An open single-person aircraft structure

Abstract

The utility model discloses an open type single person aircraft structure, including left duct power unit, right duct power unit, rear duct power unit, body structure, wear structure, safety lifesaving mechanism and avionics mechanism, left duct power unit, right duct power unit and rear duct power unit adopt three duct aerodynamic layout structure, and it is arranged in the shape of a triangle, body structure setting in three duct aerodynamic layout structure center position, one side fixedly connected with wear structure of body structure, and the other side fixedly connected with avionics mechanism, safety lifesaving mechanism setting in the upper of avionics mechanism, the utility model discloses compact, possess flight steady and the characteristic of flexible operation, the setting of safety lifesaving mechanism has realized single person aircraft low altitude emergency personnel to abandon the plane and escape, improves personnel safety and reduces aircraft system weight simultaneously, through the quick plug -and -play design has realized the duct power unit and fuselage quick connection configuration, improves assembly efficiency and aircraft transportation convenience.

Description

Technical Field

[0001] This utility model belongs to the field of manned aircraft technology, and in particular relates to an open single-person aircraft structure. Background Technology

[0002] Wearable single-person aerial vehicles (SVTOLs), as a relatively novel type of aircraft, have significant application potential in the civilian sector. They are primarily used in high-rise building fire emergency rescue scenarios, combining firefighting and rescue functions. In specialized fields such as fire fighting, customs, and coast guard, they are used for tethered firefighting, rescuing people trapped in high-rise buildings, and coast guard boarding operations. In the high-altitude operations sector, they are used for high-altitude work in industries such as power, and for unmanned cleaning of glass curtain walls. In the entertainment sector, they are used in scenic spots and amusement parks for single-person flight experiences, opening up new modes of aerial recreation. With the gradual maturation of key technologies for small vertical take-off and landing (VTOL) aircraft, SVTOLs are increasingly being used in the civilian sector to improve the maneuverability and flexibility of pilots. SVTOLs can work in confined spaces, are not limited by urban environments, operate close to buildings, and are unaffected by wall impacts.

[0003] Existing single-person aircraft are mainly powered by turbojet engines. The human carries and holds several miniature turbojet engines, and achieves vertical take-off and landing and cruise flight by controlling the attitude of several miniature turbojet engines, thereby improving the human's mobility. However, since the flight attitude is directly related to the human body attitude, it has high requirements for the physical fitness and control ability of the human, which is not conducive to its widespread use. At the same time, the hands are occupied during the flight, making it impossible to control the equipment in the air. Utility Model Content

[0004] The purpose of this invention is to address the problems mentioned in the background art by proposing an open-type single-person aircraft structure. This aircraft comprises a three-ducted propulsion system, an airframe structure system, a safety and survival system, and an avionics system. It integrates key technologies such as high thrust-to-weight ratio ducted propulsion design, three-ducted propulsion flight control, and low-altitude / ultra-low-altitude emergency escape, forming a wearable ducted-powered single-person aircraft. This aircraft has a compact structure and features high stability, ease of operation, and good safety.

[0005] To achieve the purpose of this utility model, an open-type single-person aircraft structure is disclosed, including a left ducted power unit, a right ducted power unit, a rear ducted power unit, a fuselage structure, a wearable structure, a safety and rescue mechanism, and an avionics mechanism; the left ducted power unit, the right ducted power unit, and the rear ducted power unit adopt a three-ducted aerodynamic layout structure, arranged in a triangular pattern; the fuselage structure is located at the center of the three-ducted aerodynamic layout structure; the wearable structure is fixedly connected to one side of the fuselage structure, and the avionics mechanism is fixedly connected to the other side; the safety and rescue mechanism is located above the avionics mechanism.

[0006] Furthermore, the left and right duct power units are located at the same height on both sides of the fuselage structure, while the rear duct power unit is higher than the left and right duct power units.

[0007] Furthermore, the left duct power unit, right duct power unit, and rear duct power unit all use the same power system; the power system includes the duct, blades, tail cone, main beam, and motor; the blades are arranged in a circular array at the center of the duct and are fixed by bolts to the upper and lower hubs; the head of the main beam is installed on the inner wall of the duct through the main beam connector, and the end of the main beam is bolted to the motor mount; the motor is nested inside the motor mount; the rectifier arm is distributed at a 90° angle to the main beam, and the end of the rectifier arm is bolted to the motor mount; the airborne omnidirectional antenna is located on the upper arc arm of the duct; the cone and tail cone are connected by rivets, and heat dissipation fins are arranged on the side of the cone; the tail cone houses the motor, ESC, and GPS positioning antenna.

[0008] Furthermore, the left and right ducted power units have upper crossbeams, servos, and servo-driven aerodynamic control surfaces mounted below their power systems. The main beam incorporates a spatial structure to avoid interference with the upper crossbeams and aerodynamic control surfaces. The propeller blades are connected to the aerodynamic control surfaces via four hinges, and the motors adjust the speed of the blades and the deflection angle via the aerodynamic control surfaces. The aircraft can balance the anti-torque of the rear ducted rotor and achieve directional control. The aerodynamic control surfaces provide the control force required for maneuvering flight, while the duct and blades provide the thrust required for flight. The rear ducted power unit lacks aerodynamic control surfaces and is installed at a relatively higher height to reduce airflow interference from the crew and the front ducted unit to the rear ducted unit during forward flight, thereby improving forward flight efficiency and stability.

