Unmanned aerial vehicle capturing device based on radio distance detection

Abstract

The invention discloses an unmanned aerial vehicle capturing device based on radio distance detection, and relates to the technical field of unmanned aerial vehicle capturing devices.The unmanned aerial vehicle capturing device comprises an unmanned aerial vehicle body, a support is installed at the bottom of the unmanned aerial vehicle body through bolts, and two balance units are connected to the bottom of the support; the two balance units are used for balancing the unmanned aerial vehicle body and symmetrically distributed at the bottoms of the two sides of the unmanned aerial vehicle body, and recoil force is generated at the moment when the launching unit launches the catching net, so that a spherical protrusion at the end of an elastic element on one side of the launching unit overcomes clamping force of the spherical protrusion and a positioning groove; a second spring pushes a second piston to move in a sliding pipe, air or liquid media in a pressure pipe are pressed into the sliding pipe through a connecting pipe, a clamp drives a launching unit to move backwards to the position under the center of the abdomen of the unmanned aerial vehicle body through a pressure unit, and the situation that the unmanned aerial vehicle body inclines forwards due to weight forward movement after the unmanned aerial vehicle is captured due to the fact that the launching unit is too front is avoided. And balance and stability are ensured.

Description

Technical Field

[0001] This invention relates to the field of drone capture device technology, and more particularly to a drone capture device based on radio distance detection. Background Technology

[0002] With the increasing misuse of low-altitude small drones, the demand for "detect and capture" maneuver interception in key airspaces such as airports and urban core areas is becoming increasingly urgent. Current technologies generally integrate radio distance detection modules and transmitters into multi-rotor platforms, achieving precise forward capture through real-time ranging.

[0003] To avoid the drone's body obstructing the net, current drone capture devices typically fix the launcher at the very front of the multi-rotor platform. While this arrangement prevents the capture net and counterweight from entangled with the propeller during launch, it causes the target drone's weight to act directly on the nose hardpoint after capture, generating a sudden forward and downward eccentric moment. Because the lifting surface remains horizontal, the aircraft's center of gravity shifts forward instantaneously, resulting in an uncontrollable forward tilt. This forward tilt is particularly pronounced when the target drone is large or heavy, and even with full rudder compensation, the flight control system struggles to restore balance, becoming a core flaw that current "forward-mounted" solutions cannot overcome.

[0004] To address this, the present invention proposes a drone capture device based on radio distance detection. After the radio ranging triggers the launch, the recoil drives the transmitter to move instantly to the underside of the drone's belly. The target's weight acts on the vertical line of the center of gravity, and the platform does not need to compensate for the pitch moment. Summary of the Invention

[0005] One objective of this invention is to provide a drone capture device based on radio distance detection, which can solve the problem that the drone is prone to imbalance after capture due to forward launch.

[0006] According to an embodiment of the present invention, a drone capture device based on radio distance detection includes a drone body. A bracket is bolted to the bottom of the drone body, and a balancing unit is connected to the bottom of the bracket. Two balancing units are provided to balance the drone body, and the two balancing units are symmetrically distributed on both sides of the bottom of the drone body. A pressure unit is provided between the two balancing units. A clamp is fixedly installed on the outside of the pressure unit and connected to the balancing unit. A launching unit is provided at one end of the pressure unit, and the pressure unit is used to provide pressure to the launching unit. The inside of the pressure unit is connected to the inside of the launching unit. A capture net is assembled inside the launching unit, and the four ends of the capture net are connected to a counterweight. The counterweight is embedded inside the launching unit.

[0007] Furthermore, the balancing unit includes a piston assembly and a limiting assembly. The piston assembly is engaged with the C-shaped slots on both sides of the connecting slot, and the connecting surface is provided with a set bolt to fix the piston assembly. The piston assembly is used to drive the pressure unit to move back and forth in the horizontal direction. The limiting assembly is installed on the surface of the piston assembly and is used to cooperate with the launching unit to limit the piston assembly.

[0008] Furthermore, the piston assembly includes a pressure tube with a hollow interior. A first spring is installed at one end of the pressure tube, and a first piston is installed at the other end of the first spring. The outer wall of the first piston is tightly fitted to the inner wall of the pressure tube. An exhaust groove, which is a circular groove, is provided at one end of the pressure tube. One side of the exhaust groove is connected to one end of a connecting pipe, and the other end of the connecting pipe is connected to the side wall of one end of a slide tube. A second piston is installed inside the slide tube, and the outer wall of the second piston is tightly fitted to the inner wall of the slide tube. The second piston is fixedly connected to one end of a piston rod, and the surface of the piston rod is slidably connected to one end of the slide tube. A strip-shaped protrusion is provided on the surface of the piston rod to restrict the rotation of the piston rod. The other end of the piston rod is fixedly connected to a clamp.

