阅读说明：本技术 一种收展翼与悬挂复用的eVTOL飞车 (eVTOL flying vehicle with folding wings and suspension for reuse ) 是由 马铁华 焦斌 陈昌鑫 张艳兵 武耀艳 徐浩飞 冯伟琦 武志博 于 2021-09-30 设计创作，主要内容包括：本发明涉及空中交通技术领域,具体是一种收展翼与悬挂复用的eVTOL飞车。包括整流壳体、动力系统、机舱系统、收展翼系统以及前起落架系统。收展翼与悬挂复用兼顾了地面行驶与空中飞行,同时省去了作为车辆的悬挂机构降低了飞车飞行时的“死重”。机身整体倾转的垂直起降方式省去了倾转机翼垂直起降方式的倾转机构,降低了飞车飞行时的“死重”。大挠度机翼后缘吸气缝利用边界层吞吸技术有效优化大仰角起飞时流场,保证大仰角起飞时的大挠度机翼升力。(The invention relates to the technical field of air traffic, in particular to an eVTOL (electric virtual vehicle) aerodyne with folding wings and suspension for multiplexing. The aircraft comprises a fairing shell, a power system, a cabin system, a wing folding system and a nose landing gear system. The wing folding and unfolding and the suspension reuse take ground running and air flight into consideration, and meanwhile, a suspension mechanism used as a vehicle is omitted, so that the dead weight of the flying vehicle during flying is reduced. The vertical take-off and landing mode of the whole tilting body saves a tilting mechanism of the vertical take-off and landing mode of the tilting wings, and reduces dead weight during flying. The trailing edge suction slot of the large-deflection wing effectively optimizes the flow field during high-elevation takeoff by utilizing a boundary layer suction technique and ensures the lift force of the large-deflection wing during high-elevation takeoff.)

1. An eVTOL (extreme velocity orbit) aerodyne with folding wings and suspension multiplexing functions is characterized by comprising a rectifying shell (1), a power system (2), an engine room system (3), a folding wing system (4) and a nose landing gear system (5),

the cabin system (3) is positioned in a front shell of the rectifying shell (1), and driving equipment (301) and a seat (302) are arranged in the cabin system (3);

the power system (2) is positioned in a rear shell of the rectifying shell (1), the width and the height of the rear shell of the rectifying shell (1) are larger than those of a front shell of the rectifying shell (1), and openings allowing airflow to pass through the power system (2) are formed in the front end and the rear end of the rear shell of the rectifying shell (1);

the wing folding and unfolding system (4) comprises support parts (401) fixedly arranged on two sides below a front shell of the rectifying shell (1), each support part (401) is hinged with a large-deflection wing (402) capable of swinging back and forth along the horizontal direction, the free end of each large-deflection wing (402) is rotatably provided with a motor wheel (403), the motor wheels (403) can support the rear part of the rectifying shell (1), and the hubs of the motor wheels (403) are arranged in a propeller arrangement mode;

the nose landing gear system (5) comprises a rotating shaft (501) arranged inside the lower portion of a front shell of the rectifying shell (1), and a motor (503) arranged in the front shell of the rectifying shell (1), wherein the motor (503) controls the rotating angle of the rotating shaft (501), two ends of the rotating shaft (501) extend out of the front shell of the rectifying shell (1), two ends of the rotating shaft (501) located outside the front shell of the rectifying shell (1) are respectively provided with a large-deflection landing gear (502) extending forwards, the front end of the large-deflection landing gear (502) rotates to be provided with a brake wheel (506), and the brake wheel (506) can support the front portion of the rectifying shell (1).

2. The eVTOL (eVTOL) flying vehicle with the folding wings and the hanging wings reusable as claimed in claim 1, wherein the two sides of the upper edge of the rear end of the rear shell of the rectifying shell (1) are respectively provided with vertical rear fuselage wings (101), the upper parts of the vertical rear fuselage wings (101) at the two sides are closed, a horizontal rear fuselage wing (102) is arranged between the upper ends of the vertical rear fuselage wings (101) at the two sides, a splitter plate (103) is arranged between the middle part of the horizontal rear fuselage wing (102) and the lower edge of the rear end of the rear shell of the rectifying shell (1), ducts are formed between the splitter plate (103) and the horizontal rear fuselage wing (102) and between the adjacent vertical rear fuselage wings (101), and a duct fan (104) is arranged in each duct.

