Intelligent variable-wing centrifugal plasma charging turbojet stealth unmanned aerial vehicle

Abstract

The utility model discloses an intelligent variable-wing centrifugal plasma charging turbojet stealth unmanned aerial vehicle. Comprising a fairing, an upper fuselage, a lower fuselage, a tail, an intelligent rudder wing, a turbine set, a plasma device, an air expansion cavity, a small impeller, a large impeller, a lower shell, an upper shell, a positioner, a connector, an end cover, a motor set, a coupler, an ion pulser, an electroactive exciter, a farad module, a control power supply, a centrifugal electronic speed controller, a flight controller, a right electronic speed controller, a left electronic speed controller, a measurement and control instrument, a left paddle set, a voltage plate and an active belt. The unmanned aerial vehicle comprises aileron wheels, ailerons, wheels, a rear landing gear and a front landing gear. The unmanned aerial vehicle overcomes the defects that a low-altitude hybrid wing unmanned aerial vehicle does not have jet propulsion combining vertical take-off and landing with efficient cruising, does not have intelligent wing changing, and is high in energy consumption, short in voyage, large in engine noise, not environmentally friendly and the like. The intelligent variable-wing ailerons and the intelligent rudder wings are utilized to realize loss control, energy consumption reduction, response speed improvement, impact reduction and the like, the voyage of the unmanned aerial vehicle is improved, noise is reduced, and the unmanned aerial vehicle is easy to control and has a stealth function.

Description

Technical Field

[0001] This invention belongs to the field of lightweight, environmentally friendly, energy-saving, biomimetic, detection, and hybrid-wing aircraft equipment. It is used to improve the flight capability and environmental adaptability of unmanned aerial vehicles and provides a new type of stealth drone that can both take off and land vertically and cruise efficiently, meeting the needs of diverse application scenarios. It can also be used in various aircraft, ships, and vehicles that use centrifugal compressed plasma turbojet engines, namely, intelligent variable-wing centrifugal plasma turbojet stealth drones. Background Technology

[0002] Traditional low-altitude multi-rotor unmanned aerial vehicles (UAVs) suffer from drawbacks such as the need for multiple mechanical structures to support multiple rotors, high energy consumption, short endurance, lack of gliding ability in the event of power failure, and unconcentrated thrust. Traditional low-altitude hybrid-wing UAVs also suffer from drawbacks such as the lack of a pure electric vector jet propulsion system that combines vertical take-off and landing with efficient cruise, lack of intelligent wing scaling, high energy consumption, short range, loud engine noise, lack of stealth capabilities, and environmental unfriendliness. This invention utilizes polymer nanoconfined effect flexible organic semiconductor material technology and ionic electroactive polymer IPG smart material network technology combined with electroactive material control technology to enable intelligent variable-wing ailerons and intelligent rudders to achieve flight vector control, reduce energy consumption, improve response speed, and reduce impact. It utilizes centrifugal compressed air combined with plasma gas pressurization and turbine propulsion jet technology to achieve concentrated airflow for effective propulsion, low-energy gliding, increased UAV range, reduced noise, and easy control. It utilizes tetrathiofulvalene thin film technology combined with electronic control technology to achieve visual stealth capability of the fuselage. At the same time, it solves the defects of existing UAVs, such as needing multiple mechanical structures to support multiple rotors, high power consumption, short endurance, lack of gliding ability when power fails, non-concentrated thrust, and the lack of a pure electric vector jet propulsion system for vertical take-off and landing combined with efficient cruise in traditional low-altitude hybrid-wing UAVs, lack of intelligent variable-wing design, high energy consumption, short range, high engine noise, lack of stealth, and environmental pollution. This invention achieves a novel approach that utilizes intelligent variable-wing and intelligent rudder wings to accomplish functions such as flight vector control, energy reduction, improved response speed, reduced impact, extended UAV range, reduced noise, ease of control, and visual stealth. It features a simple structure, high utilization rate, ease of manufacturing, and can be applied to multiple fields such as agriculture, power, logistics, emergency rescue, exploration, and military, with great potential for sustainable development. Summary of the Invention

[0003] The purpose of this invention is to provide a sustainable solution that utilizes polymer nanoconfined effect flexible organic semiconductor material technology and ionic electroactive polymer IPG smart material network technology combined with electroactive material control technology to enable intelligent variable wing and intelligent rudder wings to achieve flight vector control, reduce energy consumption, improve response speed, and reduce impact. It also utilizes centrifugal compression combined with plasma gas pressurization and turbine propulsion jet technology to achieve concentrated airflow injection, effective propulsion, low-energy gliding, increased UAV range, reduced noise, and easier control. Furthermore, it employs tetrathiofulvalene thin film technology combined with electronic control technology to achieve visual stealth capabilities. Simultaneously, it utilizes additive manufacturing 3D printing density control technology to achieve integrated fairing, integrated upper fuselage and wings, integrated lower fuselage and front and rear landing gear, and integrated tail. This solution addresses the shortcomings of existing UAVs, such as requiring multiple mechanical structures for support, high energy consumption, short endurance, lack of gliding ability in case of power failure, unconcentrated thrust, high engine noise, lack of stealth, and environmental unfriendliness. This invention realizes a new type of aircraft equipment that utilizes intelligent variable wing and intelligent rudder to achieve flight vector control, reduce energy consumption, improve response speed, reduce impact, increase UAV range, reduce noise, is easy to control, and can achieve visual stealth. It has a simple structure, is safe, energy-saving, lightweight, has high utilization rate, is easy to process, and can be applied to multiple fields such as agriculture, power, logistics, emergency rescue, detection, and military, with great potential for sustainable development.