[0009] Furthermore, the limiting component includes a second spring and a positioning groove. The second spring is located inside the second piston. One end of the second piston is provided with a circular slot, and one end of the second spring protrudes from the end of the second piston. The positioning groove is fixedly installed on the side wall of the slide tube. The outer wall surface of the positioning groove is provided with a hemispherical groove. The positioning groove is engaged with a spherical protrusion. The spherical protrusion is provided at one end of the elastic element. The elastic element is connected to the launching unit. The elastic element is made of elastic metal and has a U-shaped structure.

[0010] Furthermore, the pressure unit includes an exhaust assembly and a reset assembly. The exhaust assembly is connected to the launching unit and is used to exhaust air into the launching unit. The exhaust assembly is connected to the reset assembly via a fixing ring and is used to reset the exhaust assembly. The fixing ring has bolts on its surface and the head of the fixing ring is fixed to the surface of the exhaust assembly by bolts.

[0011] Furthermore, the exhaust assembly includes a compression pipe, inside which a third piston is disposed, and a rubber ring is embedded in the outer wall of the third piston. One end of the third piston is fixedly connected to a transmission rod, and a third spring is disposed outside one end of the transmission rod. A tailstock is fixedly installed at one end of the compression pipe, and a dust cover is connected to one end of the tailstock. The dust cover is made of rubber and has a corrugated structure on its surface for telescopic extension. The surface of the transmission rod has grooves, and the grooves on the surface of the transmission rod have teeth inside.

[0012] Furthermore, the reset assembly includes a rotating shaft rotatably connected to the surface of a fixed ring. One end of the rotating shaft has a hexagonal groove for engaging with an external hexagonal groove wrench. A transmission gear is keyed to the outside of the rotating shaft, meshing with the surface of a transmission rod. A ratchet is located on one side of the transmission gear, connected to the rotating shaft key. The surface of the ratchet engages with a locking block, which restricts the ratchet's unidirectional rotation. A spring is embedded in the surface of the locking block to elastically push the locking block to rotate in the ratchet direction. A paddle is fixedly mounted on one end of the locking block, and the connection between the locking block and the paddle is rotatably connected to a limiting shaft. The limiting shaft is rotatably connected to the fixed ring. A micro switch is mounted on the surface of the fixed ring, electrically connected to a control terminal. The telescopic end of the micro switch abuts against the surface of the paddle.

[0013] Furthermore, the launching unit includes an assembly head and a driving assembly. The assembly head is used to install a capture net. The driving assembly is located above one end of the assembly head and is used to drive the assembly head to rotate. The interior of the assembly head is connected to the interior of the pressure assembly. Both sides of the assembly head are rotatably connected to connecting heads. The interior of the connecting heads is connected to the interior of connecting heads. The interior of the connecting heads has a hollow structure. One end of the connecting head is fixedly connected to a pressure tube. Both sides of the assembly head are fixedly connected to elastic elements.

[0014] Furthermore, the assembly head has a launching slot at one end, which is radially oriented. The assembly head also has a receiving slot for holding a capture net. A tail line slot is provided at the rear end of the receiving slot for holding the tail line of the capture net, and the tail line of the capture net is fixedly connected to the rear end of the tail line slot. A connecting cavity is provided at the rear end of the tail line slot. One end of the connecting cavity is connected to the interior of the connector, and the other end of the connecting cavity is connected to the ends of the four launching slots.

[0015] Furthermore, the drive assembly includes a waterproof cover, the two sides of which are fixedly connected to the connector by screws. A drive motor is fixedly installed inside the waterproof cover. The drive motor is electrically connected to the control terminal. A drive gear is keyed to the external output end of the drive motor. The drive gear meshes with a gear ring, which is installed outside the connector.