3. The eVTOL (eVTOL) flying vehicle with the folding wings and the hanging wings multiplexed function as claimed in claim 2, wherein the splitter plate (103) divides the rear opening of the rear shell of the rectifying shell (1) into two regions, a tail guide plate (105) of the aircraft body is arranged below the middle part of each region along the up-down direction, and the turning angle of all the tail guide plates (105) of the aircraft body can be adjusted.

4. An eVTOL aircraft with folding wings and suspension multiplexing according to claim 1, characterized in that the rotating shaft (501) is connected with the motor (503) through a worm gear mechanism (504).

5. An eVTOL flying vehicle for wing retraction and suspension reuse according to claim 4, characterized in that a buffer damper (505) is arranged between the motor (503) and the vehicle body.

6. The eVTOL (eVTOL) flying vehicle with the multiplexing of the folding wings and the hanging wings as claimed in claim 1, wherein the inside of the large-deflection wing (402) is provided with a hollow cavity, the wing tip of the large-deflection wing (402) is of a closed structure, the wing root of the large-deflection wing (402) is communicated with the inside of the rear shell of the rectifying shell (1), the wing root of the large-deflection wing (402) is hermetically connected with the rear shell of the rectifying shell (1), the front edge of the large-deflection wing (402) is of a closed structure, and an air suction gap (404) allowing air flow to enter is arranged above the rear edge of the large-deflection wing (402).

7. The eVTOL flying vehicle with the multiplexing of the folding wings and the hanging is characterized in that the middle upper part of the rear end of the front shell of the rectifying shell (1) is connected with the middle upper part of the inner edge of the front end of the rear shell of the rectifying shell (1) through at least three support rods (106), and the lower part of the rear end of the front shell of the rectifying shell (1) is closely connected with the lower part of the inner edge of the front end of the rear shell of the rectifying shell (1).

8. An eVTOL flying vehicle with both wings deployed and suspended according to claim 1, characterized by the gradually upward deployment of the high flexibility wings (402) from inside to outside.

9. An eVTOL aircraft with folding wing and suspension multiplexing according to claim 1, characterized in that the front shell of the fairing shell (1) is flush with the lower edge of the front shell of the fairing shell (1).

10. An eVTOL vehicle with folding wings and suspension multiplexing according to claim 1, characterized in that the upper surface of the rear shell of the fairing shell (1) is in a streamline arc shape gradually inclining downwards from front to back.

Technical Field

The invention relates to the technical field of air traffic, in particular to an eVTOL (electric virtual vehicle) aerodyne with folding wings and suspension for multiplexing.

Background

Under the global large background of carbon peak reaching and carbon neutralization, hydrogen energy is the first choice of future aircrafts, but hydrogen energy sources are insufficient, such as low power density of a hydrogen fuel cell, high requirement on hydrogen purity, and the proton membrane technology mastered in countries of Japan, America and the like; meanwhile, the energy efficiency of the hydrogen fuel engine is lower than that of the hydrogen fuel battery, and the weight of the generator is increased when the hydrogen fuel engine is used for converting electric energy.

The eVTOL has great significance for future traffic, but the main limiting factors for the design of the hydrogen energy eVTOL is that: (1) the vertical take-off and landing requires hydrogen power with higher power density; (2) the extra weight reduction requirements are that the 'dead weight' of the aircraft caused by the 'chassis' (suspension drive and the like) of the vehicle is reduced, and the 'dead weight' caused by a mechanism required by the mode conversion of vertical take-off and landing and flying patrol is reduced; (3) strict size limitations: the overall dimension of the aerocar is absolutely restricted by ground roads, parking lots and the like; (4) the structure is simple, and the flight control robustness is strong; (5) the noise is acceptable, and the low noise is suitable for ground traffic and UAM.

