A manned aircraft

Abstract

The utility model discloses a manned aircraft belongs to aircraft technical field, contains frame, frame is equipped with human body fixing device and at least two turbofan subassembly, human body fixing device is used for fixing human body on frame, and turbofan subassembly is through turbofan tilting axle and can be connected in tilting axle, and rotating axle is connected in frame, and frame is through rotating motor drive turbofan tilting axle and rotates with tilting axle as the axle, and turbofan subassembly drives its with turbofan tilting axle as the axle and tilts through tilting motor. The utility model discloses the mode of rotatable and tiltable wheel rim fan cooperation telescopic aileron drive, improves the utilization efficiency of energy and the space efficiency of flight. The driving force of wheel rim fan is in the peripheral wheel rim, and the traditional middle motor drive mode is cancelled. Because there is no airflow and wake flow distortion of middle drive motor, therefore the smooth continuous flow passage of whole duct can improve the thrust, eliminate an important noise source, and reduce the noise of whole fan.

Description

Technical Field

[0001] This utility model relates to a manned aircraft and belongs to the field of low-altitude aircraft technology. Background Technology

[0002] Manned aircraft have broad application prospects, and various forms of manned aircraft exist in existing technologies. For example, patents with numbers "202410420041X" and "2025100776701" both describe flight backpacks that use jet engines to provide lift. However, this method has several drawbacks. First, jet engines use fuel as propulsion, which requires consideration of fuel tank storage, safety, and environmental issues.

[0003] Although patent number "2023106989308" describes a drive system using an electrically driven turbofan, like the two existing patents mentioned above, it relies solely on thrusters to provide lift and thrust for horizontal flight. This drive method is energy-intensive and not conducive to long-distance flight. Furthermore, the human restraint device (waist belt 32 and back strap 31) in this patent (2023106989308) is not securely fastened to the operator in actual use, resulting in poor comfort and safety. Additionally, the operating system is controlled by both hands, failing to free the operator's hands. Utility Model Content

[0004] To address the shortcomings of existing technologies, the purpose of this utility model is to provide a manned aircraft that solves the technical problems of existing manned aircraft relying entirely on propulsion for flight and the inconvenience of operation and storage.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: A manned aircraft includes a frame, the frame being provided with a human body restraint device and at least two turbofan assemblies, the human body restraint device being used to secure a human body to the frame; The turbofan assembly is rotatably connected to the rotating shaft via a turbofan tilting shaft. The rotating shaft is connected to the frame, and the frame drives the turbofan tilting shaft to rotate around the rotating shaft via a rotary motor. The turbofan assembly is driven to tilt around the turbofan tilting shaft via a tilting motor.

[0006] To facilitate locking of the wing assembly, the frame is also equipped with a slot with a locking tongue. When the turbofan assembly is deployed to a preset angle relative to the frame, the locking tongue engages the turbofan tilt shaft in the slot.

[0007] Preferably, in the aforementioned manned aircraft, the turbofan assembly includes a turbofan frame and a turbofan unit mounted on the turbofan frame. The turbofan frame is fixedly connected to the turbofan tilt axis. The turbofan unit includes a turbofan body and a stator disposed on the outer edge of the turbofan body. The turbofan body includes blades and a turbofan outer ring disposed on the outer edge of the blades. The turbofan outer ring is provided with a permanent magnet. The stator includes a magnet and a coil wound around the magnet.

[0008] Specifically, the magnet is fixedly installed on the turbofan frame, and the outer ring of the turbofan is rotatably installed on the turbofan frame via bearings. The ends of the turbofan frame are provided with bearing fixing slots and magnet fixing slots in sequence, which mate with the bearings and magnets, respectively. There are multiple turbofan units. When there are two turbofan units, the two turbofan units are installed on opposite sides of the turbofan frame. When there are more than two turbofan units, the turbofan units and the turbofan frame are stacked sequentially.

