Anti-unmanned aerial vehicle aircraft based on rotary cutting

Abstract

The invention discloses an anti-unmanned aerial vehicle aircraft based on rotary cutting, and belongs to the technical field of unmanned aerial vehicle countering. The aircraft comprises a seeker cabin, a steel rope cabin, an instrument cabin, a power cabin, a steering engine cabin and a parachute pack cabin. An infrared seeker is arranged in the seeker cabin; the steel rope cabin can independently rotate relative to the front cabin section and the rear cabin section under driving of the motor and release the flexible steel rope wound in the steel rope cabin, the motor drives a shell of the steel rope cabin to rotate at a high speed and drives the flexible steel rope to rotate at a high speed, and therefore rotary cutting of the target unmanned aerial vehicle is achieved. A main power supply, a control computer, a data chain and an inertial navigation device are arranged in the instrument cabin; the power cabin provides patrol flight power for the aircraft; a steering engine for controlling the rudder wings to rotate is arranged in the cabin, and a pressurizing device for pressurizing the parachute pack cabin is arranged in the parachute pack cabin; the target unmanned aerial vehicle is softly killed, the application range is wide, and the problem that the cost-effectiveness ratio of an existing anti-unmanned aerial vehicle aircraft is relatively low can be effectively solved.

Description

Technical Field

[0001] The present invention relates to the technical field of UAV countermeasures, and in particular to an anti-UAV aircraft based on rotary cutting. Background Art

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

[0003] Existing anti-drone systems employ various techniques to detect, identify, interfere with, and destroy intruding drones, thereby eliminating the threat and protecting personnel and property. These techniques include radio jamming, laser strikes, microwave attacks, and net capture. However, these methods have limitations. For example, radio jamming is not effective against drones using frequency hopping and spread spectrum technology; their range is limited, making them ineffective against long-range drones; laser strikes are expensive and pose safety risks in urban areas; their sustained illumination capability is limited, making it difficult to track and strike high-speed drones; and net capture equipment is bulky and heavy, affecting the carrier's endurance and maneuverability, resulting in a low success rate for capturing high-speed, highly maneuverable drones. Furthermore, net capture equipment requires recovery and disposal, making it complex to operate.

[0004] Therefore, how to overcome the above technical deficiencies is an urgent problem to be solved by those skilled in the art. In recent years, the technology of using aircraft to counter drones has gradually emerged. It can quickly strike target drones and has the ability to autonomously search, identify and attack targets, providing new ideas for countering drones. Summary of the Invention

[0005] In view of this, the present invention provides an anti-UAV aircraft based on rotary cutting. The flexible steel rope in the combat cabin rotates with the internal rotating shaft. After the aircraft approaches the target, the flexible steel rope is released through the internal rotating shaft, and then the motor drives the combat cabin shell to rotate at high speed and drives the flexible steel rope to rotate at high speed at the same time, thereby realizing rotary cutting of the target UAV; the aircraft is also equipped with a recovery parachute, and after the UAV is destroyed, the aircraft can be recovered and reused.

[0006] An anti-UAV aircraft based on rotary cutting, comprising a seeker cabin, a combat cabin, an instrument cabin, a power cabin, a steering gear cabin and a parachute cabin;

[0007] An infrared seeker is provided in the seeker cabin;

[0008] The combat cabin is driven by a motor to independently rotate relative to the front and rear cabin sections and release the flexible steel rope wrapped inside it. The motor drives the combat cabin shell to rotate at high speed and drives the flexible steel rope to rotate at high speed, thereby achieving rotary cutting of the target UAV.

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

[0010] The power cabin is provided with a turbojet engine and a fuel tank for providing cruising power for the aircraft, and the outer wall of the power cabin shell is provided with a foldable wing; the tail of the power cabin is provided with a nozzle, which passes through the steering gear cabin;

[0011] The steering gear compartment is provided with a steering gear for controlling the rotation of the rudder blades;

[0012] A pressurizing device for pressurizing the parachute cabin is provided in the parachute cabin, the parachute bag is placed in a ring shape inside the parachute cabin, and a sealing plugging cover is provided at the tail of the parachute cabin.

