Wearable three-cascade powered single-person aircraft

Abstract

The application discloses a wearable three-cascade power single-person aircraft, which comprises a power system, an avionics system, a man-machine interaction system, a safety lifesaving system and a wearable fuselage; the power system adopts a three-cascade aerodynamic layout and is arranged in a triangle shape, wherein the two cascade units on the front side are arranged on the left and right sides of the wearable aircraft body at the same height, and the cascade unit on the back side is arranged at a height higher than that of the cascade units on the front side; the man-machine interaction system is arranged on the left side of the wearable fuselage and the head of the human body, and is used for manually controlling flight and monitoring flight state; and the safety lifesaving system is arranged on the upper part of the wearable fuselage and is used for guaranteeing the safety of the personnel in an emergency. The aircraft has the characteristics of compact structure, high stability, simple operation and good safety.

Description

Technical Field

[0001] This invention belongs to the field of wearable single-person vertical take-off and landing aircraft, and specifically relates to a wearable three-duct powered single-person aircraft. Background Technology

[0002] Wearable single-person aerial vehicles (SAVs) have significant application potential in both military and civilian fields due to their compact size, maneuverability, and ease of transport. In the military, they are primarily used for casualty evacuation, supply transport, and rapid assault; in the civilian sector, they are mainly used for emergency medical evacuation, personal commuting, and logistics transportation. With the gradual maturation of key technologies for small vertical takeoff and landing (VTOL) aircraft, SAVs are increasingly being used in both military and civilian fields to improve soldier mobility.

[0003] Current single-person aerial vehicles (SAVs) are primarily turbojet-powered, with the user carrying and holding several miniature turbojet engines. Vertical takeoff and landing (VTOL) and cruise flight are achieved through attitude control of these engines, enhancing the user's mobility. However, because flight attitude is directly related to body posture, it demands high physical fitness and control skills from the user, hindering widespread adoption. Furthermore, these aircraft require both hands to operate in-flight controls. Ducted-drive aircraft offer advantages such as high propulsion efficiency, low noise, and high safety. Currently, some ducted-drive VTOL aircraft exist in China, but all have cockpit layouts, hindering rapid personnel deployment. There are currently no wearable ducted-drive VTOL single-person SAVs. Summary of the Invention

[0004] To address the shortcomings of existing single-person aircraft, this invention proposes a wearable three-ducted powered single-person aircraft. This aircraft integrates key technologies such as high thrust-to-weight ratio ducted power design, three-ducted power flight control, and low-altitude and ultra-low-altitude emergency escape, forming a wearable ducted powered single-person aircraft with a compact structure and features high stability, easy operation, and good safety.

[0005] The technical solution to achieve the purpose of this invention is: a wearable three-duct powered single-person aircraft, comprising a power system, an avionics system, a human-machine interaction system, a safety and rescue system, and a wearable fuselage;

[0006] The power system includes three power units, which adopt a three-duct aerodynamic layout in a triangular arrangement. The two front duct units are located at the same height on both sides of the wearable fuselage, while the rear duct unit is installed at a higher height than the front duct units. The human-machine interface system is located on one side of the wearable fuselage and above the wearable head, and is used for manual flight control and monitoring of flight status. The safety and life-saving system is located on the upper part of the wearable fuselage, and is used to ensure personnel safety in emergencies. The avionics system provides power supply, flight control, and positioning and navigation for the entire aircraft.

[0007] Compared with the prior art, the significant advantages of this invention are:

[0008] (1) Based on the three-ducted air control surface power system, a wearable single-person aircraft is proposed. The aircraft layout of this invention has the front duct arranged in the middle of the fuselage, which is close to the center of gravity of the whole aircraft, thus improving flight maneuverability. The rear duct is placed on the upper part of the fuselage, which improves flight stability and reduces human interference with the air intake of the rear duct. It achieves compact size and high safety, and has the characteristics of flight stability and flexible operation.