[0016] The beneficial effects of this invention are:

[0017] This invention, by setting a balancing unit, positions the launch unit initially at the bottom front of the drone body, preventing the drone body itself from interfering with the launch of the capture net and preventing the capture net from getting entangled with the propeller blades. When the launch unit launches the capture net, the recoil force generated causes the spherical protrusion at the end of the elastic element on one side of the launch unit to overcome the locking force with the positioning groove. After the locking is released, the second spring pushes the second piston to move inside the slide tube, exposing the connecting pipe and the internal channel of the slide tube, so that the pressure pipe is connected to the slide tube. The first spring pushes the first piston to move, forcing the air or liquid medium in the pressure pipe into the slide tube through the connecting pipe, pushing the second piston to move the piston rod and clamp backward. The clamp, through the pressure unit, moves the launch unit backward to directly below the center of the drone body's abdomen, preventing the launch unit from being too far forward, which would cause the drone body to tilt forward due to the forward shift of weight after capture, thus ensuring balance and stability.

[0018] This invention utilizes a pressure unit to remotely drive a microswitch, causing its telescopic end to pop out and press down a lever. The lever then causes a locking block to overcome the pressure of the top spring and disengage from the ratchet. The ratchet then releases its rotational restriction on the shaft and transmission gear, causing the transmission rod to disengage. Under the action of the third spring, the third piston is pushed, instantly injecting air from the compressed tube into the launching unit. The high-pressure air drives the counterweight to throw the capture net outward, capturing the drone in front. After the drone returns, the microswitch is reset, and the locking block re-engages with the ratchet under the action of the spring. Maintenance personnel can manually rotate the shaft by inserting a hexagonal wrench into the hexagonal groove. The gear drives the transmission rod backward, resetting the third piston and recompressing the third spring. The entire process can achieve multiple cycles of net activation without an external power source, significantly improving ease of use.

[0019] This invention, through the setting of a launch unit, allows the high-pressure airflow from the pressure unit to enter the communicating cavity via a compression pipe and a connector, simultaneously pushing the counterweights in each launch slot to carry out the capture net. The drive motor drives the assembly head to rotate downwards via a drive gear-ring drive, enabling the capture of targets below the UAV body. As the assembly head rotates, it simultaneously drives the elastic element to disengage the spherical protrusion from the positioning slot. Even without recoil, it can be unlocked by rotation, allowing the launch unit to automatically move backwards to directly below the center of the UAV belly, ensuring stable suspension after capture. At the same time, the connecting pipe dampens and suppresses the flow of the medium in the pressure pipe, avoiding backward impact and achieving a smooth and reliable launch, turning, and backward movement process. Attached Figure Description

[0020] The accompanying drawings are provided to further illustrate the invention and form part of the specification. They are used in conjunction with embodiments of the invention to explain the invention and do not constitute a limitation thereof. In the drawings:

[0021] Figure 1 This is a schematic diagram of the overall structure of a drone capture device based on radio distance detection proposed in this invention;

[0022] Figure 2 This is a side view schematic diagram of a drone capture device based on radio distance detection proposed in this invention.

[0023] Figure 3 This is a front view schematic diagram of a drone capture device based on radio distance detection proposed in this invention.

[0024] Figure 4 This is a top view schematic diagram of a drone capture device based on radio distance detection proposed in this invention.

[0025] Figure 5 This is a schematic diagram of the rearward state of the launching unit of a drone capture device based on radio distance detection proposed in this invention.

[0026] Figure 6 This is a schematic diagram of the initial state of the launching unit of a drone capture device based on radio distance detection proposed in this invention.

[0027] Figure 7 This is a schematic diagram of the elastic sheet structure of a drone capture device based on radio distance detection proposed in this invention.

[0028] Figure 8 This is a schematic cross-sectional view of the assembly head of a drone capture device based on radio distance detection proposed in this invention.

[0029] Figure 9 This is a schematic diagram of the pressure unit structure of a drone capture device based on radio distance detection proposed in this invention.

[0030] Figure 10 This is a schematic diagram of the internal structure of the pressure unit of a drone capture device based on radio distance detection proposed in this invention.

[0031] Figure 11 This is a schematic diagram of the lever structure of a drone capture device based on radio distance detection proposed in this invention.

[0032] Figure 12 This is a schematic diagram of the balancing unit structure of a drone capture device based on radio distance detection proposed in this invention.

[0033] Figure 13 This is a schematic diagram of the internal structure of the slide tube of a drone capture device based on radio distance detection proposed in this invention.

[0034] Figure 14 This is a schematic diagram of the internal structure of the pressure tube of a drone capture device based on radio distance detection proposed in this invention.