[0009] Ideally, the rotation axis should be perpendicular to the plane of the frame, and the turbofan tilt axis should be parallel to the plane of the frame.

[0010] Preferably, the human body fixation device includes a seat cushion and two human body fixation frames that can be opened apart. A locking device is provided between the human body fixation frames and the frame, and the two human body fixation frames are locked together by a sliding sleeve.

[0011] To enhance safety, the human restraint frame is equipped with airbags; the frame is also equipped with parachutes.

[0012] To improve range, this embodiment also includes a wing assembly mounted on the frame. The wing assembly includes at least two retractable and cooperating first and second wings, which are connected by a guide structure.

[0013] Preferably, the aforementioned manned aircraft further includes a foot pedal telescopic rod that can extend and retract relative to the frame, the lower end of which is provided with a foot pedal that can be rotated, and the foot pedal is provided with an aircraft control device.

[0014] Preferably, in the aforementioned manned aircraft, the bottom of the foot pedal is provided with a ground support structure. When the foot pedal is rotated to a certain angle relative to the foot pedal telescopic rod, the manned aircraft can stand on the ground with the bottom of the foot pedal as the support plane.

[0015] The beneficial effects achieved by this utility model are: Compared to existing technologies, this invention has the following advantages: First, this invention uses a rotatable and tiltable rim fan in conjunction with a retractable wing for drive, improving energy utilization efficiency and flight space efficiency. The rim fan in this invention is driven by the outer rim, eliminating the traditional center-mounted motor drive. Because there is no center-mounted motor to obstruct airflow and cause wake distortion, the smooth and continuous flow path inside the entire duct enhances thrust. Eliminating the central motor removes a significant noise source, reducing overall fan noise. By replacing the center-mounted motor with rim drive, the structure is simplified and compact, resulting in a shorter axial length of the entire fan system, reduced weight, and higher power density. With the rim drive on the outer edge, the stator coils and rotor permanent magnets are far from the center of rotation, resulting in lower moment of inertia, faster acceleration or deceleration, lower energy consumption during speed changes, and more rapid response to speed changes.

[0016] The turbofan blades of this invention form an integral bladed disk, thus greatly reducing the probability of blade-related injuries or blade damage. There are four turbofan assemblies located at the four corners of the fuselage, containing at least eight individual turbofan units. These coaxial, adjacent turbofans rotate in opposite directions, counteracting torque and allowing for real-time adjustment of the fuselage attitude, resulting in highly agile flight.

[0017] Secondly, the wings of this invention feature a telescopic design, the turbofan can be retracted relative to the frame, the seat cushion has a folding design, and the footrests can be retracted upwards using a telescopic lever, greatly improving the portability of the entire aircraft and making it highly conducive to miniaturization and weight reduction. When not in use, the footrests can serve as the entire base for easy storage.

[0018] This invention incorporates both airbag and parachute designs, which enhances safety to a certain extent. The overall operation can be controlled by the feet and helmet, freeing up the hands. Attached Figure Description