[0004] To achieve the above objectives, the present invention adopts the following technical solution:

[0005] The structural scheme of this invention is as follows: a smart variable-wing centrifugal plasma-charged turbojet stealth unmanned aerial vehicle, comprising a fairing (1), an upper fuselage (2), a lower fuselage (3), a tail (4), a smart rudder wing (5), a turbine assembly (6), a plasma generator (7), an air expansion chamber (8), a small impeller (9), a large impeller (10), a lower shell (11), an upper shell (12), a locator (13), a connector (14), an end cap (15), a motor assembly (16), a coupling (17), an ion pulser (18), an electroactive exciter (19), a farad module (20), a control power supply (21), a centrifugal ESC (22), a flight controller (23), a right ESC (24), a left ESC (25), a measurement and control unit (26), a right propeller assembly (27), and a left propeller assembly (28). Voltage plate (29), active belt (30), aileron wheel (31), right aileron (32), aileron (33), wheel (34), rear landing gear (35), front landing gear (36), fairing (1) left end face fastened to the left end face fastening hole of the upper fuselage (2) and lower fuselage (3) fastening assembly, upper fuselage (2) and lower fuselage (3) parting surface coated with epoxy resin and fastened together, tail (4) inserted into the right side surface of the assembly after upper fuselage (2) and lower fuselage (3) are glued and fastened together with epoxy resin and positioned and locked with screws, fairing (1) after being combined with upper fuselage (2), lower fuselage (3) and tail (4) outer surface covered with tetrathiofulvalene film, smart rudder wing (5) glued with epoxy resin and fastened to the upper right of the jet nozzle of tail (4)The turbine assembly (6) is integrated with the drive shaft and connected to the assembly of the lower housing (11) and the upper housing (12) via bearing limit. Three plasma generators (7) are distributed at 120° angles and sealed and press-fitted into the upper housing (12) and the lower housing (11). The gas expansion chamber (8) is located between the conical surfaces on the right side of the assembly of the plasma generators (7) and the upper housing (12) and the lower housing (11). The small impeller (9) and the large impeller (10) are integrated with the drive shaft and connected to the assembly of the lower housing (11) and the upper housing (12) via bearing limit. The mating surfaces of the lower housing (11) and the upper housing (12) are connected. The components are connected by epoxy resin and then bonded together. The lower end face of the locator (13) is connected to the lower right side of the lower body (3) and the lower left side of the tail (4) with epoxy resin and thread. The right end boss of the connector (14) is pressed onto the lower right step of the locator (13). The left end groove of the connector (14) is installed on the lower right boss of the lower body and is positioned by screw connection. The inner surface of the right end of the end cover (15) is coated with epoxy resin and then pressed onto the left end step of the assembly of the lower housing (11) and the upper housing (12). The right motor shaft of the motor assembly (16) is screwed into the threaded hole at the left end of the drive shaft of the large impeller (10) on the right side. The lower plane of the motor assembly (16) is coated with epoxy resin and then inserted. The coupling (17) is installed on the lower right platform of the lower body (3). The threaded hole at the left end of the coupling (17) is threaded to the right motor shaft of the motor unit (16). The threaded hole at the right end of the coupling (17) is threaded to the left end of the drive shaft of the large impeller (10). The ion pulser (18) is installed on the control power supply (21) and is internally connected to the control power supply (21) through control wires. The ion pulser (18) is externally connected to the three sets of plasma generators (7) through three sets of control wires. The active exciter (19) is installed on the control power supply (21) and is internally connected to the control power supply (21) through control wires. The active exciter (19) is externally connected to the two sets of voltage plates (29) through four sets of control wires. A set of intelligent rudder wings (5), a set of electrodes covered with a tetrathiofulvalene film on the outer surface, a farad module (20) bonded to the bottom wall inside the lower fuselage (3) with epoxy resin, its electrodes being connected in parallel with the control power supply (21) electrodes, a centrifugal ESC (22) integrated on the flight controller (23), its output wires being connected to the corresponding wires of the motor assembly (16), the flight controller (23) bonded to the bottom wall inside the lower fuselage (3) with epoxy resin, a right ESC (24) integrated on the flight controller (23), its output wires being connected to the corresponding wires of the right propeller assembly (27) motor, and a left ESC (25) integrated on the flight controller (23), its output wires being connected to the corresponding wires of the left propeller assembly (28) motor.Four voltage plates (29) are installed in two groups in the left and right main wings respectively and are bolted to the left and right main wings. The left ends of four active belts (30) are bolted to the voltage plates (29) on the left and right main wings respectively. Two aileron wheels (31) are installed on the rotatable shafts in the right aileron (32) and aileron (33) respectively. Each rotatable shaft positions the right aileron (32) and aileron (33) on the right main wing and the left main wing respectively. The right ends of the four active belts (30) are bolted to the right aileron (32) and aileron (33) respectively. The aileron wheel (31) has its synchronous gears on the upper and lower semicircular surfaces. The right aileron (32) is mounted on a pivot hole in the middle of the right main wing, which is structurally integrated with the upper fuselage (2), via a rotatable shaft. The aileron (33) is mounted on a pivot hole in the middle of the left main wing, which is structurally integrated with the upper fuselage (2), via a rotatable shaft. Three wheels (34) are mounted on axles below the two nose landing gears (36) and below the rear landing gear (35), respectively. The two nose landing gears (36) are structurally integrated with the lower fuselage (3), and the rear landing gear (35) is structurally integrated with the lower fuselage (3).