[0035] In the diagram: 1. UAV body; 2. Support frame; 3. Balancing unit; 31. Pressure pipe; 32. First spring; 33. First piston; 34. Exhaust channel; 35. Connecting pipe; 36. Sliding pipe; 37. Second piston; 38. Piston rod; 39. Second spring; 310. Positioning groove; 311. Connecting slot; 4. Clamp; 5. Pressure unit; 51. Compression pipe; 52. Third piston; 53. Third spring; 54. Transmission rod; 55. Tailstock; 56. Dust cover; 57. Retaining ring; 58. Transmission gear; 59. Rotating shaft; 510. Locking block; 511. Micro switch; 512. Ratchet; 513. Paddle; 514. Limiting shaft; 6. Launching unit; 61. Assembly head; 62. Launch slot; 63. Storage slot; 64. Tail wire slot; 65. Connecting cavity; 66. Gear ring; 67. Drive gear; 68. Drive motor; 69. Waterproof cover; 7. Counterweight. Detailed Implementation

[0036] The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic diagrams, illustrating only the basic structure of the invention, and therefore only show the components relevant to the invention.

[0037] refer to Figure 1-6 The device includes a drone body 1, a bracket 2 bolted to the bottom of the drone body 1, a balancing unit 3 connected to the bottom of the bracket 2, two balancing units 3 for balancing the drone body 1, and two balancing units 3 symmetrically distributed on both sides of the bottom of the drone body 1, a pressure unit 5 between the two balancing units 3, a clamp 4 fixedly installed on the outside of the pressure unit 5 and connected to the balancing unit 3, a launch unit 6 at one end of the pressure unit 5 for providing pressure to the launch unit 6, the inside of the pressure unit 5 being connected to the inside of the launch unit 6, a capture net being assembled inside the launch unit 6, and the four ends of the capture net being connected to the counterweight 7, the counterweight 7 being embedded inside the launch unit 6;

[0038] This implementation scheme, by initially setting the launch unit 6 at the bottom of the UAV body 1 in a forward position and automatically moving it to the underside of the fuselage after launch using recoil, allows the weight of the captured target UAV to act directly on the vertical line of the overall center of gravity. This eliminates the sudden forward and downward eccentricity generated at the moment of capture in the traditional "forward installation" scheme, thereby solving the core defect of the UAV body 1 being uncontrollably tilted forward due to the forward shift of the center of gravity and the flight control system being unable to restore balance even with full rudder input. It also enables the platform to maintain stability after capture without compensating for pitch moment.

[0039] All electrical components mentioned in the text are electrically connected to an external main controller, which can be a conventional known device such as a computer for control.

[0040] refer to Figure 12-14The balancing unit 3 includes a piston assembly and a limiting assembly. The piston assembly engages with the C-shaped slots on both sides of the connecting slot 311, and the connecting surface is provided with set bolts to fix the piston assembly. The piston assembly is used to drive the pressure unit 5 to move horizontally back and forth. The limiting assembly is installed on the surface of the piston assembly and is used to limit the piston assembly in conjunction with the launching unit 6. The piston assembly includes a pressure tube 31, which has a hollow internal structure. A first spring 32 is provided at one end of the pressure tube 31, and a first piston 33 is provided at the other end of the first spring 32. The outer wall of the first piston 33 is tightly fitted with the inner wall of the pressure tube 31. An exhaust groove 34 is provided at one end of the pressure tube 31. The exhaust groove 34 is a circular groove. One side of the exhaust groove 34 is connected to one end of the connecting tube 35, and the other end of the connecting tube 35 is connected to one side wall of the slide tube 36. A second piston 37 is provided inside the slide tube 36. The wall is tightly fitted to the inner wall of the slide tube 36. The second piston 37 is fixedly connected to one end of the piston rod 38. The surface of the piston rod 38 is slidably connected to one end of the slide tube 36. The surface of the piston rod 38 is provided with a strip-shaped protrusion structure to limit the rotation of the piston rod 38. The other end of the piston rod 38 is fixedly connected to the clamp 4. The limiting component includes a second spring 39 and a positioning groove 310. The second spring 39 is located inside the second piston 37. One end of the second piston 37 is provided with a circular hole groove, and one end of the second spring 39 protrudes from the end of the second piston 37. The positioning groove 310 is fixedly installed on the side wall of the slide tube 36. The outer wall surface of the positioning groove 310 is provided with a hemispherical groove. The positioning groove 310 is engaged with a spherical protrusion 312. The spherical protrusion 312 is provided at one end of the elastic element 313. The elastic element 313 is connected to the launching unit 6. The elastic element 313 is an elastic metal and has a U-shaped structure.