[0019] Figure 1 This is a front view of the overall structure of this utility model; Figure 2 This is a front view of the turbofan assembly and wing assembly of this utility model in their stowed state; Figure 3 This is an overall structural diagram of the back of this utility model; Figure 4 This is a rear structural diagram of the turbofan assembly and wing assembly of this utility model in their stowed state; Figure 5 This is a structural diagram of the turbofan assembly of this utility model; Figure 6 This is a cross-sectional view of the turbofan assembly of this utility model; Figure 7 This is an exploded view of the turbofan assembly of this utility model; Figure 8 This is a cross-sectional view of the human body fixation frame and locking device in the locked state. Figure 9 This is a cross-sectional view of the human body fixation frame and locking device of this utility model in a separated state; Figure 10 This is a partial enlarged view of the guide structure of this utility model; Figure 11 This is a diagram showing the changes in the flight state of this utility model; Figure 12 This is a diagram illustrating the emergency stop or reverse flight state of this utility model. Figure 13 This is a diagram illustrating the turning state during flight of this utility model; The meanings of the reference numerals in the diagram are as follows: 1-Frame; 2-Turbofan assembly; 3-Wing assembly; 4-Human restraint frame; 5-Locking device; 6-Parachute; 7-Foot pedals; 8-Seat cushion; 11-Armrest; 12-Foot pedal telescopic bar; 21-Rotation shaft; 21a-Rotation motor; 22-Tilting motor; 23-Turbofan tilting shaft; 24-Slot; 241-Lock tongue; 25-Turbofan frame; 251-Outer step; 252-Inner step; 26-Turbofan unit; 261-Air inlet grille. ; 262-Turbofan body; 2621-Blade; 2622-Turbofan outer ring; 263-Bearing; 264-Magnet; 265-Permanent magnet; 301-Slide groove; 302-Slide rod; 31-First wing; 32-Second wing; 51-Locking pin; 52-Spring; 53-Lock tongue seat; 511-Sloping surface; 401-Locking hole; 41-Hinge; 42-Sliding sleeve; 43-Elastic pin; 44-Airbag; 251-Bearing fixing groove; 252-Magnet fixing groove. Detailed Implementation

[0020] The present invention will be further described below with reference to the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present invention, and should not be used to limit the scope of protection of the present invention.

[0021] like Figures 1 to 7 As shown: This embodiment discloses a manned aircraft, comprising a frame 1. The frame 1 is equipped with a human restraint device 4 and at least two turbofan assemblies 2. The human restraint device is used to secure a human body to the frame 1. The turbofan assemblies 2 are used to provide flight power to the frame 1.

[0022] In this embodiment, the turbofan assembly 2 is tiltably connected to the rotating shaft 21 via a turbofan tilting shaft 23. The rotating shaft 21 is connected to the frame 1, and the frame 1 is driven by a rotary motor 21a to rotate and oscillate around the rotating shaft 21. The turbofan assembly 2 is driven by a tilting motor 22 to rotate around the turbofan tilting shaft 23. For ease of description, the plane where the frame 1 is located is marked as the XY plane in this embodiment. Therefore, the axis of the rotating shaft 21 is preferably parallel to the Z-axis, and the turbofan tilting shaft 23 is preferably perpendicular to the rotating shaft 21. It should be noted that in practical applications, the rotary motor 21a and the rotating shaft 21, and the tilting motor 22 and the turbofan tilting shaft 23 can be configured with a speed-changing mechanism or a transmission direction adjustment mechanism according to actual conditions such as torque, speed, and spatial arrangement. The above configuration methods are all conventional means for those skilled in the art and are also within the protection scope of this patent. The tilting motor 22 or the turbofan tilting shaft 23 is preferably equipped with a brake or holding brake device to lock the tilting angle of the turbofan assembly 2 at a fixed position.

[0023] As can be seen from the above description, the movement mode of the turbofan assembly 2 in this embodiment is as follows: Motion Method 1: Driven by the rotary motor 21a, the turbofan assembly 2 oscillates around the rotation axis 21 in the XY plane (where the frame 1 is located). This motion method can be used to achieve the storage of the turbofan assembly 2 relative to the frame 1. Figure 2 and Figure 4 (Status) or Expand Figure 1 and Figure 3 state).

[0024] Motion Method 2: Under the action of the tilting motor 22, the turbofan assembly 2 can rotate around the turbofan tilting shaft 23 by a certain angle. This motion method can be used to realize the tilting of the turbofan assembly 2 relative to the frame 1, thereby realizing the control of the pushing direction / angle of the frame 1. This motion method is also referred to as the tilting of the turbofan assembly 2.