[0009] Furthermore, the airframe structure includes a U-shaped main frame and landing gear. The U-shaped main frame has a seat-backpack-like structure, comprising several parallel U-shaped main load-bearing crossbeams and secondary crossbeams in the xy plane, a U-shaped main load-bearing longitudinal beam in the yz plane, and several relatively vertically distributed secondary longitudinal beams. The beams are thin-walled circular tubes, integrally formed through welding. The U-shaped main frame has diagonal braces on both sides, which can be flexibly disassembled to ensure personnel safety during flight. The crossbeams and longitudinal beams are welded at their intersections to form a closed-loop force distribution. A battery base is installed at the bottom of one U-shaped main load-bearing longitudinal beam, with two straight sliding grooves and a limiting slot for battery installation detection. The backplate adapter is installed symmetrically at the intersection of the upper secondary crossbeam and the middle main load-bearing crossbeam, and is locked with positioning screws. Battery positioning locking blocks are installed on both secondary longitudinal beams, adjacent to the upper secondary crossbeam, to ensure the battery pack is locked. The U-shaped main frame extends outwards... The welded chute structure incorporates an integrated female connector; the ducted power unit cantilever is externally connected to an integrated male connector, and the integrated female and male connectors achieve quick assembly and disassembly of the U-shaped main frame and the ducted power unit through mating; locking blocks are located on the outside of the U-shaped main frame, pressing the ducted power unit cantilever to ensure the strength of the cantilever end; the handheld control stick is located at the front left side of the U-shaped main frame for direct operation; the lower U-shaped main load-bearing beam is fully welded with 16 nuts, and the fuselage landing gear is located below the lower U-shaped main load-bearing beam to provide stable support for the aircraft when parked on the ground; the fuselage landing gear consists of three "Y"-shaped tubular sections, two of which are fixed by a T-joint structure, and the fuselage landing gear is connected to the lower main load-bearing beam of the U-shaped main frame through a landing gear adapter; shock-absorbing balls are located at the bottom of the fuselage landing gear to buffer impacts and protect the structure during aircraft landing and ground operations.

[0010] Furthermore, the wearable structure includes a detachable back panel, shoulder straps, chest straps, waist securing straps, and leg securing straps. The shoulder straps, chest straps, waist securing straps, and leg securing straps are mounted on the detachable back panel, and the human body is secured to the detachable back panel via the straps and straps. The detachable back panel is connected to the back panel adapter of the body structure via a separation mechanism. The separation mechanism includes a distributed four-pin mechanism and an unlocking mechanism. The unlocking mechanism is composed of steel wire ropes and plastic tubes. The pin mechanism is moved by the steel wire ropes, which are fixed in position and direction within the plastic tubes. The four ropes converge on the fixing mechanism. The fixing mechanism consists of a latch, a lock seat, and a cover plate. The four pin ropes are fixed on the latch, which can rotate around the rotation axis of the lock seat, synchronously pulling the ropes. The cover plate is used to fix the four plastic tubes. There are two hanging ear structures on each side of the groove inside the unlocking mechanism. The hanging ear structures are connected to the pin mechanism by two miniature springs. An energy storage spring is provided between the separation mechanism and the unlocking mechanism. When the connector is inserted into the latch in the correct position, the pin engages with the connector groove, forming an automatic reset mechanism. When the separation mechanism receives a command, the energy storage spring between the separation mechanism and the unlocking mechanism causes the back plate adapter to pop out, preventing the latch from jamming.

[0011] Furthermore, the safety and rescue mechanism includes a parachute assembly and a parachute-person connection device; the parachute assembly and parachute-person connection device are installed on the upper end face of the avionics mechanism. The parachute assembly consists of an explosive bolt, a canopy cover, a parachute rocket, a fixed main parachute, and a tear strip; the explosive bolt is located on the outside of the canopy cover, the parachute rocket is located at the lower end of the canopy cover, close to the canopy cover, the fixed main parachute is connected to the parachute rocket, and is compressed inside the parachute assembly by the tear strip. When the parachute rocket is launched, it drives the fixed main parachute to open the tear strip and deploy the parachute. When the safety and rescue system needs to be activated, the controller first issues a command, then the explosive bolt inside the parachute assembly jettisons the canopy cover, followed by the launch of the parachute rocket. The separation mechanism unlocks from the back panel adapter to achieve separation of the human and the aircraft. The parachute rocket pulls out the pin of the fixed main parachute strap, pulling the main parachute out of the canopy. After all components are straightened, the parachute rocket is separated from the main parachute by tearing the tear strip. The main parachute enters the airflow, inflates fully, and carries the occupants down steadily until landing.