[0013] Furthermore, the infrared seeker is installed at the interface between the seeker cabin and the combat cabin, and a circular hole is opened 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, a bearing, a guide tube and a flexible steel rope; the motor is installed at the interface between the combat cabin and the instrument cabin, and a circular hole is opened at the center of the interface, on which a bearing is installed; the inner rotating shaft is installed through the bearing hole at the junction of the combat cabin and the front and rear cabins to connect the combat cabin with 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 around the outer rotating shaft, and the ends of the N flexible steel ropes pass through N guide tubes respectively, and the N guide tubes are installed on the inner wall of the combat cabin shell, and the installation points are located on the axial circle and are arranged at equal intervals of X°. The shell at the installation point has a hole, and the flexible steel rope extends from the hole; the combat cabin shell and the front and rear cabin sections are all clearance-fitted, and 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 cabin is installed at the interface between the instrument cabin and the power cabin, 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 cabin and the power cabin 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 steering gear compartment, a circular hole is opened at the center of the interface, a nozzle is installed at the tail of the engine, the nozzle extends from the circular hole, and the nozzle passes through the steering gear compartment; the oil tank is installed at the interface between the power compartment and the instrument compartment; the oil tank is directly connected to the turbojet engine through an oil pipe; M foldable wings are installed on the outer wall of the power compartment shell.

[0017] Furthermore, the steering gear cabin is equipped with four servos, which are installed on the inner wall of the servo gear housing and are distributed in an "X" shape. Circular holes are opened at the servo gear installation positions for passing the rudder shaft; four rudder wings are installed on the outer wall of the servo gear cabin housing and assembled with the rudder shaft.

[0018] Furthermore, the workflow 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, and 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 for cruising. During the flight, the control computer controls the steering gear to deflect the rudder wings to adjust the aircraft's attitude and fly along the predetermined route;

[0021] Aircraft locks on target: During the flight of the aircraft, the image generated by the infrared seeker can be transmitted to the ground via the data link, and the UAV target can be locked by the human-in-the-loop method or the seeker can lock on the UAV target by autonomous recognition;

[0022] Aircraft attack target: After the seeker locks onto the UAV target, the aircraft continues to fly closer to the target. After reaching a certain distance from the target, the control computer issues a command to the motor located in the combat cabin. The motor drives the outer shaft to rotate, releasing the N flexible steel ropes wrapped around the outer shaft. The flexible steel ropes are then extended out of the combat cabin shell through the guide tube. After the N flexible steel ropes are released, the control computer issues a command to the motor, which drives the inner shaft to rotate at high speed. The rotation of the inner shaft also drives the combat cabin shell and the flexible steel ropes to rotate synchronously. After the aircraft approaches the target, the high-speed rotating flexible steel ropes rotate and cut the UAV target, shooting it down.

[0023] Aircraft recovery: After the aircraft shoots down the UAV target, the control computer controls the turbojet engine to stop working. 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 the sealing cover are pushed out. The parachute opens, the aircraft slows down and falls, and the telemetry information sent back through the data link is used to determine the position of the aircraft, completing the recovery of the aircraft. After recovery, the aircraft is inspected, some damaged parts are replaced, the engine fuel is refilled, the flexible steel rope is retracted to the outer shaft, the parachute is retracted into the parachute compartment, and the tail sealing cover is replaced and reinstalled before it can be put into use again.

[0024] Beneficial effects:

[0025] 1. The combat cabin of the present invention uses a method of releasing and driving a flexible steel rope to rotate at high speed to achieve rotary cutting of the target UAV. It does not have hard-kill warheads such as explosives, and will not cause secondary damage after destroying the target UAV. It can be used in areas with large traffic flow, which improves the safety of use after the target UAV is destroyed and has a wide range of applications.