[0009] (2) A novel low-altitude and ultra-low-altitude emergency escape technology for single-person aircraft is proposed. Through a human-machine separation device, parachute rocket, group parachute assembly and parachute opening control assembly, personnel can abandon the aircraft and escape in low-altitude emergency situations, thereby improving personnel safety and reducing the weight of the aircraft system. Attached Figure Description

[0010] Figure 1 This is a diagram of the three-duct single-person vertical takeoff and landing aircraft system of the present invention.

[0011] Figure 2 This is a schematic diagram of the overall system of the present invention.

[0012] Figure 3 This is a diagram of the power unit of the present invention.

[0013] Figure 4 This is a diagram of the avionics system of the present invention.

[0014] Figure 5 This is a diagram of the human-computer interaction system of the present invention.

[0015] Figure 6 This is a diagram of the safety and life-saving system of the present invention.

[0016] Figure 7 This is a structural diagram of the wearable device of the present invention.

[0017] Figure 8 Figure (a) and Figure (b) are schematic diagrams illustrating the effect of the rear duct layout on the flow field of the wearable body of the present invention.

[0018] Figure 9 This is a schematic diagram of an embodiment of the present invention.

[0019] Figure 10 This is a top-view geometric diagram of the dual-servo tilting tri-rotor UAV of the present invention.

[0020] Figure 11 This is a diagram showing the angle of the tiltable control surfaces as viewed from the rear of the fuselage, according to the present invention.

[0021] Figure 12This is a diagram showing the relationship between the controller and the control allocation structure of the present invention.

[0022] Explanation of reference numerals in the attached drawings: 1-Power unit A, 2-Power unit B, 3-Power unit C, 4-Avionics system, 5-Human-machine interface system, 6-Safety and rescue system, 7-Wearable fuselage, 8-Servos, 10-Ductwork, 11-Propeller blade, 12-Tail cone, 13-Aerodynamic control surfaces, 14-Electronic speed controller, 15-Electric motor, 16-Lithium-ion battery pack, 17-Flight control module, 18-Navigation and data link module, 19-GPS positioning antenna, 20-Airborne omnidirectional antenna, 21-Vehicle end, 22-Ground end, 23-Helmet display, 24-Flight control stick, 25-Parachute rocket, 26-Parachute assembly, 27-Human-machine separation device, 28-Parachute deployment control assembly, 29-Main frame, 30-Wearable restraint system, 31-Landing gear. Detailed Implementation

[0023] like Figure 1 , Figure 2 As shown, this invention proposes a three-duct single-person vertical take-off and landing aircraft system, including a power system, an avionics system 4, a human-machine interaction system 5, a safety and rescue system 6, and a wearable fuselage 7. It can realize single-person vertical take-off and landing and all-directional maneuvering flight. The system has the characteristics of good maneuverability, low requirements for take-off and landing sites, and low operating costs.

[0024] The aircraft features an optimized aerodynamic layout. Its power unit is a ducted power unit arranged in a triangular configuration, employing a three-duct aerodynamic layout. The two front ducted units are positioned at the same height on either side of the wearable fuselage. The rear ducted unit is installed at a higher height than the front ducted units. In this invention, the rear ducted unit is 0.5m higher than the front ducted unit, which reduces the inflow interference from the occupants and the front ducted unit to the rear ducted unit during forward flight, improving forward flight efficiency and stability. The human-machine interface system is located on the left side of the wearable fuselage and above the user's head, used for manual flight control and monitoring of flight status. The safety and rescue system is located on the upper part of the wearable fuselage, used to ensure personnel safety in emergencies.

[0025] Figure 8 This is a schematic diagram illustrating the effect of the rear duct layout of the wearable aircraft of the present invention on the flow field. When all three ducts are arranged in the middle of the aircraft, the airflow entering the rear duct is blocked by the human body during forward flight, generating vortices and reducing the efficiency of the power system, as shown in Figure (b). When the rear duct is arranged on the upper part of the aircraft, the vortices caused by the human body can be avoided during forward flight, as shown in Figure (a). At the same time, the front duct of the aircraft of the present invention is arranged in the middle of the aircraft, which is closer to the center of gravity of the aircraft, improving flight maneuverability, while the rear duct is placed on the upper part of the aircraft, improving flight stability.

