A counter-drone aircraft based on rotary cutting

Abstract

The application discloses a kind of anti-unmanned aerial vehicle based on rotary cutting, belong to unmanned aerial vehicle countermeasure technical field.Flight vehicle includes guide head cabin, steel rope cabin, instrument cabin, power cabin, rudder cabin and umbrella package cabin;Guide head cabin is equipped with infrared homing head;Steel rope cabin can independently rotate under the drive of motor relative to front and rear cabin section and release flexible steel rope wound in its inside, motor drives steel rope cabin shell high-speed rotation simultaneously with flexible steel rope high-speed rotation, to realize rotary cutting to target unmanned aerial vehicle;Instrument cabin is equipped with main power supply, control computer, data link and inertial navigation device inside, power cabin provides cruising power for flight vehicle;Machine cabin is equipped with rudder that controls wing rotation, umbrella package cabin is equipped with pressurizing device that pressurizes umbrella package cabin;The application carries out soft killing to target unmanned aerial vehicle, wide application range, can effectively solve the problem that current anti-unmanned aerial vehicle flight vehicle cost-effectiveness is relatively low.

Description

Technical Field

[0001] This invention relates to the field of drone countermeasures technology, and specifically to a rotary cutting-based anti-drone aircraft. Background Technology

[0002] With the rapid development of drone technology and its widespread adoption in various fields, the potential threats posed by drones are becoming increasingly prominent.

[0003] Existing anti-drone systems employ various technologies to detect, identify, interfere with, and destroy illegally intruding drones, thereby eliminating the drone threat and protecting personnel and property. These technologies encompass radio jamming, laser strikes, microwave attacks, and net capture, among others. However, these methods have limitations. For instance, radio jamming is less effective against drones using frequency hopping or spread spectrum technologies; its effective range is limited, making it difficult to deal with long-range drones; laser strikes are costly and pose safety hazards in urban areas, have limited sustained illumination capabilities, and are difficult to use to track and engage high-speed drones; net capture equipment is bulky and heavy, affecting the aircraft's endurance and maneuverability, and has a low success rate in capturing high-speed, highly maneuverable drones; and it requires complex recovery and processing after capture.

[0004] Therefore, overcoming the aforementioned technical deficiencies is a problem that urgently needs to be solved by those skilled in the art. In recent years, technologies that utilize aircraft to counter drones have gradually emerged. These technologies can quickly strike target drones and possess the ability to autonomously search, identify, and attack targets, providing new ideas for drone countermeasures. Summary of the Invention

[0005] In view of this, the present invention provides an anti-drone aircraft based on rotational cutting. The flexible steel cable inside the combat cabin rotates with the internal rotating shaft. After the aircraft approaches the target, the flexible steel cable is released through the internal rotating shaft. Then, the motor drives the outer shell of the combat cabin to rotate at high speed, which in turn drives the flexible steel cable to rotate at high speed, thereby realizing the rotational cutting of the target drone. The aircraft is also equipped with a recovery parachute, which allows the aircraft to be recovered and reused after the drone is damaged.

[0006] An anti-drone aircraft based on rotary cutting includes a guidance head compartment, a combat compartment, an instrument compartment, a power compartment, a servo compartment, and a parachute compartment;

[0007] The guidance head compartment is equipped with an infrared guidance head;

[0008] The combat cabin can rotate independently relative to the front and rear sections under the drive of the motor and release the flexible steel rope wrapped inside it. The motor drives the outer shell of the combat cabin to rotate at high speed, which in turn drives the flexible steel rope to rotate at high speed, thereby achieving rotational cutting of the target UAV.

[0009] The instrument compartment is equipped with a main power supply for powering the aircraft's equipment, a control computer for power distribution, launch, and flight control of the aircraft, a data link for communication between the aircraft and the ground, and an inertial navigation system for measuring the aircraft's attitude and acceleration information.

[0010] The power compartment is equipped with a turbojet engine and fuel tank that provide loitering power for the aircraft. The outer wall of the power compartment is fitted with foldable wings. A nozzle is located at the rear of the power compartment and extends through the servo gear compartment.