[0012] Furthermore, the avionics system includes a high-voltage battery pack and a hardware module compartment. The high-voltage battery pack is installed via two directional rails on the battery base of the lower support rod at the rear of the U-shaped main frame of the fuselage structure. It is fixed to the rear of the fuselage with bolts and battery positioning locking blocks, forming a "backpack-style" battery. The high-voltage battery pack is charged through three high-voltage charging modules. The hardware module compartment is located above the high-voltage battery pack, with a parachute assembly mounted on the upper left. The uppermost crossbeam of the fuselage runs through the hardware module compartment. The hardware module compartment consists of a navigation and data link module, a flight control module, a GPS module, a CAN relay board, an Ethernet relay module, and a low-voltage battery pack. The system consists of a magnetic closure device, with the left, right, and rear connectors respectively docking with the locking block. The low-voltage battery pack powers each mechanism and can be removed and removed via the magnetic closure device. The flight control module is used to stabilize the flight of the single-person aircraft, while the navigation and data link module provides flight status information to the flight control module. Three GPS positioning antennas are arranged at the three equal divisions of the rear duct, serving as backups for each other and used for differential positioning. The left and right connectors are routed inside the main load-bearing crossbeams on the lower side of the U-shaped main frame, while the rear connector is routed inside the main load-bearing longitudinal beams on the U-shaped main frame, converging in the hardware module compartment, with the wiring not exposed.

[0013] Furthermore, the quick-release connector consists of an integrated male connector connected to the cantilever end of the ducted power unit and an integrated female connector connected to the U-shaped main body frame; the integrated male connector is designed with a limiting pin and the integrated female connector is designed with a limiting groove for precise insertion and removal, and is pressed by a locking block on the upper side.

[0014] Compared with the prior art, the significant advancements of this utility model are as follows: 1) It proposes an open single-person aircraft structure system based on a three-ducted propulsion system, achieving compact size and high safety, and possessing the characteristics of flight stability and flexible operation; 2) It proposes a novel low-altitude and ultra-low-altitude emergency escape technology for single-person aircraft, which enables personnel to abandon the aircraft and escape in low-altitude emergencies through a human-machine separation device, parachute assembly, group parachute assembly, and parachute opening control assembly, improving personnel safety while reducing the weight of the aircraft system; 3) It proposes a quick-plug design technology to achieve rapid connection and configuration of the ducted propulsion unit and the fuselage, improving assembly efficiency and the convenience of aircraft transportation.

[0015] To more clearly illustrate the functional characteristics and structural parameters of this utility model, the following description is provided in conjunction with the accompanying drawings and specific embodiments. Attached Figure Description

[0016] The accompanying drawings, which are included to provide a further understanding of the present invention and form part of this application, illustrate exemplary embodiments of the present invention and, together with the description thereof, serve to explain the present invention and do not constitute an undue limitation thereof. In the drawings:

[0017] Figure 1This is a schematic diagram of the overall structure of the present invention;

[0018] Figure 2 a, Figure 2 b is a schematic diagram of the power system layout;

[0019] Figure 3 a, Figure 3 b is a schematic diagram of the left duct power unit structure;

[0020] Figure 4 This is a structural diagram of the body of this utility model;

[0021] Figure 5 This is a diagram of the safety and life-saving system of this utility model;

[0022] Figure 6 a, Figure 6 b is a wearable diagram of this utility model;

[0023] Figure 7 a, Figure 7 b is a diagram of the avionics system of this utility model;

[0024] Figure 8 Schematic diagram of an explosion of an integrated pluggable connector;

[0025] The attached diagram is labeled as follows: 1. Left ducted power unit; 2. Right ducted power unit; 3. Rear ducted power unit; 4. Airframe structure; 5. Wearable structure; 6. Safety and rescue mechanism; 7. Avionics mechanism; 8. Upper crossbeam; 9. Servo; 10. Aerodynamic control surface; 11. Duct; 12. Propeller blade; 13. Tail cone; 14. Main beam; 15. Motor; 16. Motor mount; 17. Upper hub; 18. Lower hub; 19. Rectifier arm; 20. Airborne omnidirectional antenna; 21. Main beam connector; 22. Heat dissipation fin; 23. Integrated male connector; 24. Hinge; 25. Electronic speed controller; 26. GPS positioning antenna; 27. U-shaped main frame; 28. Airframe landing gear; 29. ​​Shock absorber ball; 30. Diagonal brace; 31. Battery base; 32. Locking block; 33. Integrated female connector; 34. Battery positioning locking block; 35. Landing gear adapter; 36. Backplate adapter; 37. Hand joystick; 38. Ducted power unit cantilever. 39 Detachable back panel, 40 shoulder straps, 41 chest strap, 42 waist fixing strap, 43 leg fixing strap, 44 separation mechanism, 45 pin mechanism, 46 unlocking mechanism, 47 steel wire rope, 48 plastic tube, 49 fixing mechanism, 50 locking tongue, 51 locking seat, 52 cover plate, 53 rope, 54 hanging ear structure, 55 miniature spring, 56 energy storage spring, 57 parachute assembly, 58 parachute connection device, 60 explosive bolt, 61 parachute compartment cover, 62 parachute rocket, 63 fixed main parachute, 64 high-voltage battery pack, 65 hardware module compartment, 66 navigation and data link module, 67 flight control module, 70 low-voltage battery pack, 71 magnetic closing device, 72 left connector, 73 right connector, 74 rear connector, 75 sliding groove structure, 77 GPS module, 78 CAN relay board, 79 Ethernet relay module, 80 high-voltage charging module. Detailed Implementation

[0026] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the protection scope of the present utility model.