[0041] This implementation scheme incorporates a balancing unit 3, with the launching unit 6 initially positioned at the bottom front of the drone body 1. This prevents the drone body 1 from interfering with the launch of the capture net, thus preventing the capture net and counterweight 7 from tangling around the launch unit 6's propeller blades when capturing a drone in front. The launch unit 6 generates recoil force the moment it launches the capture net. This recoil force allows the spherical protrusion 312 at one end of the elastic element 313 on one side of the launch unit 6 to overcome the locking force with the positioning groove 310. After the spherical protrusion 312 at one end of the elastic element 313 releases its lock with the positioning groove 310, the second piston 37 moves a certain distance inside the slide tube 36 under the push of the second spring 39. After the second piston 37 moves a certain distance, the channel between the connecting pipe 35 and the inside of the slide tube 36 is exposed, allowing the pressure pipe 31 to connect with the inside of the slide tube 36. The first spring 32... Under the action of the first spring 32, the first piston 33 can move. The first piston 33 can push the air or liquid medium inside the pressure tube 31 into the slide tube 36 through the connecting tube 35. Then, the medium inside the pressure tube 31 will push the second piston 37 to move. The second piston 37 can drive the clamp 4 to move backward through the piston rod 38. At the same time, the clamp 4 can drive the launching unit 6 to move backward through the pressure unit 5, so that the launching unit 6 can move to the center position of the abdomen of the drone body 1. This avoids the launching unit 6 being too far forward, which would cause the drone body 1 to tilt forward due to the weight of the captured drone after it is captured by the capture net, resulting in an unstable balance. The weight of the captured and suspended drone is much greater than the weight tilting force caused by the backward movement of the pressure unit, so as to compensate for the instability caused by the backward movement of the pressure unit.

[0042] refer to Figure 9-11The pressure unit 5 includes an exhaust assembly and a reset assembly. The exhaust assembly is connected to the launching unit 6 and is used to exhaust air into the launching unit 6. The exhaust assembly is connected to the reset assembly via a fixing ring 57, which is used to reset the exhaust assembly. Bolts are provided on the surface of the fixing ring 57, and the head of the fixing ring 57 is fixed to the surface of the exhaust assembly by bolts. The exhaust assembly includes a compression pipe 51, inside which is a third piston 52. A rubber ring is embedded in the outer wall of the third piston 52. One end of the third piston 52 is fixedly connected to a transmission rod 54. A third spring 53 is provided on the outside of one end of the transmission rod 54. A tailstock 55 is fixedly installed on one end of the compression pipe 51, and a dust cover 56 is connected to one end of the tailstock 55. The dust cover 56 is made of rubber and has a corrugated structure on its surface for telescopic movement. The surface of the transmission rod 54 has grooves, and the grooves on the surface of the transmission rod 54 have teeth inside. The reset assembly includes a rotating shaft. 59. The rotating shaft 59 is rotatably connected to the surface of the fixed ring 57. One end of the rotating shaft 59 is provided with a hexagonal groove for engaging with an external hexagonal groove wrench. A transmission gear 58 is keyed to the outside of the rotating shaft 59. The transmission gear 58 meshes with the surface of the transmission rod 54. A ratchet 512 is provided on one side of the transmission gear 58. The ratchet 512 is keyed to the rotating shaft 59. The surface of the ratchet 512 engages with a locking block 510 to limit the unidirectional rotation of the ratchet 512. A spring is embedded in the surface of the locking block 510 to elastically push the locking block 510 to rotate in the direction of the ratchet 512. A paddle 513 is fixedly installed at one end of the locking block 510. The connection between the locking block 510 and the paddle 513 is rotatably connected to the limiting shaft 514. The limiting shaft 514 is rotatably connected to the fixing ring 57. A micro switch 511 is installed on the surface of the fixing ring 57. The micro switch 511 is electrically connected to the control terminal. The telescopic end of the micro switch 511 abuts against the surface of the paddle 513.