[0006] The turbine assembly (6) consists of three turbines and is integrated with the small impeller (9), the large impeller (10), and the drive shaft to form a centrifugal compressor turbine rotor. It uses polyimide as the base material and its outer surface has a physical vapor deposition nano-zirconia ceramic layer. The three plasma units (7) are respectively distributed at a 120° angle and sealed and pressed into the upper shell (12) and the two are sealed and pressed into the lower shell (11). Each plasma unit (7) has 5 pairs of cathode and anode plasma electrodes. The anode is made of titanium alloy and the cathode is made of tungsten alloy. The lower shell (11) and the upper shell (12) both use polyimide as the base material. Their combination forms a turbine jet shell. The lower shell is located inside the gas expansion chamber (8). The inner surface of the body (11) and the upper shell (12) is formed by physical vapor deposition of nano-zirconia ceramic layers to form a plasma gas expansion chamber. The small impeller (9), the large impeller (10), the lower shell (11), the upper shell (12), the positioner (13), the connector (14), the end cover (15), the motor unit (16), the coupling (17), and the plasma pulser (18) are combined to form a centrifugal compressed plasma turbojet. The left end face of the lower shell (11) and the right end of the end cover (15) of the combined body have three air intake channels distributed at a 120° angle, which respectively penetrate the centrifugal compressed plasma turbojet in the upper shell (12) and the lower shell (11). The voltage plate (29) consists of two cathode plates and two anode plates. The cathode and anode on the left end of the active strip (30) are respectively pressed between the cathode plate and anode plate of the voltage plate (29) by bolts. The active strip (30) uses a flexible organic semiconductor material based on the polymer nano confinement effect and is constructed as a synchronous belt. The anode wheel (31), the right anode (32), and the electroactive exciter (19) form a nano-electroactive right anode. The voltage plate (29) consists of two cathode plates and two anode plates. The cathode and anode on the left end of the active strip (30) are respectively pressed between the cathode plate and anode plate of the voltage plate (29) by bolts. The active strip (30) uses a flexible organic semiconductor material based on the polymer nano confinement effect and is constructed as a synchronous belt. The anode wheel (31), the anode (33), and the electroactive exciter (19) form a nano-electroactive left anode.

[0007] Two of the four active bands (30) use flexible organic semiconductor materials based on polymer nanoconfinement effect and are constructed as synchronous bands. Together with the aileron wheel (31), the right aileron (32), and the electroactive exciter (19), they form a nano-electroactive right aileron. The other two active bands (30) use flexible organic semiconductor materials based on polymer nanoconfinement effect and are constructed as synchronous bands. Together with the aileron wheel (31), the aileron (33), and the electroactive exciter (19), they form a nano-electroactive left aileron.

[0008] The intelligent rudder (5) uses an ionic electroactive polymer (IPG) smart material network to form a conductive network. A polymer film is coated on the outer surface of the intelligent rudder (5) and epoxy resin is used to bond the left end of the intelligent rudder (5) to the upper part of the jet nozzle on the lower right side of the tail (4). Together with the electroactive exciter (19), the flight controller (23) and the electronic gyroscope sensor therein, it forms an intelligent rudder module.

[0009] The fairing (1), together with the upper fuselage (2), lower fuselage (3), tail (4), and electroactive exciter (19), forms an electrovisual stealth drone body by bonding a tetrathiofulvalene film to the outer surface with epoxy resin.