[0025] In practical applications, when the turbofan assembly 2 is retracted relative to the frame 1 via the aforementioned movement method 1, the turbofan assembly 2 generates thrust. In this state, the thrust of the turbofan assembly 2 generates a bending moment on the turbofan tilt shaft 23 and a rotational torque on the rotary motor 21a. To facilitate the reliable fixing of the turbofan assembly 2 relative to the frame 1 at a certain angle, this embodiment also provides a slot 24 on the frame 1. One side of the slot 24 has a fixed baffle, and the other side has a retractable locking tongue 241. When the turbofan assembly 2 is extended relative to the frame 1 to a preset angle, the locking tongue 241 engages the turbofan tilt shaft 23 in the slot 24, thereby restricting the turbofan tilt shaft 23. In this way, during the flight of the aircraft, the rotary motor 21a does not need to continuously apply torque to the rotating shaft 21, improving the reliability of the connection between the turbofan assembly 2 and the frame 1, the load, and the overall safety of the aircraft.

[0026] Specifically, in combination Figure 6 and Figure 7 In this embodiment, the turbofan assembly 2 includes a turbofan frame 25 and a turbofan unit 26 mounted on the turbofan frame 25. The turbofan frame 25 is fixedly connected to the turbofan tilting shaft 23. The turbofan unit 26 includes a turbofan body 262 and a stator disposed on the outer edge of the turbofan body 262. The turbofan body 262 includes blades 2621 and a turbofan outer ring 2622 disposed on the outer edge of the blades 2621. Preferably, the blades 2621 and the turbofan outer ring 2622 are designed as a single unit, and the centers of all blades 2621 are fixed together by a central shaft with a relatively small diameter, which indicates the integrity and strength of the entire turbofan body 262.

[0027] The outer ring 2622 of the turbofan engine has a ring of multiple permanent magnets 265, which are fixedly attached to the outer edge of the outer ring 2622 and preferably in an embedded design. The stator includes magnets 264 and coils wound around the magnets 262, with the coils being powered. The magnets 264 are fixedly mounted to the turbofan frame 25, and the outer ring 2622 is rotatably mounted to the turbofan frame 25 via bearings 263. That is, the outer ring 2622 is fixed to the inner ring of the bearing 263, and the outer ring of the bearing 263 is fixedly mounted inside the turbofan frame 25. The bearings 263 provide fixed and rotatable support for the stator and rotor.

[0028] Specifically, the ends of the turbofan frame 25 are sequentially provided with bearing fixing grooves 251 and magnet fixing grooves 252, which respectively mate with bearings 263 and magnets 262. There can be multiple turbofan units 26. When there are two turbofan units 26, they are installed on opposite sides of the turbofan frame 25; when there are more than two turbofan units 26, they are stacked sequentially with the turbofan frame 25. During actual assembly, corresponding through holes can be made at the magnet fixing grooves 252 and magnets 262 on the turbofan frame 25, and all turbofan frames 25 and turbofan units 26 can be fixed by passing the same bolt through these through holes.

[0029] In this embodiment, a turbofan assembly 2 preferably has only two turbofan units 26, which are respectively installed on both sides of the turbofan frame 25. During operation, the two turbofan bodies 262 on both sides of the same turbofan frame 25 rotate in opposite directions. This can counteract the rotational torque of the turbofan bodies 262 and also increase thrust. As a preferred embodiment, the outer edge center of the turbofan frame 25 is fixedly connected to the turbofan tilting shaft 23, that is, the extended axis of the turbofan tilting shaft 23 passes through the center of the turbofan frame 25. In this way, when the entire turbofan assembly 2 generates thrust, it will not generate additional rotational torque on the turbofan tilting shaft 23, but only bending moment. An air inlet screen 261 can be provided at the air inlet of the entire turbofan assembly 2, that is, at the air inlet of the uppermost turbofan unit 26. The outer edge of the air inlet screen 261 has an outwardly extending flange structure to form an air inlet guide structure and increase the air intake.

[0030] The human body restraint device in this embodiment includes a seat cushion 8 and two openable human body restraint frames 4. The seat cushion 8 is hinged to the frame 1 and adopts an upward flipping design relative to the frame 1 for easy folding and storage.