[0043] This implementation scheme incorporates a pressure unit 5, which remotely drives a microswitch 511. The microswitch 511 extends, causing the lever 513 to depress. This lever 513 then rotates the locking block 510, allowing it to overcome the pressure of the top spring and disengage from the ratchet 512. The ratchet 512 then releases its restriction on the rotating shaft 59 and the transmission gear 58, allowing the gear to rotate freely. This disengages the transmission rod 54, which, under the action of the third spring 53, pushes the third piston 52 to move. The third piston 52 instantly pushes the air inside the compression tube 51 to the launching unit 6. The launching unit 6, driven by high-pressure air, instantly launches the counterweight 7. The counterweight 7 drives the capture net to be launched from inside the launching unit 6, thereby capturing the drone in front. After the drone body 1 is retracted, the micro switch 511 is controlled to retract, so that the locking block 510 can engage with the ratchet 512 under the action of the spring, thereby restricting the ratchet 512 to rotate only in one direction. By inserting a hexagonal wrench into the hexagonal groove at one end of the rotating shaft 59, the rotating shaft 59 can be rotated, and the rotating shaft 59 can drive the gear to rotate. The gear can drive the transmission rod 54 to move backward, and the transmission rod 54 can drive the third piston 52 to the initial position, and compress the third spring 53 for the next use. The pressure unit 5 of this device can activate the capture net without an external power source and can be used multiple times, improving the convenience of use.

[0044] refer to Figure 7-8The launching unit 6 includes an assembly head 61 and a drive assembly. The assembly head 61 is used to install the capture net. The drive assembly is located above one end of the assembly head 61 and is used to drive the assembly head 61 to rotate. The interior of the assembly head 61 is connected to the interior of the pressure assembly. Both sides of the assembly head 61 are rotatably connected to the connectors 610. The interiors of the connectors 610 are connected to each other and have a hollow structure. One end of the connectors 610 is fixedly connected to the pressure tube 31. Both sides of the assembly head 61 are fixedly connected to the elastic elements 313. A launching groove 62 is provided at one end of the interior of the assembly head 61. The launching groove 62 is radially oriented. A receiving groove 63 is provided inside the assembly head 61 for placing the capture net. The net has a tail wire groove 64 at its rear end, which is used to hold the tail wire of the capture net. The tail wire is fixedly connected to the rear end of the tail wire groove 64. A connecting cavity 65 is provided at the rear end of the tail wire groove 64. One end of the connecting cavity 65 is connected to the inside of the connector 610, and the other end of the connecting cavity 65 is connected to the ends of the four launching slots 62. The drive assembly includes a waterproof cover 69. The waterproof cover 69 is fixedly connected to the connector 610 on both sides by screws. A drive motor 68 is fixedly installed inside the waterproof cover 69. The drive motor 68 is electrically connected to the control terminal. A drive gear 67 is keyed to the output end of the drive motor 68. The drive gear 67 meshes with a gear ring 66, which is installed on the outside of the connector 610.

[0045] This implementation scheme features a launch unit 6. High-pressure airflow from the pressure unit 5 enters the connector 610 through a compression pipe 51, then flows into the connecting cavity 65. This propels the counterweights 7 in each launch slot 62. A drive motor 68 drives a drive gear 67, which in turn drives a gear ring 66. The gear ring 66 then drives an assembly head 61, causing it to face downwards, thus enabling the capture of drones below the main body 1. In addition, as the assembly head 61 rotates, it also causes the elastic element 313 to disengage from the spherical protrusion 312 and the positioning groove 310. Without recoil, the spherical protrusion 312 can also disengage from the positioning groove 310 through the rotation of the assembly head 61. This allows the launch unit 6 to automatically move backward to the center below the fuselage, maintaining the stability of the drone's rear suspension. At the same time, the connecting pipe 35 can suppress the flow of the medium inside the pressure pipe 31, providing a damping effect and preventing the launch unit 6 from moving backward momentarily, thus improving stability.