[0011] The servo compartment is equipped with a servo mechanism for controlling the rotation of the servo wings.

[0012] The parachute compartment is equipped with a pressurization device to pressurize the parachute compartment. The parachute is placed in a ring inside the parachute compartment, and a sealing cap is provided at the rear of the parachute compartment.

[0013] Furthermore, the infrared seeker is installed at the interface between the seeker compartment and the combat compartment, with a circular hole at the center of the interface, on which a bearing is installed.

[0014] Furthermore, the combat cabin includes a combat cabin shell, a motor, an outer rotating shaft, an inner rotating shaft, bearings, guide tubes, and flexible steel cables. The motor is installed at the interface between the combat cabin and the instrument cabin, with a circular hole at the center of the interface, on which a bearing is installed. The inner rotating shaft passes through the bearing hole at the interface between the combat cabin and the front and rear cabins, connecting the combat cabin and the front and rear cabins as a whole. The outer rotating shaft is sleeved on the inner rotating shaft, and the inner and outer rotating shafts are driven to rotate separately by the motor. N flexible steel cables are wound on the outer rotating shaft, and the ends of the N flexible steel cables pass through N guide tubes. The N guide tubes are installed on the inner wall of the combat cabin shell, with the installation points located on the axial circle and set at equal intervals of X°. The shell has openings at the installation points, and the flexible steel cables extend from the openings. The combat cabin shell and the front and rear cabin sections are all clearance fit. The shell is installed on the inner rotating shaft, and the shell can rotate synchronously with the inner rotating shaft.

[0015] Furthermore, the main power supply in the instrument compartment is installed at the interface between the instrument compartment and the power compartment, the control computer is installed on the main power supply, and the data link is installed on the control computer; the inertial navigation device is installed on the data link, and the instrument compartment and the power compartment are assembled to form an assembly.

[0016] Furthermore, the turbojet engine in the power compartment is installed at the interface between the power compartment and the servo compartment. A circular hole is opened at the center of the interface. A nozzle is installed at the tail of the engine, extending from the circular hole and penetrating the servo compartment. The fuel tank is installed at the interface between the power compartment and the instrument compartment. The fuel tank and the turbojet engine are directly connected through fuel lines. M foldable wings are installed on the outer wall of the power compartment shell.

[0017] Furthermore, the servo compartment contains four servos, which are installed on the inner wall of the servo housing in an "X" shape. Each servo has a round hole at its installation position for the servo shaft to pass through. Four servo wings are installed on the outer wall of the servo compartment housing and are assembled with the servo shaft.

[0018] Furthermore, the flight process of the aircraft includes five steps: aircraft launch, aircraft flight, aircraft target lock, aircraft attack target, and aircraft recovery.

[0019] Aircraft launch: The aircraft folds its wings and rudders and places them into the launch tube. After receiving the launch command, the ejection device ejects the aircraft out of the tube. The wings and rudders automatically unfold after the aircraft leaves the tube.

[0020] Aircraft flight: When the aircraft is a certain distance from the ground, the control computer sends an ignition command to the turbojet engine ignition device. The turbojet engine ignites, and the aircraft enters the flight phase to cruise. During the flight, the control computer controls the servo motor to deflect the rudder to adjust the aircraft's attitude and fly along the predetermined route.

[0021] Aircraft target locking: During flight, the infrared seeker generates images that can be transmitted to the ground via data link. The drone can lock onto the target through a human-in-the-loop method or through autonomous identification by the seeker.

[0022] Aircraft Attack Target: After the seeker locks onto the UAV target, the aircraft continues to fly closer to the target. Once it reaches a certain distance from the target, the control computer sends a command to the motors located in the combat cabin. The motors drive the outer shaft to rotate, releasing the N flexible steel cables wrapped around the outer shaft. These flexible steel cables extend outside the combat cabin shell through guide tubes. After all N flexible steel cables have been released, the control computer sends a command to the motors, which drive the inner shaft to rotate at high speed. The rotation of the inner shaft simultaneously drives the combat cabin shell and the flexible steel cables to rotate synchronously. As the aircraft approaches the target, the high-speed rotating flexible steel cables spin and cut the UAV target, shooting it down.