[0031] One side of the human body immobilizer 4 is connected to the frame 1 via a hinge 41, and the two human body immobilizers 4 are locked together by a sliding sleeve 42. The sliding sleeve 42 can slide relative to one of the human body immobilizers 4 and lock onto the other human body immobilizer 4, thereby locking the two human body immobilizers 4 together. For example, a locking hole can be provided on the sliding sleeve 42, through which it locks onto the human body immobilizer 4. Furthermore, the human body immobilizer 4 also needs to be locked to the frame 1, which is achieved by a locking device 5 fixed to the frame 1. Figure 8 and Figure 9As shown: The locking device 5 includes a latch seat 53, which drives the locking pin 51 to extend in the locking direction via a spring 52. The end of the human body fixation frame 4 has a lock hole 401, and the end of the locking pin 51 has an inclined surface 511 facing the human body fixation frame 4. When the human body fixation frame 4 is inserted into the latch seat 53, the front end of the human body fixation frame 4 cooperates with the inclined surface 511, opening the locking pin 51. Then, under the action of the spring 52, it is reinserted into the lock hole 401, achieving quick locking. When unlocking is required, simply pull the locking pin 51 upwards.

[0032] Considering passenger safety, this embodiment also includes the following safety devices. First, an airbag 44 is provided at the front of the human restraint frame 4 (at the user's chest position). The human restraint frame 4 can be provided with a cavity to accommodate the airbag 44 at the user's chest position. The airbag 44 is triggered when a signal is detected. Second, the frame 1 is also provided with a parachute 6, which can be deployed in the event of a fall. The triggering and deployment methods of the airbag 44 and parachute 6 can be calibrated differently as needed, and this embodiment does not limit them. In addition, two handrails 11 can be provided at the front of the frame 1. The handrails 11 can be equipped with portable devices such as storage boxes and hooks as needed.

[0033] In this embodiment, the frame 1 is preferably driven by four arrayed turbofan assemblies 2. As mentioned in the background art of this utility model, if the entire flight process relies on the turbofan assemblies 2 in this embodiment to provide lift and thrust for horizontal flight, it will not be suitable for long-distance flight, especially in the horizontal flight phase. If the weight of the entire aircraft is offset by the wings, it is of great significance for improving the endurance. Therefore, this embodiment also includes wing assemblies 3 installed on the frame 1. In this embodiment, the wing assembly 3 adopts a multi-section telescopic design, specifically at least two telescopic cooperating first wings 31 and second wings 32. The first wings 31 and second wings 32 are connected by a guide structure, and the second wings 32 are located outside the first wings 31. Figure 10 As shown, the guide structure in this embodiment includes a groove 301 and a cooperating slide rod 302. For example, an inwardly extending groove 301 is provided on the first wing 31, and a cooperating slide rod 302 is provided on the second wing 32. When using a wing with more sections, the wing can be guided by setting multiple superimposed guide structures. The guide structure, compared to a structure with a reinforcing rib on the wing assembly 3, can improve the bending strength of the wing. In this embodiment, the telescopic drive method between the multiple wing sections can adopt the lead screw structure in the prior art, which will not be described in detail in this embodiment.

[0034] The turbofan assembly 2, also known as a ducted fan, eliminates the airflow obstruction and wake distortion caused by a centrally located drive motor. This results in a smooth, continuous flow path within the duct, enhancing thrust. Eliminating the central motor removes a significant noise source, reducing overall fan noise. By replacing the central motor with rim drive, the axial length of the entire fan system is shortened, weight is reduced, and power density is increased. With the rim drive located on the outer edge, the stator coils and rotor permanent magnets are further from the center of rotation, resulting in lower moment of inertia, faster acceleration and deceleration, lower energy consumption during speed changes, and more rapid response to speed variations.

[0035] The turbofan blades form a single bladed disk, thus greatly reducing the probability of blade-related injuries or blade damage. The four turbofan assemblies 2 located at the four corners of the fuselage contain at least eight individual turbofan units, with adjacent coaxial turbofans rotating in opposite directions. This counteracts torque and allows for real-time adjustment of the fuselage attitude, resulting in highly agile flight.