[0026] 2. Compared with other anti-UAV aircraft, the present invention can not only destroy the target UAV but also effectively recycle and reuse the aircraft, effectively solving the problem of relatively low cost-effectiveness of current anti-UAV aircraft.

[0027] 3. The length of the flexible steel rope of the present 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. The present invention cuts and destroys the target UAV through a high-speed rotating flexible steel rope, can accurately strike the target, ensure that the key components of the UAV are cut off and destroyed, making it lose its flight ability, and improve the effectiveness and success rate of intercepting the target UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 Schematic diagram of the overall structure of the anti-UAV aircraft based on rotary cutting.

[0030] Among them: 1-seeker cabin, 2-combat cabin, 3-external shaft, 4-instrument cabin, 5-control computer, 6-power cabin, 7-servo cabin, 8-parachute cabin, 9-parachute, 10-nozzle, 11-infrared seeker, 12-inner shaft, 13-flexible steel rope, 14-guide tube, 15-motor, 16-inertial navigation unit, 17-data link, 18-main power supply, 19-wing, 20-fuel tank, 21-oil pipe, 22-turbojet engine, 23-rudder wing, 24-servo, 25-pressurization device, 26-sealing cover. DETAILED DESCRIPTION

[0031] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0032] Example 1

[0033] See attached Figure 1 This embodiment provides an anti-UAV aircraft based on rotary cutting, which includes, starting from the head, a seeker cabin 1, a combat cabin 2, an instrument cabin 4, a power cabin 6, a steering gear cabin 7 and a parachute cabin 8.

[0034] An infrared seeker 11 is installed in the seeker cabin. The infrared seeker 11 is installed at the interface between the seeker cabin 1 and the combat cabin 2. A circular hole is opened at the center of the interface, and a bearing is installed on it.

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

[0036] The instrument cabin 4 is equipped with a main power supply 18, which is installed at the interface between the instrument cabin 4 and the power cabin 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 cabin 4 and the power cabin 6 are assembled to form an assembly.

[0037] The power compartment 6 is equipped with 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 steering gear compartment 7, and a circular hole is opened at the center of the interface. A nozzle 10 is installed at the tail of the engine 22, and the nozzle 10 extends from the circular hole. The nozzle 10 passes through the steering gear 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 the oil pipe 21; two foldable wings 19 are installed on the outer wall of the power compartment 6 shell, which are placed at 180° on both sides of the aircraft.

[0038] There are four servos 24 installed in the servo cabin 7. The servos 24 are installed on the inner wall of the servo cabin 7 shell, and the four servos 24 are distributed in an "X" shape; there are circular holes at the installation positions of the servos 24 for passing the rudder shaft; the rudder wings 23 are installed on the outer wall of the servo cabin 24 shell and assembled with the rudder shaft.

[0039] A pressurizing device 25 is installed in the parachute cabin 8, and the pressurizing device 25 is installed at the interface between the steering gear cabin 7 and the parachute cabin 8; the parachute bag 9 is placed in a ring shape inside the parachute cabin 8; and a sealing plug cover 26 is installed at the tail of the parachute cabin 8.

[0040] Example 2:

[0041] See attached Figure 1This embodiment provides an aircraft for destroying drones based on rotary cutting and a recovery method thereof. The workflow of the aircraft as described in Example 1 includes five steps: aircraft launch, aircraft flight, aircraft target locking, aircraft attack target, and aircraft recovery.

[0042] Aircraft launch: The aircraft of the present invention can fold the wings 19 and the rudder wings 23 and place them in the launch tube. After receiving the launch command, the ejection device ejects the aircraft out of the tube. The wings 19 and the 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 20 meters above the ground, the control computer 5 sends an ignition command to the ignition device of the turbojet engine 22. The turbojet engine 22 ignites, and the aircraft enters the flight phase for cruise flight. During the flight, the control computer 5 controls the steering gear 24 to deflect the rudder 19 to adjust the aircraft's attitude and fly along the predetermined route.