[0023] Aircraft Recovery: After the aircraft shoots down the drone target, the control computer stops the turbojet engine. After the turbojet engine stops working, the control computer sends a command to the pressurization device located in the parachute compartment. Under the action of high-pressure gas, the parachute and sealing cap are pushed out, the parachute opens, and the aircraft decelerates and falls. The aircraft's position is determined by telemetry information transmitted back via data link, and the aircraft recovery is completed. After recovery, the aircraft is inspected, some damaged parts are replaced, the engine is refueled, the flexible steel cable is retrieved to the outer shaft, the parachute is retrieved into the parachute compartment, and the tail sealing cap is replaced and installed. After this, the aircraft can be put back into use.

[0024] Beneficial effects:

[0025] 1. The combat cabin of this invention uses the release and high-speed rotation of a flexible steel cable to achieve rotational cutting of the target UAV. It has no hard-kill warheads such as explosives, and will not cause secondary damage after the target UAV is destroyed. It can be used in areas with high traffic, improves the safety of use after the target UAV is destroyed, and has a wide range of applications.

[0026] 2. Compared with other anti-drone aircraft, this invention can destroy the target drone while effectively recovering and reusing the aircraft, effectively solving the problem of the relatively low cost-effectiveness of current anti-drone aircraft.

[0027] 3. The length of the flexible steel rope of this invention can be adjusted according to actual combat needs, and it can cut multiple drone targets at the same time. Compared with traditional anti-drone aircraft, it can effectively deal with drone swarm attacks.

[0028] 4. This invention uses a high-speed rotating flexible steel cable to cut and destroy the target drone, enabling precise strikes and ensuring that the drone's key components are cut and destroyed, rendering it incapable of flight, thus improving the effectiveness and success rate of intercepting the target drone. Attached Figure Description

[0029] Figure 1 This is a schematic diagram of the overall structure of an anti-drone aircraft based on rotary cutting.

[0030] The components are: 1-Guidance head compartment, 2-Combat compartment, 3-Outer pivot, 4-Instrument compartment, 5-Control computer, 6-Power compartment, 7-Servo compartment, 8-Parachnoid compartment, 9-Parachnoid, 10-Nozzle, 11-Infrared seeker, 12-Inner pivot, 13-Flexible steel cable, 14-Guide tube, 15-Motor, 16-Inertial navigation system, 17-Data link, 18-Main power supply, 19-Wing, 20-Fuel tank, 21-Fuel pipe, 22-Turbojet engine, 23-Rudder wing, 24-Servo, 25-Pressure device, 26-Sealing plug. Detailed Implementation

[0031] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0032] Example 1

[0033] See appendix Figure 1 This embodiment provides an anti-drone aircraft based on rotary cutting, which includes, in sequence from the head: a guidance head compartment 1, a combat compartment 2, an instrument compartment 4, a power compartment 6, a servo compartment 7, and a parachute compartment 8.

[0034] The guidance head compartment is equipped with an infrared guidance head 11, which is installed at the interface between the guidance head compartment 1 and the combat compartment 2. A circular hole is opened at the center of the interface, and a bearing is installed on it.

[0035] The combat compartment 2 is equipped with a motor 15, which is installed at the interface between the combat compartment 2 and the instrument compartment 4. A circular hole is opened at the center of the interface, and a bearing is installed on it. The combat compartment contains two rotating shafts, namely an inner rotating shaft 12 and an outer rotating shaft 3. The inner rotating shaft 12 is installed through the bearing hole at the interface between the combat compartment 2 and the front and rear compartments, connecting the combat compartment 2 and the front and rear compartments as a whole. The outer rotating shaft 3 is fitted on the inner rotating shaft 12. The inner and outer rotating shafts can be driven to rotate separately by the motor 15. Three flexible steel ropes 13 are wound on the outer rotating shaft 3. The ends of the three flexible steel ropes 13 pass through three guide tubes 14. The three guide tubes 14 are installed on the inner wall of the outer shell of the combat compartment 2. The installation points are located on the axial circle and are placed at equal intervals of 120°. The outer shell is perforated at the installation point, and the flexible steel ropes 13 can extend out from the perforated point. The outer shell of the combat compartment 2 and the front and rear compartments are all clearance fit. The outer shell is installed on the inner rotating shaft 12 and can rotate with the inner rotating shaft 12.