Disclosure of Invention

The invention provides an eVTOL (electric vehicle) flying vehicle for folding and unfolding wings and hanging for reuse, which aims at the main difficult restriction factors of the design of the existing hydrogen energy eVTOL flying vehicle.

The invention is realized by the following technical scheme: an eVTOL (eVTOL) aerodyne with reusable wings for extension and retraction comprises a rectifying shell, a power system, an engine room system, a wing extension system and a nose landing gear system;

the cabin system is positioned in the front shell of the rectifying shell, and driving equipment and seats are arranged in the cabin system;

the power system is positioned in a rear shell of the rectifying shell, the width and the height of the rear shell of the rectifying shell are larger than those of a front shell of the rectifying shell, and openings allowing airflow to pass through the power system are formed in the front end and the rear end of the rear shell of the rectifying shell;

the wing folding and unfolding system comprises supporting parts fixedly arranged on two sides below a front shell of the rectifying shell, each supporting part is hinged with a large-deflection wing capable of swinging back and forth along the horizontal direction, the free end of each large-deflection wing is rotatably provided with a motor wheel, the motor wheel can support the rear part of the rectifying shell, and the hubs of the motor wheels are arranged in a propeller arrangement mode;

the front undercarriage system comprises a rotating shaft arranged inside the lower portion of a front shell of the rectifying shell and a motor arranged in the front shell of the rectifying shell, the motor controls the rotating angle of the rotating shaft, two ends of the rotating shaft extend out of the front shell of the rectifying shell, two ends of the rotating shaft positioned outside the front shell of the rectifying shell are respectively provided with a large-deflection undercarriage extending forwards, the front end of the large-deflection undercarriage rotates to be provided with a brake wheel, and the brake wheel can support the front portion of the rectifying shell.

As a further improvement of the technical scheme of the invention, fuselage tail vertical wings are respectively arranged on two sides of the upper edge of the rear end of the rear shell of the rectifying shell, the upper parts of the fuselage tail vertical wings on the two sides are in a folded shape, a fuselage tail horizontal tail wing is arranged between the upper ends of the fuselage tail vertical wings on the two sides, a splitter plate is arranged between the middle part of the fuselage tail horizontal tail wing and the lower edge of the rear end of the rear shell of the rectifying shell, ducts are formed among the splitter plate, the fuselage tail horizontal tail wing and the adjacent fuselage tail vertical wings, and a duct fan is arranged in each duct.

As a further improvement of the technical scheme of the invention, the splitter plate divides the rear end opening of the rear shell of the rectifying shell into two regions, the tail guide plates of the airframe are distributed below the middle part of each region along the vertical direction, and the turning angles of all the tail guide plates of the airframe can be adjusted.

As a further improvement of the technical scheme of the invention, the rotating shaft is connected with the motor through a worm gear mechanism.

As a further improvement of the technical scheme of the invention, a buffer damper is arranged between the motor and the machine body.

As a further improvement of the technical scheme of the invention, the interior of the large-deflection wing is provided with a hollow cavity, the wing tip of the large-deflection wing is of a closed structure, the wing root of the large-deflection wing is communicated with the interior of the rear shell of the rectifying shell, the wing root of the large-deflection wing is hermetically connected with the rear shell of the rectifying shell, the front edge of the large-deflection wing is of a closed structure, and an air suction gap allowing air flow to enter is arranged above the rear edge of the large-deflection wing.

As a further improvement of the technical solution of the present invention, the middle upper portion of the rear end of the front casing of the rectifying casing is connected to the middle upper portion of the inner edge of the front end of the rear casing of the rectifying casing through at least three support rods 106, and the lower portion of the rear end of the front casing of the rectifying casing is connected to the lower portion of the inner edge of the front end of the rear casing of the rectifying casing in a sealing manner.

As a further improvement of the technical scheme of the invention, the unfolded large-deflection wing is gradually upwards arranged from inside to outside.