[0026] Furthermore, the three-duct single-person vertical take-off and landing aircraft has two aerodynamic control surfaces 9 driven by servo motors 8 installed below the ducts on both the left and right sides. There are no aerodynamic control surfaces in the rear duct. By adjusting the rotor speed and aerodynamic control surface deflection angle in each duct, the aircraft can balance the anti-torque and heading control of the rotor in the rear duct.

[0027] like Figure 3 As shown, the power subsystem includes power unit A1, power unit B2, and power unit C3. Power units A1 and B2 are located on the left and right sides of the wearable fuselage, respectively, in a symmetrical distribution. Each includes a duct 10, blades 11, tail cone 12, aerodynamic control surfaces 13, electronic speed controller (ESC) 14, motor 15, and servo motor 8. The duct 10 and blades 11 provide the thrust required for flight. The blades 11 are located in the duct 10 and connected by the aerodynamic control surfaces 13. The tail cone 12 is located below the blades 11 and is used to support the ESC 14, motor 15, servo motor 8, and airborne omnidirectional antenna 20. The ESC 14 is used to adjust the motor speed, the motor 15 is used to drive the blades, and the servo motor 8 is used to drive the control surfaces. The aerodynamic control surfaces 13 provide the directional control force required for maneuvering flight.

[0028] The power unit C3 is located at the rear of the wearable device and includes a duct 10, blades 11, tail cone 12, ESC 14, and motor 15. Blades 11 are located in the duct 10 and provide the thrust required for flight. Tail cone 12 is located below blades 13 and is used to carry ESC 14, motor 15, and GPS positioning antenna 19.

[0029] like Figure 4 As shown, the avionics system 4 includes a lithium-ion battery pack 16, a flight control module 17, a navigation and data link module 18, a GPS positioning antenna 19, and an airborne omnidirectional antenna 20. The lithium-ion battery pack 16 powers each subsystem and is located at the rear of the fuselage, carried by the wearable fuselage. The flight control module 17 is used to stabilize the flight of the single-person aircraft. The navigation and data link module 18 is used to provide flight status information to the flight control module 17 and transmit information to the ground station. It is located on the top of the wearable fuselage. The three GPS positioning antennas 19 are arranged at the three equal divisions of the rear duct, serving as backups for each other, and are used for differential positioning. The airborne omnidirectional antenna 20 is used to communicate with the ground control station and is located inside the tail cones of the left and right ducts.

[0030] like Figure 5As shown, the human-machine interaction system 5 includes two subsystems: the vehicle terminal 21 and the ground terminal 22. The vehicle terminal 21 includes a helmet-mounted display 23 with built-in voice equipment and a flight control joystick 24, which are used by the aircraft passengers to monitor the flight mission status in real time, communicate with ground personnel and other aircraft passengers in the air via voice, and switch the aircraft to manual piloting mode at any time to manually control the aircraft. The ground terminal 22 is a handheld portable aircraft ground control station, which is used for checking the configuration of various parameters before the aircraft takes off, flight mission planning mainly includes route planning, and monitoring the flight and mission status throughout the flight, as well as communicating with the aircraft passengers via voice.

[0031] like Figure 6 As shown, the safety and rescue system 6 includes a parachute rocket 25, a cluster parachute assembly 26, a human-machine separation device 27, and a parachute deployment control assembly 28. The human-machine separation device 27 is installed at the junction of the aircraft structure and the back of the human. This device is connected to the wearable restraint system 30 and the aircraft structure via a buckle. In an emergency, the buckle is pulled out, and the wearable restraint system is separated from the aircraft structure. The parachute deployment control assembly 28 is installed on the top of the aircraft structure and is used to control the deployment of the parachutes. The parachute rocket 25 and the cluster parachute assembly 26 are installed on the upper end face of the battery compartment. When the safety and rescue system needs to be activated, the controller first issues a recovery command to enter the recovery procedure. Then, the parachute canopy explodes and the canopy canopy is jettisoned. The parachute rocket 25 is then launched, and the restraints are unlocked from the fuselage to achieve human-machine separation. The parachute rocket 25 pulls out the pin that secures the main parachute restraints, pulling the cluster parachutes out of the canopy. After the cluster parachute assembly 26 is straightened, it is separated from the rocket and the main parachute by tearing the belt. The main parachute is inflated by the airflow and fully opens, carrying the occupants to a stable descent until landing.