[0036] The instrument compartment 4 contains a main power supply 18, which is installed at the interface between the instrument compartment 4 and the power compartment 6. The control computer 5 is installed on the main power supply 18, and the data link 17 is installed on the control computer 5. The inertial navigation device 16 is installed on the data link 17. The instrument compartment 4 and the power compartment 6 are assembled to form an assembly.

[0037] The power compartment 6 houses a turbojet engine 22 and a fuel tank 20. The turbojet engine 22 is installed at the interface between the power compartment 6 and the servo compartment 7, with a circular hole at the center of the interface. The engine 22 has a nozzle 10 at its tail, which extends from the circular hole and passes through the servo compartment 7 and the parachute compartment 8. The fuel tank 20 is installed at the interface between the power compartment 6 and the instrument compartment 4. The fuel tank 20 and the turbojet engine 22 are directly connected through a fuel pipe 21. Two foldable wings 19 are installed on the outer wall of the power compartment 6, positioned at 180° on both sides of the aircraft.

[0038] The servo compartment 7 contains four servos 24, which are mounted on the inner wall of the servo compartment 7 and are arranged in an "X" shape. Each servo 24 has a round hole at its mounting position for the servo shaft to pass through. The servo wing 23 is mounted on the outer wall of the servo compartment 24 and is assembled with the servo shaft.

[0039] The parachute compartment 8 is equipped with a pressurization device 25, which is installed at the interface between the servo compartment 7 and the parachute compartment 8; the parachute 9 is placed in a ring inside the parachute compartment 8; and a sealing plug 26 is installed at the rear of the parachute compartment 8.

[0040] Example 2:

[0041] See appendix Figure 1This embodiment provides an aircraft based on a rotary cutting and destruction drone and its recovery method. The workflow of the aircraft as described in Embodiment 1 includes five steps: aircraft launch, aircraft flight, aircraft target locking, aircraft attacking the target, and aircraft recovery.

[0042] Aircraft launch: The aircraft of this invention can fold its wings 19 and rudder wings 23 and place them into the launch tube. After receiving the launch command, the ejection device ejects the aircraft out of the tube. The wings 19 and rudder wings 23 automatically unfold after the aircraft leaves the tube, and the aircraft launch process ends.

[0043] Aircraft flight: The control computer 5 calculates the aircraft's position, speed, and attitude information in real time based on the data measured by the inertial navigation device 16. When the aircraft is 20m above the ground, the control computer 5 sends an ignition command to the turbojet engine 22 ignition device. The turbojet engine 22 ignites, and the aircraft enters the flight phase to cruise. During the flight, the control computer 5 controls the servo motor 24 to deflect the rudder 19 to adjust the aircraft's attitude and fly along the predetermined route.

[0044] Aircraft target locking: During the flight of the aircraft, the image generated by the infrared seeker 11 can be transmitted to the ground via the data link 17. The UAV target can be locked by human-in-the-loop method or by the seeker autonomously identifying the UAV target.

[0045] Aircraft Attack Target: After the seeker 11 locks onto the UAV target, the aircraft continues to fly and approach the target. When it is 200m away from the target, the control computer 5 sends a command to the motor 15 located in the combat cabin 2. The motor 15 drives the outer shaft 3 to rotate, causing the three flexible steel cables 13 wrapped around the outer shaft 3 to be released. The flexible steel cables 13 are extended outside the shell of the combat cabin 2 through the guide tube 14. After the three flexible steel cables 13 are released, the control computer 5 sends a command to the motor 15. The motor 15 drives the inner shaft 12 to rotate at high speed. While the inner shaft 12 is rotating, it drives the shell of the combat cabin 2 and the flexible steel cables 13 to rotate synchronously. After the aircraft approaches the target, the high-speed rotating flexible steel cables 13 rotate and cut the UAV target, shooting down the UAV.