[0044] Aircraft locks on target: During the flight of the aircraft, the image generated by the infrared seeker 11 can be transmitted to the ground through the data link 17, and the UAV target can be locked by a man-in-the-loop method or by the seeker autonomous identification method.

[0045] Aircraft attacks target: After the seeker 11 locks the UAV target, the aircraft continues to fly closer to 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, so that the three flexible steel ropes 13 wrapped around the outer shaft 3 are released, and the flexible steel ropes 13 are extended to the outside of the combat cabin 2 shell through the guide tube 14; after the three flexible steel ropes 13 are released, the control computer 5 sends a command to the motor 15, and the motor 15 drives the inner shaft 12 to rotate at high speed. While the inner shaft 12 rotates, it drives the combat cabin 2 shell and the flexible steel ropes 13 to rotate synchronously. After the aircraft approaches the target, the high-speed rotating flexible steel ropes 13 rotate and cut the UAV target to shoot down the UAV.

[0046] UAV materials are generally made of carbon fiber materials, and the shear strength of conventional orthogonal ply carbon fiber is τ = 100MPa. According to the shear force formula F s =τA, A is the cutting surface area, based on the cutting thickness of 10mm and the cutting length of 100mm, the shear force F required for the flexible steel rope cutting drone s is 100kN, so the centrifugal force F generated by the rotation of the steel rope c >F s The steel rope centrifugal force F c =mω 2r, the flexible steel ropes 13 selected are all round steel ropes with teeth. The extended length after unfolding is 2m, the linear density is 1kg / m, the length of the steel rope involved in cutting is 0.1m, and it is calculated that the required speed of the motor 15 needs to be greater than 6750rpm, so the speed of the selected motor 15 is 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 pressurizing device 25 located in the parachute compartment 8. Under the action of high-pressure gas, the parachute bag 9 and the sealing cover 26 are pushed out, the parachute bag 9 opens, the aircraft slows down and falls, and the telemetry information sent back by the data link 17 is used to determine the position of the aircraft, and the aircraft is recovered; after recovery, the aircraft is inspected, some damaged parts are replaced, the fuel tank 20 is refilled with fuel, the flexible steel rope 13 is retracted to the outer rotating shaft 3, the parachute bag 9 is retracted into the parachute compartment 8, and the tail sealing cover 26 is replaced and reinstalled before it can be put into use again.

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

Claims

1. An anti-UAV aircraft based on rotary cutting, characterized in that: It includes the seeker cabin, rope cabin, instrument cabin, power cabin, steering gear cabin and parachute cabin; An infrared seeker is provided in the seeker cabin; The steel rope compartment can rotate independently relative to the front and rear compartments under the drive of the motor and release the flexible steel rope wound inside it. The motor drives the steel rope compartment shell to rotate at high speed and drives the flexible steel rope to rotate at high speed, thereby achieving rotary cutting of the target UAV; The instrument compartment is equipped with a main power supply for supplying power to aircraft equipment, a control computer for aircraft power distribution, launch and flight control; a data link for communication between the aircraft and the ground; and an inertial navigation unit for measuring aircraft attitude and acceleration information. The power cabin is provided with a turbojet engine and a fuel tank for providing cruising power for the aircraft, and the outer wall of the power cabin shell is provided with a foldable wing; the tail of the power cabin is provided with a nozzle, which passes through the steering gear cabin; The steering gear compartment is provided with a steering gear for controlling the rotation of the rudder blades; A pressurizing device for pressurizing the parachute cabin is provided in the parachute cabin, the parachute bag is placed in a ring shape inside the parachute cabin, and a sealing plugging cover is provided at the tail of the parachute cabin.

2. The anti-UAV aircraft based on rotary cutting according to claim 1, characterized in that: The infrared seeker is installed at the interface between the seeker cabin and the steel rope cabin. A circular hole is opened at the center of the interface, and a bearing is installed on the hole.