[0027] like Figure 1 As shown, an open-type single-person aircraft structure includes a left ducted power unit 1, a right ducted power unit 2, a rear ducted power unit 3, a fuselage structure 4, a wearable structure 5, a safety and rescue mechanism 6, and an avionics mechanism 7. The left ducted power unit 1, the right ducted power unit 2, and the rear ducted power unit 3 adopt a three-ducted aerodynamic layout structure and are arranged in a triangular pattern. The fuselage structure 4 is located at the center of the three-ducted aerodynamic layout structure. The wearable structure 5 is fixedly connected to one side of the fuselage structure 4, and the avionics mechanism 7 is fixedly connected to the other side. The safety and rescue mechanism 6 is located above the avionics mechanism 7.

[0028] Specifically, the left duct power unit 1 and the right duct power unit 2 are located at the same height on both sides of the body structure 4, while the rear duct power unit 3 is higher than the left duct power unit 1 and the right duct power unit 2.

[0029] like Figure 2 a, Figure 2 b、 Figure 3 a, Figure 3 As shown in b, the left duct power unit 1, right duct power unit 2, and rear duct power unit 3 use the same power system; the power system includes a duct 11, blades 12, tail cone 13, main beam 14, and motor 15; the blades 12 are arranged in a circular array at the center of the duct 11 and are fixed by bolts to the upper hub 17 and the lower hub 18; the head of the main beam 14 is installed on the inner wall of the duct 11 through the main beam connector 21, and the end of the main beam 14 is locked to the motor mount 16 by bolts; the motor 15 is nested in the motor mount 16; the rectifier arm 19 is distributed at a 90° angle to the main beam 14, and the end of the rectifier arm 19 is locked to the motor mount 16 by bolts; the airborne omnidirectional antenna 20 is located on the upper arc arm of the duct 11; the cone and tail cone 13 are connected by rivets, and the heat dissipation fins 22 are arranged on the side of the cone; the tail cone 13 houses the motor 15, the electronic speed controller 25, and the GPS positioning antenna 26.

[0030] Specifically, the upper crossbeam 8, the servo motor 9, and the aerodynamic control surface 10 driven by the servo motor 9 are installed below the power systems of the left duct power unit 1 and the right duct power unit 2; the main beam 14 is provided with a spatial structure avoidance design for the upper crossbeam 8 and the aerodynamic control surface 10; the blade 12 is connected to the aerodynamic control surface 10 through four hinges 24, and the motor 15 adjusts the speed of the blade 12 and the deflection angle of the aerodynamic control surface 10.

[0031] like Figure 4 , Figure 8As shown, the fuselage structure 4 includes a U-shaped main frame 27 and a fuselage landing gear 28. The U-shaped main frame 27 has a seat-backpack-like structure, including several U-shaped main load-bearing crossbeams and secondary crossbeams distributed parallel to each other in the xy plane, a U-shaped main load-bearing longitudinal beam in the yz plane, and several relatively vertically distributed secondary load-bearing longitudinal beams. The beams are thin-walled circular tube structures, integrally formed by welding. The U-shaped main frame 27 has diagonal braces 30 on both sides. The crossbeams and longitudinal beams are welded at their intersections to form a closed-loop force distribution. A battery base 31 is installed at the bottom of a U-shaped main load-bearing longitudinal beam. The battery base 31 has two straight sliding grooves and a limiting slot. The backplate adapter 36 is installed at the intersection of the upper secondary crossbeam and the middle main load-bearing crossbeam, in a symmetrical shape, and is locked by positioning screws. The battery positioning locking block 34 is installed on the two secondary longitudinal beams, adjacent to the upper secondary crossbeam. The protruding ends of the U-shaped main frame 27 are welded. The sliding groove structure 75 has an integrated female connector 33 built in; the ducted power unit cantilever 38 is externally connected to an integrated male connector 23, and the integrated female connector 33 and the integrated male connector 23 achieve quick assembly and disassembly of the U-shaped main frame 27 and the ducted power unit through mating; the locking block 32 is set on the outside of the U-shaped main frame 27, and the locking block 32 presses the ducted power unit cantilever 38; the hand control stick 37 is located at the left front end of the U-shaped main frame 27; the lower U-shaped main load-bearing beam is fully welded with 16 nuts, and the fuselage landing gear 28 is located below the lower U-shaped main load-bearing beam; the fuselage landing gear 28 is three "Y"-shaped tubular components, two of which are fixed by a three-way structural component, and the fuselage landing gear 28 is connected to the lower main load-bearing beam of the U-shaped main frame 27 through the landing gear adapter 35; the shock-absorbing ball 29 is set at the bottom of the fuselage landing gear 28.

[0032] like Figure 5 , Figure 6 a, Figure 6As shown in b, the wearable structure 5 includes a detachable back panel 39, shoulder straps 40, chest straps 41, waist securing straps 42, and leg securing straps 43. The shoulder straps 40, chest straps 41, waist securing straps 42, and leg securing straps 43 are mounted on the detachable back panel 39, and the human body is secured to the detachable back panel 39 via the straps and straps. The detachable back panel 39 is connected to the back panel adapter 36 of the body structure 4 via a separation mechanism 44. The separation mechanism 44 includes a distributed four-position latch mechanism 45 and an unlocking mechanism 46. The unlocking mechanism 46 is composed of a steel wire rope 47 and a plastic tube 48. The latch mechanism 45 is connected to the body structure 4 via a steel wire rope 47 and a plastic tube 48. The wire rope 47 is pulled and moved. The wire rope 47 is fixed in position and direction inside the plastic tube 48. The four ropes converge on the fixing mechanism 49. The fixing mechanism 49 consists of a locking tongue 50, a locking seat 51 and a cover plate 52. The locking tongue 50 is fixed with the rope 53 of the four pins. The locking tongue 50 can rotate around the rotation axis of the locking seat 51 and pull the rope 53 to move synchronously. The cover plate 52 is used to fix the four plastic tubes 48. There are two hanging ear structures 54 on each side of the groove inside the unlocking mechanism 46. The hanging ear structure 54 is connected to the pin mechanism 45 by two miniature springs 55. An energy storage spring 56 is provided between the separation mechanism 44 and the unlocking mechanism 46.