[0010] The principle of this invention is as follows: the vertical ascent and descent process of the intelligent variable-wing centrifugal plasma-boosted turbojet stealth drone is achieved by controlling the propeller motor on the right propeller assembly (27) installed on the right wing, controlling the propeller motor on the left propeller assembly (28) installed on the left wing, controlling the motor on the motor assembly (16) at the left end of the centrifugal compressed plasma-boosted turbojet installed in the tail (4), and controlling the electrode assembly on the intelligent rudder wing (5) installed above the lower right jet nozzle of the tail (4). According to the flight command, the flight controller (23) controls the control power supply (21) to output electrical energy to the right ESC (24), left ESC (25) and centrifugal ESC (22). The flight controller (23) controls the right ESC (24) to supply power to the propeller motor on the right propeller assembly (27) to drive the right propeller to rotate and generate lift. The flight controller (23) controls the left ESC (25) to supply power to the propeller motor on the left propeller assembly (28) to drive the left propeller to rotate and generate lift. The flight controller (23) controls the centrifugal ESC (22) to supply power to the motor on the motor assembly (16), driving the coupling (17), turbine assembly (6), small impeller (9), and large impeller (10) mounted on the drive shaft of the centrifugal compressed plasma turbojet to rotate synchronously. This completes the intake of air into three centrifugal compressed plasma turbojet intake channels distributed at 120° angles, which pass through the upper casing (12) and lower casing (11) respectively. The air is then compressed in two stages by the large impeller (10) and the small impeller (9). When compressed air enters the three expansion chambers (8), the three plasma generators (7) distributed at a 120° angle control the power supply (21) under the control of the flight controller (23) to output electrical energy to the ion pulse generator (18) to generate a high-pressure pulse, causing the compressed air to form plasma and rapidly expand to form high-temperature plasma gas. Under the action of high-temperature plasma, the compressed air expands, leading to an increase in internal pressure and forming high pressure. Under the action of the turbine assembly (6), the high-pressure gas is rapidly ejected, generating longitudinal thrust acting on the intelligent variable-wing centrifugal plasma-boosted turbojet stealth drone. According to flight commands, the flight controller (23) controls the power supply (21) to output electrical energy to the corresponding terminal of the electroactive exciter (19). Through the terminal, the electroactive excitation signal is connected to the electrode group on the smart rudder (5) via wires to control the electrode group of the conductive vein on the ionic electroactive polymer (IPG) smart material on the smart rudder (5). This causes the smart rudder (5) to bend and deform downward, forcing the longitudinal high-speed airflow ejected by the centrifugal plasma turbojet to become a downward jet flow (i.e., towards the ground) under the guidance of the smart rudder (5), generating lift and thus achieving vector control of the jet flow. Through these controls, the vertical take-off and landing processes of the smart variable-wing centrifugal plasma turbojet stealth UAV are controlled.

[0011] The forward flight control process of the intelligent variable-wing centrifugal plasma-charged turbojet stealth UAV. Forward flight is achieved by controlling the propeller motor on the right rotor assembly (27) mounted on the right wing, the propeller motor on the left rotor assembly (28) mounted on the left wing, the motor on the motor assembly (16) at the left end of the centrifugal compressed plasma-charged turbojet in the tail (4), and the electrode assembly on the intelligent rudder wing (5) above the lower right jet nozzle of the tail (4). According to flight commands, the flight controller (23) controls the control power supply (21) to output electrical energy to the right ESC (24), left ESC (25) and centrifugal ESC (22). The flight controller (23) controls the right ESC (24) to supply power to the propeller motor on the right propeller assembly (27) to drive the right propeller to rotate and generate lift balance. The flight controller (23) controls the left ESC (25) to supply power to the propeller motor on the left propeller assembly (28) to drive the left propeller to rotate and generate lift balance. The flight controller (23) controls the centrifugal ESC (22) to supply power to the motor on the motor assembly (16), driving the coupling (17), turbine assembly (6), small impeller (9), and large impeller (10) mounted on the drive shaft of the centrifugal compressed plasma turbojet to rotate synchronously, thus drawing in air into three centrifugal compressed plasma turbojet intake channels distributed at 120° angles, which pass through the upper casing (12) and lower casing (11) respectively. The air is then fed through the large impeller (10) and small impeller (9). The system performs two-stage compression. When the compressed air enters the three expansion chambers (8), the three plasma generators (7) with a 120° distribution angle are controlled by the flight controller (23) to output electrical energy to the ion pulse generator (18) to generate a high-pressure pulse, causing the compressed air to form a plasma state. Under the action of the high-temperature plasma, the compressed air expands, leading to an increase in internal pressure and forming a high pressure. Under the action of the turbine assembly (6), the high-pressure gas is rapidly ejected, generating longitudinal thrust on the intelligent variable-wing centrifugal plasma-boosted turbojet stealth drone. According to flight commands, the flight controller (23) controls the power supply (21) to output electrical energy to the corresponding terminal of the electroactive exciter (19). Through the terminal, the electroactive excitation signal is connected to the electrode group on the smart rudder (5) via wires to control the electrode group of the conductive vein on the ionic electroactive polymer (IPG) smart material on the smart rudder (5). This prevents the smart rudder (5) from bending or deforming, so that the longitudinal high-speed airflow ejected by the centrifugal plasma turbojet jet is ejected horizontally and generates forward thrust. Through these controls, the forward flight of the smart variable-wing centrifugal plasma turbojet stealth UAV is achieved.