[0046] The materials used in drones are generally carbon fiber, and the shear strength of a typical orthogonal layup of carbon fiber is τ = 100 MPa. According to the shear force formula F... s =τA, where A is the area of ​​the cutting surface. Calculated based on a cutting thickness of 10mm and a cutting length of 100mm, the shearing force F required for flexible steel cable cutting a drone is... s The value is 100kN, therefore, the centrifugal force F generated by the rotation of the steel rope is... c >F s That's it. The centrifugal force F of the steel cable. c =mω 2r, the selected flexible steel ropes 13 are all toothed round steel ropes, with an extended length of 2m after unfolding and a linear density of 1kg / m. The length of the steel rope involved in cutting is 0.1m. It is calculated that the required speed of motor 15 is greater than 6750rpm. Therefore, the selected motor 15 has a speed of 10000rpm.

[0047] Aircraft Recovery: After the aircraft shoots down the UAV target, the control computer 5 controls the turbojet engine 22 to stop working. After the turbojet engine 22 stops working, the control computer 5 sends a command to the pressurization device 25 located in the parachute compartment 8. Under the action of high-pressure gas, the parachute 9 and the sealing plug 26 are pushed out. The parachute 9 opens, the aircraft decelerates and falls. The aircraft's position is determined by the telemetry information transmitted back by the data link 17, and the aircraft recovery is completed. After recovery, the aircraft is inspected, some damaged parts are replaced, the fuel tank 20 is refueled, the flexible steel cable 13 is retrieved to the outer pivot 3, the parachute 9 is retrieved into the parachute compartment 8, and the tail sealing plug 26 is replaced and installed. After that, it can be put back into use.

[0048] In summary, the above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A rotary cutting-based anti-drone aircraft, characterized in that, It includes the guidance head compartment, steel cable compartment, instrument compartment, power compartment, servo compartment, and parachute compartment; The guidance head compartment is equipped with an infrared guidance head; The steel cable cabin can rotate independently relative to the front and rear sections under the drive of the motor and release the flexible steel cable wrapped inside it. The motor drives the outer shell of the steel cable cabin to rotate at high speed, which in turn drives the flexible steel cable to rotate at high speed, thereby achieving rotational cutting of the target UAV. The instrument compartment is equipped with a main power supply for powering the aircraft's equipment, a control computer for power distribution, launch, and flight control of the aircraft, a data link for communication between the aircraft and the ground, and an inertial navigation system for measuring the aircraft's attitude and acceleration information. The power compartment is equipped with a turbojet engine and fuel tank that provide loitering power for the aircraft. The outer wall of the power compartment is fitted with foldable wings. A nozzle is located at the rear of the power compartment and extends through the servo gear compartment. The servo compartment is equipped with a servo mechanism for controlling the rotation of the servo wings. The parachute compartment is equipped with a pressurization device to pressurize the parachute compartment. The parachute is placed in a ring inside the parachute compartment, and a sealing plug is provided at the rear of the parachute compartment. The infrared seeker is installed at the interface between the seeker head compartment and the steel cable compartment. A circular hole is opened at the center of the interface, and a bearing is installed on it. The steel rope cabin includes a steel rope cabin shell, a motor, an outer rotating shaft, an inner rotating shaft, bearings, guide tubes, and flexible steel ropes. The motor is installed at the interface between the steel rope cabin and the instrument cabin, with a circular hole at the center of the interface, on which a bearing is installed. The inner rotating shaft passes through the bearing hole at the interface between the steel rope cabin and the front and rear cabins, connecting the steel rope cabin and the front and rear cabins as a whole. The outer rotating shaft is sleeved on the inner rotating shaft, and the inner and outer rotating shafts are driven to rotate separately by the motor. N flexible steel ropes are wound on the outer rotating shaft, and the ends of the N flexible steel ropes pass through N guide tubes. The N guide tubes are installed on the inner wall of the steel rope cabin shell, with the installation points located on the axial circle and set at equal intervals of X°. The shell has openings at the installation points, and the flexible steel ropes extend from the openings. The steel rope cabin shell and the front and rear cabin sections are clearance fit. The shell is installed on the inner rotating shaft, and the shell can rotate synchronously with the inner rotating shaft.