[0033] Specifically, the safety and rescue mechanism 6 includes a parachute assembly 57 and a parachute-person connection device 58; the parachute assembly 57 and the parachute-person connection device 58 are installed on the upper end face of the avionics mechanism 7; the parachute assembly 57 consists of an explosive bolt 60, a canopy cover 61, a parachute rocket 62, a fixed main parachute 63, and a rip strip; the explosive bolt 60 is located on the outside of the canopy cover 61, the parachute rocket 62 is located at the lower end of the canopy cover 61, close to the canopy cover 61, the fixed main parachute 63 is connected to the parachute rocket 62, and is compressed inside the parachute assembly 57 through the rip strip, and the launch of the parachute rocket 62 drives the fixed main parachute 63 to open the rip strip and open the parachute.

[0034] When the safety and rescue system needs to be activated, the controller first issues a command, and then the explosive bolt 60 in the parachute assembly 57 ejects the parachute compartment cover 61. Then the parachute rocket 62 is launched, and the separation mechanism 44 and the back panel adapter 36 are unlocked to achieve separation of the crew and the machine. The parachute rocket 62 pulls out the pin that secures the main parachute 63, pulling the main parachute 63 out of the parachute compartment. After all the components are straightened, the parachute rocket 62 is separated from the main parachute 63 by tearing the tear strip. The main parachute 63 is inflated by the airflow and fully opens, carrying the crew to a stable descent until landing.

[0035] like Figure 7As shown in Figure a, the avionics system 7 includes a high-voltage battery pack 64 and a hardware module compartment 65. The high-voltage battery pack 64 is installed on two directional slide rails on the battery base 31 of the lower support rod on the rear side of the U-shaped main frame 27 of the fuselage structure 4. It is fixed to the rear side of the fuselage by bolts and battery positioning locking blocks 34, forming a "backpack-style" battery. The high-voltage battery pack 64 is charged by three high-voltage charging modules 80. The hardware module compartment 65 is located above the high-voltage battery pack 64, and a parachute assembly 57 is installed on the upper left. The uppermost crossbeam of the fuselage runs through the hardware module compartment 65. The left connector 72, right connector 73, and rear connector 74 are respectively connected to the locking blocks 32. The left connector 72 and right connector 73 are respectively routed inside the main support crossbeam on the lower side of the U-shaped main frame 27, and the rear connector 74 is routed inside the main support longitudinal beam on the upper side of the U-shaped main frame 27, converging at the hardware module compartment 65. The wiring is not exposed.

[0036] like Figure 7 As shown in b, the hardware module compartment 65 comprises a navigation and data link module 66, a flight control module 67, a low-voltage battery pack 70, and a magnetic closure device 71, along with a left connector 72, a right connector 73, a rear connector 74, a GPS module 77, a CAN relay board 78, and an Ethernet relay module 79. The low-voltage battery pack 70 supplies power to each mechanism and can be removed and removed via the magnetic closure device 71. The flight control module 67 is used to stably control the flight of the single-person aircraft, and the navigation and data link module 66 provides flight status information to the flight control module 67. Three GPS positioning antennas are arranged at the three equal divisions of the rear duct, serving as backups for each other, and are used for differential positioning.

[0037] like Figure 8 As shown, the quick-release connector consists of an integrated male connector 23 connected to the cantilever end 38 of the ducted power unit and an integrated female connector 33 connected to the U-shaped main body frame 27. The integrated male connector 23 is designed with a limiting pin, and the integrated female connector 33 is designed with a limiting groove for precise insertion and removal. The upper side is pressed by a locking block 32.

[0038] Example

[0039] In one embodiment, the aircraft features an optimized aerodynamic layout. The power system consists of a left ducted power unit 1, a right ducted power unit 2, and a rear ducted power unit 3, arranged in a triangular configuration, employing a three-duct aerodynamic layout. The left and right ducted power units 1 and 2 are located at the same height on both sides of the fuselage structure, while the rear ducted power unit 3 is installed at a higher height relative to the front ducted unit. This reduces airflow interference between the crew and the front ducted unit on the rear ducted unit during forward flight, improving forward flight efficiency and stability. The fuselage structure 4 includes the fuselage frame and landing gear, with a U-shaped structure. Personnel are positioned inside the U-shaped structure in a standing posture and secured to the aircraft via a wearable structure 5. The safety and rescue mechanism 6 includes the wearable structure 5 and a parachute assembly 57, located above the avionics system 7, used to ensure personnel safety in emergency situations.