[0012] The yaw flight control process of the intelligent variable-wing centrifugal plasma-charged turbojet stealth drone. When the intelligent variable-wing centrifugal plasma-charged turbojet stealth drone needs to yaw left or right during flight, it is necessary to control the yaw angle of the right aileron (32) installed on the right wing, the yaw angle of the aileron (33) installed on the left wing, and the torsion angle of the intelligent rudder (5). When yawing to the right, the flight controller (23) controls the power supply (21) to output electrical energy to the electroactive exciter (19) according to the flight command. The electroactive exciter (19) transmits the electroactive excitation signal through the wire to the upper and lower flexible organic semiconductor material active strips (30) based on the polymer nano-confinement effect on the voltage plate (29) of the right aileron (32). By changing the electrode direction of the upper and lower active strips (30), the upper active strip (30) of the synchronous belt structure is extended and the lower active strip (30) is contracted, which drives the aileron wheel (31) to rotate, thereby turning the right aileron. (32) A downward rotation occurs, completing the right yaw. Simultaneously, the flight controller (23), according to the flight command, controls the power supply (21) to output electrical energy to the corresponding terminal of the electroactive exciter (19). Through the terminal, the electroactive excitation signal is connected to the electrode group on the smart rudder (5) via a wire to control the electrode group of the conductive vein on the ionic electroactive polymer IPG smart material on the smart rudder (5). This causes the smart rudder (5) to undergo a torsional deformation with the horizontal axis as the axis. The left side of the outer edge of the fan-shaped surface of the smart rudder (5) twists upward. The wind resistance of the twisted surface will accelerate the right yaw of the UAV. At this time, the longitudinal high-speed airflow ejected by the centrifugal compressed plasma turbojet jet generates forward thrust along the horizontal direction and remains unchanged. Through these controls, the right yaw flight of the smart variable-wing centrifugal plasma turbojet stealth UAV is achieved. When yawing to the left, the flight controller (23) causes the aileron (33) on the left wing to yaw downwards according to the command, and the right side of the fan-shaped outer edge of the smart rudder (5) twists upwards. The wind resistance of the twisted surface will accelerate the UAV to yaw to the left.

[0013] The stealth flight control process of the intelligent variable-wing centrifugal plasma-charged turbojet stealth drone is as follows: the fairing (1) is assembled with the upper fuselage (2), lower fuselage (3) and tail (4) to form the drone body. The outer surface is covered with a tetrathiofulvalene film by epoxy resin bonding and wires are connected to the electroactive exciter (19). The flight controller (23) controls the power supply (21) to output electrical energy to the corresponding terminal of the electroactive exciter (19) according to the command. According to the degree of stealth, the electric field is output to the tetrathiofulvalene film to achieve visual stealth or remove stealth.

[0014] The gliding flight control process of the intelligent variable-wing centrifugal plasma-charged turbojet stealth drone is as follows: when flying at a certain altitude, the flight controller (23) controls the longitudinal high-speed airflow ejected by the centrifugal compressed plasma-charged turbojet to generate a forward thrust of large, small or paused jet flow along the horizontal direction of the jet flow. By controlling the deflection of the aileron (33), the right aileron (32) and the bending angle or twist angle of the intelligent rudder (5), the drone can achieve unpowered or low-powered gliding flight when the left and right propeller motors are not working and the plasma generator (7) is not working. At this time, the left and right propellers are converted into rotorcraft propellers to prepare for collecting gliding energy.

[0015] This enables a new type of aircraft equipment that utilizes intelligent variable-wing and intelligent control wings to achieve flight vector control, low energy consumption, high response speed, reduced impact, increased UAV range, reduced noise, easy control, and visual stealth capabilities. It is a simple, safe, energy-saving, lightweight, highly efficient, and easy-to-manufacture aircraft that can be applied to multiple fields such as agriculture, power, logistics, emergency rescue, exploration, and military, and has great potential for sustainable development. Attached Figure Description

[0016] Figure 1 Main view structural diagram of intelligent variable-wing centrifugal plasma-charged turbojet stealth drone;

[0017] Figure 2 Schematic diagram of centrifugal compressed air plasma booster turbine jet structure;

[0018] Figure 3 Schematic diagram of the left rotor assembly and nano-electroactive left aileron structure in the left wing;

[0019] Figure 4 Enlarged view of the intelligent control wing layout on the tail section;

[0020] Figure 5 A top-view view of an intelligent variable-wing centrifugal plasma-charged turbojet stealth drone;

[0021] Figure 6 Left view of a smart variable-wing centrifugal plasma-charged turbojet stealth drone;

[0022] In the diagram: fairing (1), upper fuselage (2), lower fuselage (3), tail (4), smart rudder (5), turbine assembly (6), plasma generator (7), air expansion chamber (8), small impeller (9), large impeller (10), lower shell (11), upper shell (12), locator (13), connector (14), end cap (15), motor assembly (16), coupling (17), ion pulse generator (18), electroactive exciter (19), farad module (20), control power supply (21), centrifugal ESC (22), flight controller (23), right ESC (24), left ESC (25), telemetry and control unit (26), right propeller assembly (27), left propeller assembly (28), voltage board (29), active belt (30), aileron wheel (31), right aileron (32), aileron (33), wheel (34), rear landing gear (35), front landing gear (36). Detailed Implementation

[0023] The present invention will be further described below with reference to the accompanying drawings:

