body (1), the mounting frame is fixed to the bottom of the body (1), and the visual acquisition device (2) is fixed in the mounting frame.

3. The low-altitude anti-fall UAV according to claim 2, characterized in that: The clamping assembly (4) includes a sealing cover (41), a connecting rod (42), a pressure plate (43) and a bayonet (44), wherein the connecting rod (42) is fixed to the bottom surface of the sealing cover (41), the pressure plate (43) is fixed to the bottom surface of the connecting rod (42), the bayonet (44) is opened on both sides of the sealing cover (41), and the sealing cover (41) is movably sleeved inside the installation cavity (3).

4. The low-altitude anti-fall UAV according to claim 3, characterized in that: The elastic storage assembly (5) comprises an elastic storage bag (51), a support plate (52) and an air guide tube (53), wherein the elastic storage bag (51) is fixed on the top surface of the support plate (52), the upper end of the air guide tube (53) is fixedly connected to the bottom surface of the support plate (52) and communicated with the elastic storage bag (51), the lower end of the air guide tube (53) is connected to the communicating air passage, and a spring (7) is fixedly connected to the interior of the mounting cavity (3), and the spring (7) is fixedly connected to the bottom surface of the support plate (52).

5. The low-altitude anti-fall UAV according to claim 4, characterized in that: The communicating air passage comprises an adapting groove (8), a bottom hole (9) and a communicating groove (10); the bottom hole (9) is provided at the bottom of the mounting cavity (3) and is communicated with the mounting cavity (3); the adapting groove (8) is provided inside the machine body (1); the communicating groove (10) is provided inside the machine body (1); the two ends of the communicating groove (10) are respectively communicated with the bottom hole (9) and the adapting groove (8); the upper end of the adapting groove (8) is communicated with the mounting cavity (3); the block (213), the rigid rope (214) and the second spring (215) are all located in the adapting groove (8); the lower end of the air guide tube (53) is sleeved in the bottom hole (9) and is communicated with the bottom hole (9).

6. The low-altitude anti-fall UAV according to claim 5, characterized in that: A sealing opening (12) is provided inside the machine body (1), and two ends of the sealing opening (12) are respectively connected to the high-pressure chamber (11) and the adapting groove (8), and the sealing head (212) is movably sleeved in the sealing opening (12).

7. The low-altitude anti-fall UAV according to claim 6, characterized in that: A communication cavity (19) is provided on one side of the machine body (1), a charging assembly (20) is fixedly provided on the front side of the communication cavity (19), and the communication cavity (19) is communicated with the high-pressure cavity (11).

8. The low-altitude anti-fall UAV according to claim 7, characterized in that: The charging assembly (20) comprises a connecting plate (201), a connecting pipe (202), an air injection pipe (203) and a sealing plug (204); the connecting plate (201) is fixedly sleeved in the connecting cavity (19); the connecting pipe (202) is fixed on the front side of the connecting plate (201) and is in communication with the connecting cavity (19); the air injection pipe (203) is fixedly connected to the bottom of the connecting pipe (202); and the sealing plug (204) is threadedly sleeved on the end of the connecting pipe (202).

9. The low-altitude anti-fall UAV according to claim 8, characterized in that: The front of the machine body (1) is provided with a side port (13), the side port (13) is communicated with a high-pressure chamber (11), a purge assembly (14) is fixedly provided on the front of the side port (13), the purge assembly (14) comprises a communication frame (141), an air jet pipe (142) and an electromagnetic valve (143), the communication frame (141) is fixed on the front of the machine body (1) and is communicated with the side port (13), the electromagnetic valve (143) is fixed in the communication frame (141) and controls the communication between the communication frame (141) and the side port (13), the air jet pipe (142) is fixedly connected to the bottom of the communication frame (141) and is communicated with the communication frame (141), and the air outlet end of the air jet pipe (142) faces the visual acquisition device.

10. The low-altitude anti-fall UAV according to claim 9, characterized in that: The acceleration control component comprises an acceleration sensor (16), a power supply (17) and a control terminal (18); an assembly cavity (15) is provided on the top of the body (1); and the acceleration sensor (16), the power supply (17) and the control terminal (18) are all fixed in the assembly cavity (15).

Images