[0040] In one embodiment, the ducted power units of the three-duct single-person vertical takeoff and landing aircraft are located on the left and right sides of the wearable fuselage, respectively. Below each unit are aerodynamic control surfaces 10 driven by an upper crossbeam 8 and a servo motor 9. These control surfaces include ducts 11, blades 12, tail cones 13, main beams 14, motors 15, motor mounts 16, upper hubs 17 and lower hubs 18, rectifier arms 19, an onboard omnidirectional antenna 20, main beam connectors 21, heat dissipation fins 22, integrated male connectors 23, hinges 24, electronic speed controllers 25, and a GPS positioning antenna 26. The three-duct aircraft adjusts the power of each duct... The rotational speed of the blades 12 and the deflection angle of the aerodynamic control surfaces 10 allow the aircraft to balance the anti-torque and directional control of the rear ducted rotor. The aerodynamic control surfaces 10 provide the directional control force required for maneuvering flight. The duct 11 and blades 12 provide the thrust required for flight. The tail cone 13 carries the electronic speed controller 25 and the motor 15. The main beam 14 is fixed to the inside of the duct 11 via the main beam connector 21. The airborne omnidirectional antenna 20 is used to transmit and receive data to and from the ground station. The heat dissipation fins 22 dissipate the heat generated by the various systems of the aircraft by increasing the surface area. The GPS positioning antenna 26 is used for the aircraft's navigation and positioning.

[0041] In one embodiment, the fuselage structure 4 is mainly composed of a U-shaped main frame 27, fuselage landing gear 28, shock absorber ball 29, diagonal brace 30, battery base 31, locking block 32, integrated female connector 33, battery positioning locking block 34, landing gear adapter 35, back plate adapter 36, hand control joystick 37, ducted power unit cantilever 38, etc. The U-shaped main frame 27 achieves quick assembly and disassembly with the ducted power unit via an integrated male connector 23, an integrated female connector 33, and a sliding groove structure 75. Simultaneously, locking blocks 32 press against the ducted power unit cantilever 38 to ensure the strength of the cantilever end. Diagonal braces 30 ensure a safe range of motion for personnel's arms and can be freely installed and removed. The fuselage landing gear 28, located at the rear of the fuselage, provides stable support for the aircraft when parked on the ground. Shock-absorbing balls 29 buffer impacts, protect the structure, and improve stability and comfort during landing and ground operations, ensuring flight safety and passenger comfort upon landing. Landing gear adapters 35 connect and fix the fuselage landing gear 28 and the U-shaped main frame 27 with screws. Backplate adapters 36 connect the backplate and the main load-bearing beam of the U-shaped main frame 27. Handheld control sticks 37 control the aircraft's attitude, heading, and thrust, ensuring flight safety and precise operation.

[0042] In one embodiment, the wearable structure 5 mainly consists of a detachable back panel 39, shoulder straps 40, chest straps 41, waist fixing straps 42, and leg fixing straps 43. The human body is fixed to the detachable back panel 39 by the shoulder straps and leg fixing straps. The detachable back panel 39 is connected to the back panel adapter 36 of the body structure 4 via a separation mechanism 44. The separation mechanism 44 mainly consists of a distributed four-pin mechanism 45 and an unlocking mechanism 46. The unlocking mechanism 46 consists of a steel wire rope 47 and a plastic tube 48. The pin mechanism 45 is moved by the steel wire rope 47, and the steel wire rope 47 is fixed in position and direction within the plastic tube 48. The four ropes converge on the fixing mechanism 49. The fixing mechanism 49 consists of a locking tongue 50, a locking seat 51, and a cover plate 52. The locking tongue 50 is fixed with a rope 53 consisting of four pins. The locking tongue 50 rotates around the rotation axis of the locking seat 51, synchronously pulling the rope 53. The cover plate 52 is used to fix four plastic tubes 48. The unlocking mechanism 46 has two hanging ear structures 54 on each side of the internal groove. The hanging ear structures 54 are connected to the mechanism 45 by two miniature springs 55. When the connector is inserted into the lock in the correct position, the pins are engaged in the connector groove, forming an automatic reset mechanism. When the separation mechanism 44 receives a command, the energy storage spring 56 between the separation mechanism 44 and the unlocking mechanism 46 causes the back plate adapter 36 to pop out, preventing the lock from jamming.

[0043] In one embodiment, the safety and rescue mechanism 6 includes a parachute assembly 57 and a parachute-human connection device 58. The parachute assembly 57 and the parachute-human connection device 58 are installed on the upper end face of the avionics system 7. When the safety and rescue system needs to be activated, the controller first issues a command, and then the explosive bolt 60 in the parachute assembly 57 throws off the parachute compartment cover 61. Then the parachute rocket 62 is launched, and the separation mechanism 44 and the back panel adapter 36 are unlocked to achieve separation of the human and the machine. The parachute rocket 62 pulls out the pin of the fixing strap of the main parachute 63 and pulls the main parachute 63 out of the parachute compartment. After all the components are straightened, the parachute rocket 62 is separated from the main parachute 63 by tearing the tear strip. The main parachute 63 is inflated by the airflow and fully opens, carrying the occupants to a stable descent until landing.