[0024] like Figure 1As shown; a smart variable-wing centrifugal plasma-charged turbojet stealth unmanned aerial vehicle includes a fairing (1), upper fuselage (2), lower fuselage (3), tail (4), smart rudder (5), turbine assembly (6), plasma generator (7), gas expansion chamber (8), small impeller (9), large impeller (10), lower shell (11), upper shell (12), locator (13), connector (14), end cap (15), motor assembly (16), coupling (17), and ion generator. Pulse generator (18), electroactive exciter (19), farad module (20), control power supply (21), centrifugal ESC (22), flight controller (23), right ESC (24), left ESC (25), telemetry and control unit (26), right propeller assembly (27), left propeller assembly (28), voltage board (29), active belt (30), aileron wheel (31), right aileron (32), aileron (33), wheel (34), rear landing gear (35), front landing gear (36). This utility model consists of four main parts. The fuselage (1), upper fuselage (2), lower fuselage (3), and tail (4) constitute the electro-visual stealth drone body of the intelligent variable-wing centrifugal plasma-charged turbojet stealth drone. The intelligent variable-wing system of the intelligent variable-wing centrifugal plasma-charged turbojet stealth drone consists of intelligent rudder wing (5), voltage plate (29), active belt (30), aileron wheel (31), right aileron (32), aileron (33), electro-active exciter (19), farad module (20), control power supply (21), and flight controller (23). An air intake is opened on the upper right side of the upper fuselage (2). The power drive system of the intelligent variable-wing centrifugal plasma turbojet stealth UAV consists of a right ESC (24), a right propeller assembly (27), a left ESC (25), a left propeller assembly (28), a centrifugal compressed plasma turbojet engine, an ion pulse generator (18), a farad module (20), a control power supply (21), and a flight controller (23). The farad module (20) is a supercapacitor matrix energy storage device connected in parallel with the control power supply (21) to provide high-current instantaneous power supply capability. The measurement and control system and navigation system of the intelligent variable-wing centrifugal plasma turbojet stealth UAV consist of a measurement and control unit (26), a flight controller (23), and a control power supply (21).

[0025] like Figure 2As shown; the turbine assembly (6) consists of three turbines integrated with the small impeller (9), large impeller (10) and drive shaft to form a centrifugal compressor turbine rotor. The centrifugal compressor turbine rotor uses polyimide as the matrix material and its outer surface is covered with a physical vapor deposition nano-zirconia ceramic layer. The plasma unit (7) consists of three sets distributed at a 120° angle, one set is sealed and pressed into the upper housing (12) and two sets are sealed and pressed into the lower housing (11). Each plasma unit (7) has 5 pairs of cathode and anode plasma electrodes. The anode is made of titanium alloy and the cathode is made of tungsten alloy. The lower housing (11) and the upper housing (12) are both made of polyimide as the matrix material. Their combination forms a turbine jet housing. The lower housing (11) and the upper housing (12) in the gas expansion chamber (8) are covered with a physical vapor deposition nano-zirconia ceramic layer to form a plasma gas expansion. The centrifugal compressed plasma turbojet is composed of a cavity, a small impeller (9), a large impeller (10), a lower housing (11), an upper housing (12), a positioner (13), a connector (14), an end cover (15), a motor assembly (16), a coupling (17), and a plasma pulser (18). The lower housing (11) and the upper housing (12) assembly have three air intake channels at a 120° angle on the left end face and the right end of the end cover (15), which respectively connect to the centrifugal compressed plasma turbojet airflow channels in the upper housing (12) and the lower housing (11). The centrifugal compressed plasma turbojet is a high-temperature resistant, lightweight centrifugal compressed plasma turbojet formed by 3D printing of high-temperature resistant materials through additive manufacturing and surface physical vapor deposition of nano-zirconia ceramic layers.

[0026] like Figure 3 As shown; including the left propeller assembly (28), the voltage plate (29) is composed of two cathode plates, two layers of anode plates, the cathode and anode on the left end of the active strip (30) are respectively pressed between the cathode plate and anode plate of the voltage plate (29) by bolts, the active strip (30) is made of flexible organic semiconductor material based on polymer nano confinement effect and is constructed as a synchronous belt, the aileron wheel (31), the right aileron (32), and the electroactive exciter (19) form a nano-electroactive right aileron, the voltage plate (29) is composed of two layers of cathode plates and two layers of anode plates, the cathode and anode on the left end of the active strip (30) are respectively pressed between the cathode plate and anode plate of the voltage plate (29) by bolts, the active strip (30) is made of flexible organic semiconductor material based on polymer nano confinement effect and is constructed as a synchronous belt, the aileron wheel (31), the aileron (33), and the electroactive exciter (19) form a nano-electroactive left aileron.

[0027] like Figure 4As shown; including the intelligent rudder (5) which uses an ionic electroactive polymer IPG smart material network to form a conductive network, a polymer film covering the outer surface of the intelligent rudder (5), and epoxy resin bonding the left end of the intelligent rudder (5) to the upper part of the jet nozzle on the lower right side of the tail (4), and forming an intelligent rudder module with the electroactive exciter (19) and the electronic gyroscope sensor in the flight controller (23).

[0028] like Figure 5 As shown; including left wing, right wing, tail, fuselage, voltage plate (29), aileron wheel (31), right aileron (32), aileron (33), active belt (30), the cathode and anode on the left end of the active belt (30) are respectively pressed between the cathode plate and anode plate of the voltage plate (29) by bolts. The active belt (30) uses flexible organic semiconductor material based on polymer nano confinement effect and is constructed as a synchronous belt. The aileron wheel (31), aileron (33), and electroactive exciter (19) form a nano-electroactive aileron. The voltage plate (29) is a combination of two cathode plates and two anode plates. The cathode and anode on the left end of the active belt (30) are respectively pressed between the cathode plate and anode plate of the voltage plate (29) by bolts. The active belt (30) uses flexible organic semiconductor material based on polymer nano confinement effect and is constructed as a synchronous belt. The aileron wheel (31), aileron (33), and electroactive exciter (19) form a nano-electroactive right aileron.