[0032] like Figure 7 As shown, the wearable fuselage 7 is mainly composed of a main frame 29, a wearable restraint system 30, and a fuselage landing gear 31. The main frame 29 enables quick assembly and disassembly of the ducted power unit through a pin structure, and also carries other systems such as the power battery, parachute rocket, and parachute compartment. The wearable restraint system 30 consists of shoulder straps, waist straps, leg straps, and a detachable backplate. The human body is fixed to the detachable backplate by the shoulder straps and straps. The detachable backplate is connected to the main frame 29 through a separation mechanism. The fuselage landing gear 31 is located at the rear of the fuselage to provide stable support for the aircraft when it is parked on the ground.

[0033] The present invention will now be described in further detail with reference to the accompanying drawings.

[0034] Example

[0035] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. All other embodiments obtained by those skilled in the art based on the embodiments in this application without inventive effort are within the scope of protection of this application.

[0036] Combination Figures 2-7 The wearable triple-duct single-person vertical takeoff and landing (VTOL) aircraft system consists of a power system, avionics system 4, human-machine interface system 5, safety and rescue system 6, and wearable fuselage 7. When not in use, the system can be stored independently in its associated storage compartment. During storage and transportation, the flight platform is physically isolated by power outages, and the high-voltage battery and associated BMS have no output when power is cut off, ensuring system safety.

[0037] When a mission is required, the components of the single-person aircraft are transported to the takeoff point and quickly assembled using quick-connect structures. After assembly and verification, the system's low-voltage avionics are powered on with a single button and perform a system self-test. The system's sensor status is displayed on the ground to determine whether it meets takeoff standards.

[0038] After the self-check is completed, the mission trajectory plan is uploaded. At this point, the system is ready and enters the takeoff phase.

[0039] After verifying that all systems are working properly, the mission trajectory plan is uploaded from the ground. At this point, the system is ready and enters the takeoff phase. The ground sends a high-voltage battery power-on command, and the airborne flight controller starts the three high-voltage outputs through the I / O control of the BMS.

[0040] like Figure 9 As shown, the single-person aircraft can take off autonomously by pressing the one-button takeoff button. The onboard flight control module dynamically adjusts the output power of each duct and hovers autonomously at a height of 0.5m above the ground. At this time, the pilot can back up into the aircraft facing outwards. The pilot or an assistant can use the aircraft's fixing device to secure the pilot to the aircraft. In this state, the pilot stands naturally with both feet on the ground, holds the aircraft joystick with the left hand, and places the right hand naturally on the right armrest.

[0041] The single-person aircraft is taken off by a pilot or ground control. The pilot's feet leave the ground, and during flight, the single-person aircraft can be controlled in multiple ways:

[0042] If the ground control and the pilot do not perform any operations during the flight, the aircraft can fly autonomously through the pre-uploaded route and land autonomously at the end of the route to hover at a height of 0.5m above the ground, waiting for subsequent instructions.

[0043] During flight, control commands are issued from the ground station, and the single-person aircraft receives the commands from the ground station via the onboard data link and flies according to the commands;

[0044] During flight, the pilot controls the aircraft using the onboard joystick. The aircraft can perform operations such as flying forward, backward, moving left, moving right, and ascending / descending. At this time, the single-person aircraft takes priority in responding to the pilot's operations.

[0045] When the flight mission ends, the single-person aircraft can land via the flight path, the ground terminal, or the pilot. During the landing process, the aircraft first descends to a height of 0.5m above the ground and hovers. At this time, the pilot's feet touch the ground and the legs stand naturally.

[0046] After the pilot's feet touch the ground, with the assistance of support personnel, the safety restraints are released, and the pilot safely detaches from the aircraft. The ground unit sends a one-key landing command to the airborne flight controller, which dynamically adjusts the power output of each duct to control the aircraft to slowly descend to the ground.