3. The anti-UAV aircraft based on rotary cutting according to claim 2, characterized in that: The steel rope cabin includes a steel rope cabin shell, a motor, an outer rotating shaft, an inner rotating shaft, a bearing, a guide tube and a flexible steel rope; the motor is installed at the interface between the steel rope cabin and the instrument cabin, and a circular hole is opened at the center of the interface, on which a bearing is installed; the inner rotating shaft passes through the bearing hole at the junction of the steel rope cabin and the front and rear cabins to connect the steel rope cabin with 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 respectively, and the N guide tubes are installed on the inner wall of the steel rope cabin shell, and the installation points are located on the axial circle and are arranged at equal intervals of X°. The shell at the installation point has an opening, and the flexible steel rope extends from the opening; the steel rope cabin shell and the front and rear cabin sections are clearance-fitted, and the shell is installed on the inner rotating shaft, and the shell can rotate synchronously with the inner rotating shaft.

4. The anti-UAV aircraft based on rotary cutting according to claim 3, characterized in that: The main power supply in the instrument cabin is installed at the interface between the instrument cabin and the power cabin, 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 cabin and the power cabin are assembled to form an assembly.

5. The anti-UAV aircraft based on rotary cutting according to claim 4, characterized in that: The turbojet engine in the power compartment is installed at the interface between the power compartment and the steering gear compartment. A circular hole is opened at the center of the interface. A nozzle is installed at the tail of the engine, and the nozzle extends from the circular hole and passes through the steering gear compartment; the oil tank is installed at the interface between the power compartment and the instrument compartment; the oil tank is directly connected to the turbojet engine through an oil pipe; M foldable wings are installed on the outer wall of the power compartment shell.

6. The anti-UAV aircraft based on rotary cutting according to claim 5, characterized in that: There are four servos in the servo cabin, which are installed on the inner wall of the servo housing and are distributed in an "X" shape. There are circular holes at the servo installation positions for passing the rudder shaft; four rudder wings are installed on the outer wall of the servo cabin housing and assembled with the rudder shaft.

7. The anti-UAV aircraft based on rotary cutting according to claim 5 or 6, characterized in that: The work process of the aircraft includes five steps: aircraft launch, aircraft flight, aircraft target locking, 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, and 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 for cruising. During the flight, the control computer controls the steering gear to deflect the rudder wings to adjust the aircraft's attitude and fly along the predetermined route; Aircraft locks on target: During the flight of the aircraft, the image generated by the infrared seeker can be transmitted to the ground via the data link, and the UAV target can be locked by the human-in-the-loop method or the seeker can lock on the UAV target by autonomous recognition; Aircraft attack target: After the seeker locks onto the UAV target, the aircraft continues to fly closer to the target. After reaching a certain distance from the target, the control computer issues a command to the motor located in the steel rope cabin. The motor drives the outer shaft to rotate, releasing the N flexible steel ropes wrapped around the outer shaft. The flexible steel ropes are extended out of the steel rope cabin shell through the guide tube. After the N flexible steel ropes are released, the control computer issues a command to the motor, which drives the inner shaft to rotate at high speed. The rotation of the inner shaft also drives the steel rope cabin shell and the flexible steel ropes to rotate synchronously. After the aircraft approaches the target, the high-speed rotating flexible steel ropes rotate and cut the UAV target, shooting it down. Aircraft recovery: After the aircraft shoots down the UAV target, the control computer controls the turbojet engine to stop working. 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 the sealing cover are pushed out. The parachute opens, the aircraft slows down and falls, and the telemetry information sent back through the data link is used to determine the position of the aircraft, completing the recovery of the aircraft. After recovery, the aircraft is inspected, some damaged parts are replaced, the engine fuel is refilled, the flexible steel rope is retracted to the outer shaft, the parachute is retracted into the parachute compartment, and the tail sealing cover is replaced and reinstalled before it can be put into use again.

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