[0029] like Figure 6 As shown; including the right rotor assembly (27), left rotor assembly (28), rear landing gear (35), and front landing gear (36), the right rotor assembly (27) is mounted on the right wing, and the left rotor assembly (28) is mounted on the left wing, operating according to the flight commands of the flight controller (23). Stable flight of the intelligent variable-wing centrifugal plasma-charged turbojet stealth unmanned aerial vehicle is achieved through control.

[0030] This invention belongs to the field of lightweight, environmentally friendly, energy-saving, biomimetic, detection, and hybrid-wing aircraft equipment. It aims to enhance the flight capabilities and environmental adaptability of unmanned aerial vehicles (UAVs), providing a novel stealth UAV capable of both vertical takeoff and landing and efficient cruising. This meets the needs of more diverse application scenarios and can also be used in various aircraft, ships, and vehicles employing centrifugal plasma-charged turbojet engines—namely, an intelligent variable-wing centrifugal plasma-charged turbojet stealth UAV. It achieves a novel intelligent variable-wing centrifugal plasma-charged turbojet stealth UAV that utilizes intelligent variable wings and intelligent control wings to achieve flight vector control, low energy consumption, high response speed, reduced impact, increased UAV range, low noise, easy control, and visual stealth capabilities. It features a simple structure, high utilization rate, ease of manufacturing, and significant sustainable development potential in multiple fields such as agriculture, power, logistics, emergency rescue, and military. As a high-tech product, it has a wide range of raw material sources, requires little space, and has low production costs, providing favorable conditions for fully utilizing industrial resources, promoting the transformation and upgrading of the UAV industry, and developing the low-altitude economy.

Claims

1. A smart variable-wing centrifugal plasma-charged turbojet stealth unmanned aerial vehicle, comprising a fairing (1), an upper fuselage (2), a lower fuselage (3), a tail (4), a smart rudder wing (5), a turbine assembly (6), a plasma generator (7), an air expansion chamber (8), a small impeller (9), a large impeller (10), a lower shell (11), an upper shell (12), a locator (13), a connector (14), an end cap (15), a motor assembly (16), a coupling (17), an ion pulser (18), an electroactive exciter (19), a farad module (20), a control power supply (21), a centrifugal ESC (22), a flight controller (23), a right ESC (24), a left ESC (25), a measurement and control unit (26), a right propeller assembly (27), a left propeller assembly (28), and a voltage board. (29), active belt (30), aileron wheel (31), right aileron (32), aileron (33), wheel (34), rear landing gear (35), front landing gear (36), the left end face of the fairing (1) is fastened to the left end face fastening hole of the upper fuselage (2) and lower fuselage (3) fastening assembly, the parting surface of the upper fuselage (2) and lower fuselage (3) is coated with epoxy resin and then fastened, the tail (4) is inserted into the right side surface of the assembly after the upper fuselage (2) and lower fuselage (3) are bonded and fastened with epoxy resin and locked with screws, the outer surface of the fairing (1) after being combined with the upper fuselage (2), lower fuselage (3) and tail (4) is covered with a tetrathiofulvalene film, the smart rudder wing (5) is bonded with epoxy resin and fastened to the upper part of the jet nozzle on the lower right side of the tail (4),The turbine assembly (6) is integrated with the drive shaft and connected to the assembly of the lower housing (11) and the upper housing (12) via bearing limit. The three plasma generators (7) are distributed at 120° angles and are respectively sealed and press-fitted into the upper housing (12) and the lower housing (11). The gas expansion chamber (8) is the space between the conical surface on the right side of the assembly of the plasma generator (7) and the upper housing (12) and the lower housing (11). The small impeller (9) and the large impeller (10) are integrated with the drive shaft and connected to the assembly of the lower housing (11) and the upper housing (12) via bearing limit. The mating surface of the lower housing (11) and the upper housing (12) The assembly is formed by plugging and bonding with epoxy resin. The lower end face of the locator (13) is connected to the lower right side of the lower body (3) and the lower left side of the tail (4) with epoxy resin and threads. The right end boss of the connector (14) is pressed into the lower right step of the locator (13). The left end groove of the connector (14) is installed on the lower right boss of the lower body and is positioned by screw connection. The inner surface of the right end of the end cover (15) is coated with epoxy resin and then pressed into the left end step of the assembly of the lower housing (11) and the upper housing (12). The right motor shaft of the motor assembly (16) is screwed into the threaded hole at the left end of the drive shaft of the large impeller (10) on the right side. The lower plane of the motor assembly (16) is coated with epoxy resin and then inserted. The coupling (17) is installed on the lower right platform of the lower body (3). The threaded hole at the left end of the coupling (17) is threaded to the right motor shaft of the motor unit (16). The threaded hole at the right end of the coupling (17) is threaded to the left end of the drive shaft of the large impeller (10). The ion pulser (18) is installed on the control power supply (21) and is internally connected to the control power supply (21) through control wires. The ion pulser (18) is externally connected to the three sets of plasma generators (7) through three sets of control wires. The active exciter (19) is installed on the control power supply (21) and is internally connected to the control power supply (21) through control wires. The active exciter (19) is externally connected to the two sets of voltage plates (29) through four sets of control wires. A set of intelligent rudder wings (5), a set of electrodes covered with a tetrathiofulvalene film on the outer surface, a farad module (20) bonded to the bottom wall inside the lower fuselage (3) with epoxy resin, its electrodes being connected in parallel with the control power supply (21) electrodes, a centrifugal ESC (22) integrated on the flight controller (23), its output wires being connected to the corresponding wires of the motor assembly (16), the flight controller (23) bonded to the bottom wall inside the lower fuselage (3) with epoxy resin, a right ESC (24) integrated on the flight controller (23), its output wires being connected to the corresponding wires of the right propeller assembly (27) motor, and a left ESC (25) integrated on the flight controller (23), its output wires being connected to the corresponding wires of the left propeller assembly (28) motor.Four voltage plates (29) are installed in two groups in the left and right main wings respectively and are bolted to the left and right main wings. The left ends of four active belts (30) are bolted to the voltage plates (29) on the left and right main wings respectively. Two aileron wheels (31) are installed on the rotatable shafts in the right aileron (32) and aileron (33) respectively. Each rotatable shaft positions the right aileron (32) and aileron (33) on the right main wing and the left main wing respectively. The right ends of the four active belts (30) are bolted to the right aileron (32) and aileron (33) respectively. The aileron wheel (31) has its synchronous gears on the upper and lower semicircular surfaces. The right aileron (32) is mounted on a pivot hole in the middle of the right main wing, which is structurally integrated with the upper fuselage (2), via a rotatable shaft. The aileron (33) is mounted on a pivot hole in the middle of the left main wing, which is structurally integrated with the upper fuselage (2), via a rotatable shaft. Three wheels (34) are mounted on axles below the two nose landing gears (36) and below the rear landing gear (35), respectively. The two nose landing gears (36) are structurally integrated with the lower fuselage (3), and the rear landing gear (35) is structurally integrated with the lower fuselage (3).