[0046] Working principle: When the UAV is cruising in the air, its onboard radio distance detection module continuously measures the relative distance to the target UAV ahead. Once the target enters the preset capture range, the ground or airborne control terminal immediately issues a capture command. The command first triggers the micro switch 511 inside the pressure unit 5, causing the transmission gear 58, which was originally locked by the ratchet 512, to release. The pre-compressed spring instantly pushes the piston, injecting high-pressure air from the compression pipe 51 into the launching unit 6 at high speed through the connecting pipe. The high-pressure gas pushes four counterweights 7 outward along the radial launching slots 62, causing the capture net stored between the launching slots 62 and the receiving slots 63 to quickly unfold, forming... A sufficiently large aerial net covers the target drone, achieving initial capture. Almost simultaneously, the recoil force generated by the release of high-pressure gas acts on the launching unit 6. This recoil force is transmitted through the elastic element 313, causing the spherical protrusion 312 at its end to overcome the locking resistance between itself and the positioning groove 310 of the slide tube 36. The positioning groove 310 releases the elastic element 313, and the piston assembly inside the balancing unit 3 unlocks. The piston rod 38, originally locked by the second spring 39 and the positioning mechanism, begins to slide backward. At this time, the first spring 32 releases its stored elastic potential energy, pushing the first piston 33 to expel the air or liquid medium in the pressure tube 31 through... The connecting pipe 35 is pressed into the sliding pipe 36, further pushing the second piston 37 and piston rod 38 to move backward. The piston rod 38, through the clamp 4, drives the entire pressure unit 5 and the launching unit 6 to slide smoothly horizontally from the lower front of the nose to directly below the belly of the aircraft. This ensures that the weight of the captured target UAV is vertically suspended on the vertical line where the center of gravity of the entire aircraft is located, completely eliminating the forward and downward eccentric moment generated at the moment of capture in the traditional forward launch scheme, and avoiding uncontrollable forward tilting of the aircraft. If the target UAV is still located in the area below the belly of the aircraft after the first capture, the control terminal can restart the drive motor 68, which drives the assembly head 61 to rotate downward through the meshing of the gear and the gear ring 66. The launch angle is adjusted by rotating the drone to achieve downward capture or precise recovery. After the mission ends and the drone returns, the maintenance personnel only need to use a hex wrench to rotate the shaft 59. The transmission gear 58 drives the transmission rod 54 and the third piston 52 to reset, recompress the spring and lock the ratchet 512, preparing for the next launch. By pushing the pressure unit 5 forward, the spherical protrusion 312 engages with the positioning groove 310, and the balance unit 3 is reset. The entire working cycle does not require an external power source. It only uses recoil, spring potential energy and air pressure transmission to complete the launch, center of gravity adjustment, angle adjustment and reset, ensuring that the drone maintains a stable attitude before, during and after capture.

[0047] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A drone capture device based on radio distance detection, characterized in that, The device includes a drone body (1), a bracket (2) is bolted to the bottom of the drone body (1), a balancing unit (3) is connected to the bottom of the bracket (2), there are two balancing units (3), the two balancing units (3) are used to balance the drone body (1), and the two balancing units (3) are symmetrically distributed on both sides of the bottom of the drone body (1), a pressure unit (5) is provided between the two balancing units (3), a clamp (4) is fixedly installed on the outside of the pressure unit (5), the clamp (4) is connected to the balancing unit (3), a launch unit (6) is provided at one end of the pressure unit (5), the pressure unit (5) is used to provide pressure to the launch unit (6), the inside of the pressure unit (5) is connected to the inside of the launch unit (6), a capture net is assembled inside the launch unit (6), and the four ends of the capture net are connected to the counterweight (7), the counterweight (7) is embedded inside the launch unit (6).

2. The UAV capture device based on radio distance detection according to claim 1, characterized in that, The balancing unit (3) includes a piston assembly and a limiting assembly. The piston assembly is engaged with the C-shaped slots on both sides of the connecting slot (311), and the connecting surface is provided with a set bolt to fix the piston assembly. The piston assembly is used to drive the pressure unit (5) to move back and forth in the horizontal direction. The limiting assembly is installed on the surface of the piston assembly and is used to cooperate with the launching unit (6) to limit the piston assembly.

3. The UAV capture device based on radio distance detection according to claim 2, characterized in that, The piston assembly includes a pressure tube (31) with a hollow interior. A first spring (32) is located at one end of the pressure tube (31), and a first piston (33) is located at the other end of the first spring (32). The outer wall of the first piston (33) is tightly fitted to the inner wall of the pressure tube (31). An exhaust groove (34) is located at one end of the pressure tube (31). The exhaust groove (34) is a circular groove, and one side of the exhaust groove (34) is connected to one end of a connecting pipe (35). (35) The other end is connected to the side wall of one end of the slide tube (36). The slide tube (36) is provided with a second piston (37). The outer wall of the second piston (37) is tightly fitted with the inner wall of the slide tube (36). The second piston (37) is fixedly connected to one end of the piston rod (38). The surface of the piston rod (38) is slidably connected to one end of the slide tube (36). The surface of the piston rod (38) is provided with a strip-shaped protrusion structure to restrict the rotation of the piston rod (38). The other end of the piston rod (38) is fixedly connected to the clamp (4).