[0044] In one embodiment, the avionics system 7 includes a high-voltage battery pack 64 and a hardware module compartment 65. The high-voltage battery pack 64 is mounted on two directional rails on the battery base 31 of the lower support rod at the rear of the U-shaped main frame 27, and is fixed to the rear of the fuselage by bolts and battery positioning locking blocks 34, forming a "backpack-style" battery. The hardware module compartment 65 mainly consists of a flight control module 65, a navigation and data link module 66, a GPS positioning antenna 67, an airborne omnidirectional antenna 69, a low-voltage battery pack 70, a magnetic closure device 71, a left connector 72, a right connector 73, and a rear connector 74, etc. The low-voltage battery pack 70 is used for various... The subsystem is powered and can be removed and removed via a magnetic closure device 71. An internal guide channel is provided to prevent water accumulation. The flight control module 65 is used to stabilize the flight of the single-person aircraft. The navigation module 66 is used to provide flight status information to the flight control module. Three GPS positioning antennas 67 are arranged at the three equal divisions of the rear duct, serving as backups for each other and used for differential positioning. The blade antenna is used to communicate with the ground control station. The left connector 72 and the right connector 73 are respectively routed inside the main crossbeam under the U-shaped main frame 27, and the rear connector 74 is routed inside the main longitudinal beam on the U-shaped main frame 27. All wiring converges in the hardware module compartment 65, and the wiring is not exposed.

[0045] This single-person aircraft features high flexibility, a high safety redundancy factor, and high safety, utilizing ducted propulsion to protect personnel. This version of the aircraft is compact, agile, and fast, unrestricted by terrain. It also frees the operator's hands, enabling hands-free high-altitude operations in autopilot mode. Intelligent interactive control, combined with an AR helmet and joystick operation, allows for intelligent interaction. It fills a gap in the technology and market for ducted vertical takeoff and landing (VTOL) aircraft.

[0046] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0047] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An open-type single-person aircraft structure, characterized in that, It includes a left ducted power unit (1), a right ducted power unit (2), a rear ducted power unit (3), an airframe structure (4), a wearable structure (5), a safety and rescue mechanism (6), and an avionics mechanism (7); the left ducted power unit (1), the right ducted power unit (2), and the rear ducted power unit (3) adopt a three-ducted aerodynamic layout structure and are arranged in a triangular shape; the airframe structure (4) is located at the center of the three-ducted aerodynamic layout structure; the wearable structure (5) is fixedly connected to one side of the airframe structure (4), and the avionics mechanism (7) is fixedly connected to the other side; the safety and rescue mechanism (6) is located above the avionics mechanism (7).

2. The open-type single-person aircraft structure according to claim 1, characterized in that, The left duct power unit (1) and the right duct power unit (2) are located at the same height on both sides of the body structure (4), and the rear duct power unit (3) is higher than the left duct power unit (1) and the right duct power unit (2).

3. The open-type single-person aircraft structure according to claim 1, characterized in that, The left duct power unit (1), right duct power unit (2), and rear duct power unit (3) all use the same power system; the power system includes a duct (11), blades (12), tail cone (13), main beam (14), and motor (15); the blades (12) are arranged in a circular array at the center of the duct (11) and are fixed by bolts to the upper hub (17) and lower hub (18); the head of the main beam (14) is installed on the inner wall of the duct (11) through the main beam connector (21), and the end of the main beam (14) is... The part is bolted to the motor mount (16); the motor (15) is nested inside the motor mount (16); the rectifier arm (19) is distributed at a 90° angle to the main beam (14), and the end of the rectifier arm (19) is bolted to the motor mount (16); the airborne omnidirectional antenna (20) is located on the upper arc arm of the duct (11); the cone and the tail cone (13) are connected by rivets, and the heat dissipation fins (22) are arranged on the side of the cone; the tail cone (13) houses the motor (15), the electronic speed controller (25) and the GPS positioning antenna (26).

4. The open-type single-person aircraft structure according to claim 3, characterized in that, The left duct power unit (1) and the right duct power unit (2) are equipped with an upper crossbeam (8), a servo motor (9), and an aerodynamic control surface (10) driven by the servo motor (9) below the power system; the main beam (14) is provided with a spatial structure avoidance design for the upper crossbeam (8) and the aerodynamic control surface (10); the blade (12) is connected to the aerodynamic control surface (10) through four hinges (24), and the motor (15) adjusts the speed of the blade (12) and adjusts the deflection angle of the aerodynamic control surface (10).