2. The intelligent variable-wing centrifugal plasma-charged turbojet stealth UAV according to claim 1, characterized in that: The turbine assembly (6) consists of three turbines and is integrated with the small impeller (9), the large impeller (10), and the drive shaft to form a centrifugal compressor turbine rotor. It uses polyimide as the base material and its outer surface has a physical vapor deposition nano-zirconia ceramic layer. The three plasma units (7) are respectively distributed at a 120° angle and sealed and pressed into the upper shell (12) and the two are sealed and pressed into the lower shell (11). Each plasma unit (7) has 5 pairs of cathode and anode plasma electrodes. The anode is made of titanium alloy and the cathode is made of tungsten alloy. The lower shell (11) and the upper shell (12) both use polyimide as the base material. Their combination forms a turbine jet shell. The lower shell is located inside the gas expansion chamber (8). The inner surface of the body (11) and the upper shell (12) is formed by physical vapor deposition of nano-zirconia ceramic layers to form a plasma gas expansion chamber. The small impeller (9), the large impeller (10), the lower shell (11), the upper shell (12), the positioner (13), the connector (14), the end cover (15), the motor unit (16), the coupling (17), and the plasma pulser (18) are combined to form a centrifugal compressed plasma turbojet. The left end face of the lower shell (11) and the right end of the end cover (15) of the combined body have three air intake channels distributed at a 120° angle, which respectively penetrate the centrifugal compressed plasma turbojet in the upper shell (12) and the lower shell (11).

3. The intelligent variable-wing centrifugal plasma-charged turbojet stealth UAV according to claim 1, characterized in that: Two of the four active bands (30) use flexible organic semiconductor materials based on polymer nanoconfinement effect and are constructed as synchronous bands. Together with the aileron wheel (31), the right aileron (32), and the electroactive exciter (19), they form a nano-electroactive right aileron. The other two active bands (30) use flexible organic semiconductor materials based on polymer nanoconfinement effect and are constructed as synchronous bands. Together with the aileron wheel (31), the aileron (33), and the electroactive exciter (19), they form a nano-electroactive left aileron.

4. The intelligent variable-wing centrifugal plasma-charged turbojet stealth UAV according to claim 1, characterized in that: The intelligent rudder (5) uses an ionic electroactive polymer (IPG) smart material network to form a conductive network. A polymer film is coated on the outer surface of the intelligent rudder (5) and epoxy resin is used to bond the left end of the intelligent rudder (5) to the upper part of the jet nozzle on the lower right side of the tail (4). Together with the electroactive exciter (19), the flight controller (23) and the electronic gyroscope sensor therein, it forms an intelligent rudder module.

5. The intelligent variable-wing centrifugal plasma-charged turbojet stealth UAV according to claim 1, characterized in that: The fairing (1), together with the upper fuselage (2), lower fuselage (3), tail (4), and electroactive exciter (19), forms an electrovisual stealth drone body by bonding a tetrathiofulvalene film to the outer surface with epoxy resin.

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