[0036] As described in the background of this patent, the hand-operated mechanism of the aircraft cannot free the hands. This embodiment also includes a foot pedal telescopic rod 12 that can extend and retract relative to the frame 1. The lower end of the foot pedal telescopic rod 12 is provided with a foot pedal 7 that can be rotated (the rotation axis is the X-axis). The foot pedal 7 is provided with an aircraft control device. The bottom of the foot pedal 7 is provided with a ground support structure, such as a support foot. When the foot pedal 7 is rotated to a certain angle relative to the foot pedal telescopic rod 12, the manned aircraft can stand on the ground with the bottom of the foot pedal 7 as a support plane.

[0037] When in use, open the seat cushion 8 outwards, open the human body fixing frame 4, adjust the foot pedal 7 to a suitable position using the foot pedal telescopic rod 12, and the operator sits on the seat cushion 8. The operator is locked to the frame 1 by the locking device 5 and the sliding sleeve 42. Then, unfold the turbofan assembly 2 and open the wing assembly 3.

[0038] like Figure 11 As shown, Figure 11 The red arrows indicate the flight direction. With the turbofan assembly 2 locked (the turbofan tilt shaft 23 is inside the slot 24 and locked by the locking tongue 241), the turbofan assembly 2 is rotated to a horizontal position under the control of the tilt motor 22. Then, the turbofan assembly 2 activates, generating thrust to lift the entire aircraft upwards. Figure 11 (Figure a) When it is raised to a certain height, the turbofan assembly 2 rotates. Figure 11 As shown in Figure b), it generates horizontal thrust to fly forward, achieving crawling. At the same time, the entire frame 1 gradually tilts horizontally. During horizontal flight, the wing assembly 3 can generate lift to achieve horizontal cruise. Figure 11 (Figures c and d). Upon reaching the destination, turbofan assembly 2 tilts. Figure 11 (Image from the middle of the image) It landed slowly, and after landing, its wings retracted. Figure 11 (Figure f in the middle)

[0039] like Figure 12 and Figure 13 As shown, Figure 12 and Figure 13 The red arrow in the image indicates the flight direction. Figure 12 Arrow F in the diagram indicates the direction of the driving force of turbofan component 2. Figure 13 The arrow in the image indicates the direction of the aircraft's rotation.

[0040] During flight, because the turbofan assembly 2 can tilt relative to the frame, the four turbofan assemblies 2 can coordinate to perform some relatively flexible maneuvers, such as... Figure 12 As shown, Figure 12 All four turbofan components 2 generate a driving force in the direction of flight that is upward and backward, enabling emergency braking or reversing. When two of the turbofan components 2 generate an upward tilting force, such as... Figure 13 Arrow F in the diagram enables the aircraft to rotate, with the rotation direction as follows: Figure 13 Arrow Q in the diagram.

[0041] Compared to existing technologies, this invention has the following advantages: First, it employs a tiltable and rotatable turbofan combined with a retractable wing for propulsion, improving energy efficiency and flight range. The turbofan drive in this invention is located on the periphery, eliminating the traditional central shaft drive method, thus reducing noise. Because there is no central drive motor obstructing airflow, thrust can be increased under the same conditions. Due to the stator and other structures along the outer edge of the blades, the probability of blade-related injuries or blade damage is greatly reduced. The turbofan assemblies 2 located at the four corners can adjust the fuselage attitude at any time, making flight highly agile.

[0042] Secondly, the wings of this invention feature a telescopic design, the turbofan can be retracted relative to the frame 1, the seat 8 has a folding design, and the foot pedal telescopic rod 12 can retract the foot pedals 7 upwards, greatly improving the portability of the entire aircraft and making it very beneficial for miniaturization and weight reduction. When not in use, the foot pedals 7 can serve as the entire base for easy storage.