[0047] After the aircraft lands on the ground, the high-voltage battery management system shuts down its three high-voltage outputs. Once the ground receives the high-voltage power-off status, it then performs low-voltage power-off operations on electrical components such as the flight control system, data link, GPS, and high-voltage battery management system. After all avionics equipment is powered off, special tooling is used for rapid disassembly, and each component of the aircraft is stored separately, completing the mission process.

[0048] When a pilot experiences a system malfunction during flight that causes the aircraft to fail at low altitude, the pilot or ground control can use a button on the joystick or send a command to control the one-button parachute deployment. Upon receiving the one-button parachute deployment command, the safety system will deploy the parachute within a short time and simultaneously release the pilot from the aircraft, enabling the personnel to abandon the aircraft and escape.

[0049] In summary, this wearable three-duct single-person vertical take-off and landing aircraft system allows the pilot to perform tasks without any operation or with only simple directional control. Compared with existing single-person aircraft, it has advantages such as vertical take-off and landing, ease of operation, high level of intelligence, stable performance, and good safety.

[0050] Obviously, those skilled in the art can make various modifications and variations to the embodiments of the present invention without departing from the spirit and scope of the embodiments of the present invention. Thus, if these modifications and variations to the embodiments of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention also intends to include these modifications and variations.

[0051] The control block diagram for the pitch and tilt of a tri-rotor is as follows: Figures 10-12 As shown, the specific methods for position and attitude control of a dual-servo tilt-rotor tri-rotor UAV include:

[0052] (1) Establish a body coordinate system for a dual-servo tiltrotor UAV.

[0053] The coordinate system is fixed to the body, such as Figure 10 As shown. The three rotors of the UAV are numbered as Rotor 1, Rotor 2, and Rotor 3. The origin is the center of gravity of the UAV. b Forward is x b The positive direction of the axis, to the right is y b The positive direction of the axis is downwards (z). b Positive direction of the axis.

[0054] (2) Establish a control efficiency model for a dual-servo tilt-rotor UAV. For example... Figure 10 As shown, the established control efficiency model is as follows:

[0055]

[0056] In this model, {F x F y F z} represent the tension forces acting on the three coordinate axes of the body coordinate system, respectively; {τ x τ y τ z {T1, T2, T3} represent the torques acting on the three coordinate axes of the body coordinate system, respectively; {T1, T2, T3} represent the thrust generated by the three rotors themselves, and their range is [0, T1, T2, T3]. max ], T max This indicates the maximum thrust that each rotor can generate; This represents the x-coordinate of rotor 1 or rotor 2 relative to the body coordinate system. b The included angle formed by the axes; This indicates the motor mounting center of rotor 1 or rotor 2 relative to the fuselage x. b Along the y axis b Distance between axes; The line connecting the motor mounting centers of rotors 1 and 2 is shown along the x-axis relative to the center of mass of the aircraft. b Distance between axes; This indicates the x-axis distance between the motor mounting center of rotor 3 and the aircraft's center of mass. b The distance; δ1 and δ2 represent the angles between the control surfaces of rotor 1 and rotor 2 and the vertical direction of the body coordinate system, respectively, such as Figure 11 As shown, the symbol definition of the vertical angle between the control surface corresponding to rotor 1 and the body coordinate system is illustrated; c represents the proportional coefficient of the thrust-to-torque generated by the rotor.

[0057] (3) Establish a control allocation method for a dual-servo tilt-rotor tri-rotor UAV. The control allocation method is expressed mathematically as follows:

[0058]

[0059] Among them, {F x,d F y,d F z,d} represent the forces expected to act on the three axes of the body coordinate system; {τ x,d τ y,d τ z,d} represent the desired torques exerted by the three rotors on the three axes of the body coordinate system; τ z,δ,d The desired yaw torque is generated by the servo motor control surface.