4. The UAV capture device based on radio distance detection according to claim 2, characterized in that, The limiting component includes a second spring (39) and a positioning groove (310). The second spring (39) is located inside the second piston (37). One end of the second piston (37) is provided with a circular hole groove, and one end of the second spring (39) protrudes from the end of the second piston (37). The positioning groove (310) is fixedly installed on the side wall of the slide tube (36). The outer surface of the positioning groove (310) is provided with a hemispherical groove. The positioning groove (310) is engaged with a spherical protrusion (312). The spherical protrusion (312) is located at one end of the elastic element (313). The elastic element (313) is connected to the launching unit (6). The elastic element (313) is an elastic metal and has a U-shaped structure.

5. The UAV capture device based on radio distance detection according to claim 1, characterized in that, The pressure unit (5) includes an exhaust assembly and a reset assembly. The exhaust assembly is connected to the launching unit (6). The exhaust assembly is used to exhaust air into the launching unit (6). The exhaust assembly is connected to the reset assembly through a fixing ring (57). The reset assembly is used to reset the exhaust assembly. The surface of the fixing ring (57) is provided with bolts. The head of the fixing ring (57) is fixed to the surface of the exhaust assembly by bolts.

6. The UAV capture device based on radio distance detection according to claim 5, characterized in that, The exhaust assembly includes a compression pipe (51), inside which a third piston (52) is provided. A rubber ring is embedded in the outer wall of the third piston (52). One end of the third piston (52) is fixedly connected to a transmission rod (54). A third spring (53) is provided on the outside of one end of the transmission rod (54). A tailstock (55) is fixedly installed on one end of the compression pipe (51). A dust cover (56) is connected to one end of the tailstock (55). The dust cover (56) is made of rubber and has a corrugated structure on its surface for telescopic movement. The surface of the transmission rod (54) has a groove, and the groove on the surface of the transmission rod (54) has teeth inside.

7. The UAV capture device based on radio distance detection according to claim 5, characterized in that, The reset assembly includes a rotating shaft (59), which is rotatably connected to the surface of a fixed ring (57). One end of the rotating shaft (59) is provided with a hexagonal groove for engaging with an external hexagonal groove wrench. A transmission gear (58) is keyed to the outside of the rotating shaft (59). The transmission gear (58) meshes with the surface of a transmission rod (54). A ratchet (512) is provided on one side of the transmission gear (58). The ratchet (512) is keyed to the rotating shaft (59). The surface of the ratchet (512) engages with a locking block (510). The locking block (510) is used to limit the ratchet (512). 2) Unidirectional rotation. A spring is embedded on the surface of the locking block (510) to elastically push the locking block (510) to rotate in the direction of the ratchet (512). A paddle (513) is fixedly installed at one end of the locking block (510). The connection between the locking block (510) and the paddle (513) is rotatably connected to the limiting shaft (514). The limiting shaft (514) is rotatably connected to the fixing ring (57). A micro switch (511) is installed on the surface of the fixing ring (57). The micro switch (511) is electrically connected to the control terminal. The telescopic end of the micro switch (511) abuts against the surface of the paddle (513).

8. The UAV capture device based on radio distance detection according to claim 1, characterized in that, The launching unit (6) includes an assembly head (61) and a driving assembly. The assembly head (61) is used to install a capture net. The driving assembly is located above one end of the assembly head (61) and is used to drive the assembly head (61) to rotate. The interior of the assembly head (61) is connected to the interior of the pressure assembly. The two sides of the assembly head (61) are rotatably connected to the connecting head (610). The interior of the connecting head (610) is connected to the interior of the connecting head (610). The interior of the connecting head (610) has a hollow structure. One end of the connecting head (610) is fixedly connected to the pressure tube (31). The two sides of the assembly head (61) are fixedly connected to the elastic element (313).

9. The UAV capture device based on radio distance detection according to claim 8, characterized in that, The assembly head (61) has a launching slot (62) at one end, which is radial. The assembly head (61) also has a receiving slot (63) inside, which is used to place the capture net. The receiving slot (63) has a tail line slot (64) at the rear end, which is used to place the tail line of the capture net. The tail line of the capture net is fixedly connected to the rear end of the tail line slot (64). The tail line slot (64) has a connecting cavity (65) at the rear end, which is connected to the inside of the connector (610) at one end and to the ends of the four launching slots (62) at the other end.

10. A drone capture device based on radio distance detection according to claim 8, characterized in that, The drive assembly includes a waterproof cover (69), which is fixedly connected to the connector (610) on both sides by screws. A drive motor (68) is fixedly installed inside the waterproof cover (69). The drive motor (68) is electrically connected to the control terminal. A drive gear (67) is keyed to the output end of the drive motor (68). The drive gear (67) meshes with a gear ring (66), which is installed outside the connector (610).

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