5. The open-type single-person aircraft structure according to claim 1, characterized in that, The fuselage structure (4) includes a U-shaped main frame (27) and a fuselage landing gear (28); the U-shaped main frame (27) has a seat-backpack-style structure, including several U-shaped main load-bearing crossbeams and secondary crossbeams distributed in parallel on the xy plane, a U-shaped main load-bearing longitudinal beam on the yz plane, and several relatively perpendicularly distributed load-bearing secondary longitudinal beams. The beams are thin-walled circular tube structures, integrally formed by welding; the U-shaped main frame (27) is provided with diagonal bracing rods (30) on both sides; the crossbeams Welded at the intersection with the longitudinal beam to form a closed-loop force-bearing structure; a battery base (31) is installed at the bottom of a U-shaped main load-bearing longitudinal beam, and the battery base (31) is provided with two straight sliding grooves and a limiting slot; the back plate adapter (36) is installed at the intersection of the upper secondary crossbeam and the middle main load-bearing crossbeam, in a symmetrical shape, and is locked by positioning screws; the battery positioning locking block (34) is installed on the two secondary longitudinal beams, adjacent to the upper secondary crossbeam; the extended end of the U-shaped main frame (27) is welded with a sliding groove structure (75). Built-in integrated female connector (33); ducted power unit cantilever (38) externally connected to integrated male connector (23), the integrated female connector (33) and integrated male connector (23) achieve quick assembly and disassembly of U-shaped main frame (27) and ducted power unit through mating; locking block (32) is set on the outside of U-shaped main frame (27), locking block (32) presses the ducted power unit cantilever (38); hand-held control lever (37) is located on U The main frame (27) is located on the left front end; the lower U-shaped main load-bearing beam is fully welded with 16 nuts, and the fuselage landing gear (28) is located below the lower U-shaped main load-bearing beam; the fuselage landing gear (28) consists of three "Y"-shaped tubular components, two of which are fixed by a three-way structural component, and the fuselage landing gear (28) is connected to the lower main load-bearing beam of the U-shaped main frame (27) through a landing gear adapter (35); shock-absorbing balls (29) are set at the bottom of the fuselage landing gear (28).

6. The open-type single-person aircraft structure according to claim 1, characterized in that, The wearable structure (5) includes a detachable back panel (39), shoulder straps (40), chest straps (41), waist fixing straps (42), and leg fixing straps (43); the shoulder straps (40), chest straps (41), waist fixing straps (42), and leg fixing straps (43) are mounted on the detachable back panel (39), and the human body is fixed to the detachable back panel (39) by the straps and straps; the detachable back panel (39) is connected to the back panel adapter (36) of the body structure (4) through a separation mechanism (44); the separation mechanism (44) includes a distributed four-position latch mechanism (45) and an unlocking mechanism (46), the unlocking mechanism (46) is composed of a steel wire rope (47) and a plastic tube (48); the latch mechanism (45) is connected to the body structure (4) through a four-position latch mechanism (45) and an unlocking mechanism (46), the unlocking mechanism (46) is composed of a steel wire rope (47) and a plastic tube (48); the latch mechanism (45) is connected to the body structure (4) through a four-position latch mechanism (45) and an unlocking mechanism (46). The steel wire rope (47) is pulled and moved, and the steel wire rope (47) is fixed in position and direction inside the plastic tube (48). The four ropes converge on the fixing mechanism (49). The fixing mechanism (49) consists of a locking tongue (50), a locking seat (51) and a cover plate (52). The locking tongue (50) is fixed with the rope (53) of the four pins. The locking tongue (50) can rotate around the rotation axis of the locking seat (51) and pull the rope (53) to move synchronously. The cover plate (52) is used to fix the four plastic tubes (48). The unlocking mechanism (46) has two hanging ear structures (54) on each side of the groove inside. The hanging ear structure (54) is connected to the pin mechanism (45) through two miniature springs (55). An energy storage spring (56) is provided between the separation mechanism (44) and the unlocking mechanism (46).

7. The open-type single-person aircraft structure according to claim 1, characterized in that, The safety and rescue mechanism (6) includes a parachute assembly (57) and a parachute connection device (58); the parachute assembly (57) and the parachute connection device (58) are installed on the upper end face of the avionics mechanism (7); the parachute assembly (57) consists of an explosive bolt (60), a canopy cover (61), a parachute rocket (62), a fixed main parachute (63), and a tear strip; the explosive bolt (60) is located on the outside of the canopy cover (61), the parachute rocket (62) is located at the lower end of the canopy cover, close to the canopy cover (61), the fixed main parachute (63) is connected to the parachute rocket (62), and is compressed in the parachute assembly (57) through the tear strip; the launch of the parachute rocket (62) drives the fixed main parachute (63) to open the tear strip and open the parachute.

8. The open-type single-person aircraft structure according to claim 1, characterized in that, The avionics system (7) includes a high-voltage battery pack (64) and a hardware module compartment (65); the high-voltage battery pack (64) is installed on two directional slide rails on the battery base (31) of the lower support rod on the rear side of the U-shaped main frame (27) of the fuselage structure (4), and is fixed to the rear side of the fuselage by bolts and battery positioning locking blocks (34) to form a "backpack" battery. The high-voltage battery pack (64) is charged by three high-voltage charging modules (80); the hardware module compartment (65) is located on the high-voltage battery pack (64). Above, on the upper left, is a parachute assembly (57), and the uppermost crossbeam of the fuselage runs through the hardware module compartment (65); the left connector (72), right connector (73), and rear connector (74) are respectively connected to the locking block 32; the left connector (72) and right connector (73) are respectively routed inside the main load-bearing crossbeam on the lower side of the U-shaped main frame (27), and the rear connector (74) is routed inside the main load-bearing longitudinal beam on the upper side of the U-shaped main frame (27), converging in the hardware module compartment (65), and the lines are not exposed.

9. The open-type single-person aircraft structure according to claim 5, characterized in that, The quick-release connector consists of an integrated male connector (23) connected to the cantilever end (38) of the ducted power unit and an integrated female connector (33) connected to the U-shaped main body frame (27). The integrated male connector (23) is designed with a limiting pin and the integrated female connector (33) is designed with a limiting groove for precise insertion and removal. The upper side is pressed by a locking block (32).

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