2. The anti-drone aircraft based on rotary cutting as described in claim 1, characterized in that, The main power supply in the instrument compartment is installed at the interface between the instrument compartment and the power compartment. The control computer is installed on the main power supply, and the data link is installed on the control computer. The inertial navigation device is installed on the data link. The instrument compartment and the power compartment are assembled to form an assembly.

3. The anti-drone aircraft based on rotary cutting as described in claim 2, characterized in that, The turbojet engine in the power compartment is installed at the interface between the power compartment and the servo compartment. A circular hole is opened at the center of the interface. A nozzle is installed at the tail of the engine, which extends from the circular hole and passes through the servo compartment. The fuel tank is installed at the interface between the power compartment and the instrument compartment. The fuel tank and the turbojet engine are directly connected through fuel pipes. M foldable wings are installed on the outer wall of the power compartment shell.

4. The anti-drone aircraft based on rotary cutting as described in claim 3, characterized in that, The servo compartment contains four servos, which are installed on the inner wall of the servo housing in an "X" shape. Each servo has a round hole at its installation position for the servo shaft to pass through. Four servo wings are installed on the outer wall of the servo compartment housing and are assembled with the servo shaft.

5. A rotary cutting-based anti-drone aircraft as described in claim 3 or 4, characterized in that, The flight process of the aircraft includes five steps: aircraft launch, aircraft flight, aircraft target lock, aircraft attack target, and aircraft recovery. Aircraft launch: The aircraft folds its wings and rudders and places them into the launch tube. After receiving the launch command, the ejection device ejects the aircraft out of the tube. The wings and rudders automatically unfold after the aircraft leaves the tube. Aircraft flight: When the aircraft is a certain distance from the ground, the control computer sends an ignition command to the turbojet engine ignition device. The turbojet engine ignites, and the aircraft enters the flight phase to cruise. During the flight, the control computer controls the servo motor to deflect the rudder to adjust the aircraft's attitude and fly along the predetermined route. Aircraft target locking: During flight, the infrared seeker generates images that can be transmitted to the ground via data link. The drone can lock onto the target through a human-in-the-loop method or through autonomous identification by the seeker. Aircraft Attack Target: After the seeker locks onto the drone target, the aircraft continues to fly closer to the target. Once it reaches a certain distance from the target, the control computer sends a command to the motor located in the cable chute. The motor drives the outer shaft to rotate, releasing the N flexible steel cables wound on the outer shaft. The flexible steel cables extend outside the cable chute shell through the guide tube. After the N flexible steel cables are released, the control computer sends a command to the motor, which drives the inner shaft to rotate at high speed. The rotation of the inner shaft simultaneously drives the outer shell of the cable chute and the flexible steel cables to rotate synchronously. After the aircraft approaches the target, the high-speed rotating flexible steel cables rotate and cut the drone target, shooting it down. Aircraft Recovery: After the aircraft shoots down the drone target, the control computer stops the turbojet engine. After the turbojet engine stops working, the control computer sends a command to the pressurization device located in the parachute compartment. Under the action of high-pressure gas, the parachute and sealing cap are pushed out, the parachute opens, and the aircraft decelerates and falls. The aircraft's position is determined by telemetry information transmitted back via data link, and the aircraft recovery is completed. After recovery, the aircraft is inspected, some damaged parts are replaced, the engine is refueled, the flexible steel cable is retrieved to the outer shaft, the parachute is retrieved into the parachute compartment, and the tail sealing cap is replaced and installed. After this, the aircraft can be put back into use.

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