[0060] (4) Establish an attitude control method for a dual-servo tilt-rotor tri-rotor UAV. The control method adopts traditional PID control, where the desired input for PID control is the desired roll angle φ. d Pitch angle θ d Yaw angle ψ d The feedback inputs for PID control are the current UAV's roll angle φ, pitch angle θ, yaw angle ψ, roll rate p, pitch rate q, and yaw rate r; the output of the PID controller is the desired force {F} acting on the three axes of the body coordinate system. x,d F y,d F z,d}, the desired torques {τ} exerted by the three rotors on the three axes of the body coordinate system. x,d τ y,d τ z,d}, and the expected yaw moment τ generated by the servo control surface. z,δ,d The output of the PID controller serves as the input to the control assignment. The structural relationship between the controller and the control assignment is as follows: Figure 12 As shown. The specific steps for constructing the attitude controller are as follows:

[0061] Step 4.1: Calculate the desired airframe angular rate {p} based on the desired roll angle, pitch angle, yaw angle, and the current roll angle, pitch angle, and yaw angle of the three-ducted aircraft. d q d r d}

[0062] p d =k roll,p (φ d -φ)

[0063] q d =k pitch,p (θ d -θ)

[0064]

[0065] in, Represents ψ d The numerical derivative, Represents the numerical derivative of ψ; This is an adjustable parameter.

[0066] Step 4.2: Based on the desired body angular velocity {p d q d r d The desired torque is calculated using the current body angular rate {pqr}.

[0067]

[0068]

[0069] τ z,d =k yawrate,p (r d -r)+k yawrate,i ∫(r d -r)

[0070] τ z,δ,d =k yawrate,p2 (r d -r)+k yawrate,i2 ∫(r d -r)

[0071] in, p d The numerical derivative, This represents the numerical derivative of p. q d The numerical derivative, Represents the numerical derivative of q; All parameters are adjustable.

[0072] Step 4.3: Based on the desired flight altitude p z,d and the current height p z and vertical velocity v z Calculation of the effect on the three-ducted aircraft z b Tension F on the shaft z,d .

[0073] v z,d =sat(k p,z (p z,d -p z ),2)

[0074] F z,d =k v,z,p (v z,d -v z )+k v,z,i ∫(v z,d -v z )

[0075] in, All are adjustable parameters, and sat represents the saturation function, defined as follows:

[0076]

[0077] (5) The expected value F calculated in step (4) z,d , τ x,d , τ y,d , τ z,d , τ z,δ,d Substitute these values ​​into the control allocation matrix designed in step (3) to obtain the final control commands T1, T2, T3, δ1, δ2.

[0078] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any transformations or substitutions that can be conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A wearable, three-duct powered, single-person aircraft, characterized in that, Including the power system, avionics system (4), human-machine interaction system (5), safety and life-saving system (6), and wearable fuselage (7); The power system includes three power units, which adopt a three-duct aerodynamic layout in a triangular arrangement. The two front duct units are located at the same height on both sides of the wearable fuselage, and the rear duct unit is installed at a higher height than the front duct unit. The human-machine interaction system (5) is located on one side of the wearable fuselage (7) and the human head, and is used to manually control the flight and monitor the flight status. The safety and life-saving system (6) is located on the upper part of the wearable fuselage (7) and is used to ensure the safety of personnel in emergency situations. The avionics system (4) provides power supply, flight control and positioning and navigation for the entire aircraft. Two aerodynamic control surfaces (13) driven by servo motors (8) are installed under the ducts on both the left and right sides. There are no aerodynamic control surfaces in the rear duct. By adjusting the rotor speed and aerodynamic control surface deflection angle in each duct, the anti-torque and heading control of the rotor in the rear duct are balanced. Of the three power units, power unit A and power unit B are located on the left and right sides of the wearable fuselage, respectively, and are symmetrically distributed. Each includes a duct (10), a blade (11), a tail cone (12), an aerodynamic control surface (13), an electronic speed controller (ESC) (14), and a motor (15). The duct (10) and the blade (11) provide the thrust required for flight. The blade (11) is located in the duct (10), and the tail cone (12) is located below the blade (11) and is used to support the ESC (14), the motor (15), the servo (8), and the airborne omnidirectional antenna (20). The ESC (14) is used to adjust the motor speed, the motor (15) is used to drive the blade, the servo (8) is used to drive the control surface, and the aerodynamic control surface (13) provides the heading control force required for maneuvering flight.