[0043] This utility model incorporates both an airbag 44 and a parachute 6, which enhances safety to a certain extent.

[0044] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present utility model, and these improvements and modifications should also be considered within the protection scope of the present utility model.

Claims

1. A manned aircraft, characterized in that, Includes a frame (1), the frame (1) is provided with a human body fixation device (4) and at least two turbofan assemblies (2), the human body fixation device is used to fix a human body to the frame (1); The turbofan assembly (2) is rotatably connected to the rotating shaft (21) via the turbofan tilting shaft (23). The rotating shaft (21) is connected to the frame (1), and the frame (1) drives the turbofan tilting shaft (23) to rotate around the rotating shaft (21) via a rotary motor (21a). The turbofan assembly (2) is driven to tilt around the turbofan tilting shaft (23) via a tilting motor (22).

2. A manned aircraft according to claim 1, characterized in that, The frame (1) is also provided with a slot (24), and the slot (24) is provided with a locking tongue (241). When the turbofan assembly (2) is unfolded to a preset angle relative to the frame (1), the locking tongue (241) engages the turbofan tilting shaft (23) in the slot (24).

3. A manned aircraft according to claim 2, characterized in that, The turbofan assembly (2) includes a turbofan frame (25) and a turbofan unit (26) mounted on the turbofan frame (25). The turbofan frame (25) is fixedly connected to the turbofan tilting shaft (23). The turbofan unit (26) includes a turbofan body (262) and a stator disposed on the outer edge of the turbofan body (262). The turbofan body (262) includes blades (2621) and a turbofan outer ring (2622) disposed on the outer edge of the blades (2621). The turbofan outer ring (2622) is provided with a permanent magnet (265). The stator includes a magnet (264) and a coil wound around the magnet (262).

4. A manned aircraft according to claim 3, characterized in that, The magnet (264) is fixedly installed on the turbofan frame (25), and the outer ring of the turbofan (2622) is rotatably installed on the turbofan frame (25) through the bearing (263).

5. A manned aircraft according to claim 4, characterized in that, The turbine frame (25) is provided with a bearing fixing groove (251) and a magnet fixing groove (252) in sequence at the end. The bearing fixing groove (251) and the magnet fixing groove (252) are respectively matched with the bearing (263) and the magnet (262). There are multiple turbofan units (26). When there are two turbofan units (26), the two turbofan units (26) are installed on both sides of the turbofan frame (25). When there are more than two turbofan units (26), the turbofan units (26) and the turbofan frame (25) are stacked in sequence.

6. A manned aircraft according to claim 1, characterized in that, The rotation axis (21) is perpendicular to the plane of the frame (1), and the turbofan tilt axis (23) is parallel to the plane of the frame (1).

7. A manned aircraft according to claim 1 or 6, characterized in that, The human body fixation device includes a seat cushion (8) and two human body fixation frames (4) that can be opened apart. A locking device (5) is provided between the human body fixation frame (4) and the frame (1). The two human body fixation frames (4) are locked together by a sliding sleeve (42). The human body fixation frame (4) is also equipped with an airbag (44); The frame (1) is also equipped with a parachute (6).

8. A manned aircraft according to any one of claims 1 to 5, characterized in that, It also includes a wing assembly (3) mounted on the frame (1), the wing assembly (3) including at least two retractable cooperating first wing (31) and second wing (32), the first wing (31) and second wing (32) being cooperated by a guide structure.

9. A manned aircraft according to any one of claims 1 to 5, characterized in that, It also includes a foot pedal telescopic rod (12) that can extend and retract relative to the frame (1), the lower end of which is provided with a foot pedal (7) that can be rotated, and the foot pedal (7) is provided with an aircraft control device.

10. A manned aircraft according to claim 9, characterized in that, The foot pedal (7) has a ground support structure at the bottom. When the foot pedal (7) rotates to a certain angle relative to the foot pedal telescopic rod (12), the manned aircraft can stand on the ground with the bottom of the foot pedal (7) as the support plane.

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