2. The wearable three-duct powered single-person aircraft according to claim 1, characterized in that, Of the three power units, power unit C (3) is located at the rear of the wearable device and includes a duct (10), blades (11), tail cone (12), ESC (14), motor (15), and GPS positioning antenna (19). The blades (11) are located in the duct (10) and provide the thrust required for flight. The tail cone (12) is located below the blades (11) and is used to support the ESC (14), motor (15), and GPS positioning antenna (19).

3. The wearable three-duct powered single-person aircraft according to claim 1 or 2, characterized in that, The rear culvert unit is installed at a height 0.5m higher than the front culvert unit.

4. The wearable three-duct powered single-person aircraft according to claim 2, characterized in that, The avionics system includes a lithium-ion battery pack (16), a flight control module (17), a navigation and data link module (18), a GPS positioning antenna (19), and an airborne omnidirectional antenna (20). The lithium-ion battery pack (16) supplies power to each subsystem and is located at the rear of the fuselage, carried by the wearable fuselage. The flight control module (17) is used to stably control the flight of the single-person aircraft. The navigation and data link module (18) is used to provide flight status information to the flight control module (17) and transmit information to the ground station. It is located on the top of the wearable fuselage. The airborne omnidirectional antenna (20) is used to communicate with the ground control station and is located inside the tail cones of the left and right ducts.

5. The wearable three-duct powered single-person aircraft according to claim 4, characterized in that, Three GPS positioning antennas (19) are arranged at the three equal divisions of the rear duct, serving as backups for each other, for differential positioning.

6. The wearable three-duct powered single-person aircraft according to claim 1, characterized in that, The human-machine interaction system (5) includes a vehicle terminal (21) and a ground terminal (22). The vehicle terminal (21) includes a helmet display (23) with built-in voice equipment and a flight control joystick (24), which is used for the aircraft passengers to monitor the flight mission status in real time, communicate with ground personnel and other aircraft passengers in the air via voice, and switch the aircraft to manual driving mode at any time to manually control the aircraft. The ground terminal (22) is a handheld portable aircraft ground control station, which is used for checking the configuration of various parameters before the aircraft takes off, planning the flight mission, and monitoring the flight and mission status throughout the flight, and communicating with the aircraft passengers via voice.

7. The wearable three-duct powered single-person aircraft according to claim 1, characterized in that, The safety and rescue system (6) includes a parachute rocket (25), a cluster of parachutes (26), a human-machine separation device (27), and a parachute deployment control component (28). The human-machine separation device (27) is installed at the junction of the aircraft structure and the back of the human body. This device connects the wearable restraint system (30) to the aircraft structure via buckles. In an emergency, the buckles are pulled out, and the wearable restraint system separates from the aircraft structure. The parachute deployment control component (28) is installed on the top of the aircraft structure and is used to control the deployment of the parachutes. The parachute rocket (25) and the cluster of parachutes... (26) Installed on the upper end face of the battery compartment. When the safety rescue system needs to be activated, the controller first issues a recovery command to enter the recovery procedure. Then the parachute compartment cover explodes and the parachute compartment cover is jettisoned. Then the parachute rocket (25) is launched. The straps are unlocked from the fuselage to achieve separation of man and machine. The parachute rocket (25) pulls out the pin that fixes the main parachute strap and pulls the parachute out of the parachute compartment. After the parachute assembly (26) is straightened, the rocket is separated from the main parachute by tearing the tear strip. The main parachute enters the airflow and inflates fully, carrying the crew to a stable landing.

8. The wearable three-duct powered single-person aircraft according to claim 1, characterized in that, The wearable fuselage (7) is mainly composed of a main frame (29), a wearable restraint system (30), and a fuselage landing gear (31). The main frame (29) enables the quick assembly and disassembly of the ducted power unit through a pin structure, and simultaneously carries the power battery, parachute rocket, and parachute compartment. The wearable restraint system (30) includes shoulder straps, waist fixing straps, leg fixing straps, and a detachable back panel. The human body is fixed to the detachable back panel through the shoulder straps and straps. The detachable back panel is connected to the main frame (29) through a separation mechanism. The fuselage landing gear (31) is located at the rear of the fuselage to provide stable support for the aircraft when it is parked on the ground.

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