As a further improvement of the technical solution of the present invention, the front casing of the fairing casing is flush with the lower edge of the front casing of the fairing casing.

As a further improvement of the technical scheme of the invention, the upper surface of the rear shell of the rectifying shell is in a streamline arc shape gradually inclining downwards from front to back.

Compared with the prior art, the invention has the beneficial effects that:

(1) compared with a hydrogen fuel cell which adopts a vortex type hydrogen flame magnetohydrodynamic power generation/jet engine integrated machine and a power generation method patent (application number: 202110271364.5), the power system has the advantages of high power density, large range and high load capacity, and the technology is laid for the practicability of eVTOL.

(2) The wing folding and unfolding and the suspension reuse take ground running and air flight into consideration, and meanwhile, a suspension mechanism used as a vehicle is omitted, so that the dead weight of the flying vehicle during flying is reduced.

(3) The vertical take-off and landing mode of the whole tilting body saves a tilting mechanism of the vertical take-off and landing mode of the tilting wings, and reduces dead weight during flying.

(4) The trailing edge suction slot of the large-deflection wing effectively optimizes the flow field during high-elevation takeoff by utilizing a boundary layer suction technique and ensures the lift force of the large-deflection wing during high-elevation takeoff.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.

Fig. 1 is a schematic structural diagram of an eVTOL flying vehicle with a folding wing and a suspension for reuse according to the present invention.

Fig. 2 is a front view of an eVTOL flying vehicle with the folding wings and suspension multiplexed.

Fig. 3 is a schematic structural diagram of the wing-folding system.

Fig. 4 is a top view of an eVTOL flying vehicle with the folding wings and suspension multiplexed according to the present invention.

Fig. 5 is a schematic structural view of the nose landing gear.

Fig. 6 is another schematic structural diagram of the eVTOL flying vehicle with the folding wings and the suspension multiplexing.

Fig. 7 is another schematic structural diagram of the eVTOL flying vehicle with the folding wings and the suspension multiplexing.

Figure 8 is a cross-sectional view of the high deflection wing.

Figure 9 is a side view of the ewtol flying vehicle with the wings deployed and suspended for reuse.

Fig. 10 is a front view of the ewtol flying vehicle with the wings deployed and suspended for reuse.

Fig. 11 is a schematic vertical take-off and landing diagram of the eVTOL flying vehicle with the folding wings and the suspension multiplexing.

In the figure: 1-fairing shell, 101-fuselage tail vertical wing, 102-fuselage tail horizontal tail wing, 103-splitter plate, 104-ducted fan, 105-fuselage tail deflector plate, 106-support rod, 2-power system, 3-cabin system, 301-piloting equipment, 302-seat, 303-parachute cabin, 304-luggage cabin, 305-vehicle door, 4-folding wing system, 401-support part, 402-large deflection wing, 403-motor wheel, 404-air suction gap, 5-nose landing gear system, 501-rotating shaft, 502-large deflection landing gear, 503-motor, 504-worm gear mechanism, 505-buffer damper, 506-brake wheel.

Detailed Description

The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

As shown in fig. 1, the present invention provides a specific embodiment of an eVTOL aerobat with dual-use of a retractable wing and a suspension, which comprises a fairing body 1, a power system 2, a cabin system 3, a retractable wing system 4 and a nose landing gear system 5;

the cabin system 3 is positioned in a front shell of the rectifying shell 1, and driving equipment 301 and a seat 302 are arranged in the cabin system 3;

the power system 2 is positioned in a rear shell of the rectifying shell 1, the width and the height of the rear shell of the rectifying shell 1 are larger than those of a front shell of the rectifying shell 1, and openings allowing airflow to pass through the power system 2 are formed in the front end and the rear end of the rear shell of the rectifying shell 1;

the wing folding and unfolding system 4 comprises support parts 401 fixedly arranged on two sides below a front shell of the rectifying shell 1, each support part 401 is hinged with a large-deflection wing 402 capable of swinging back and forth along the horizontal direction, the free end of each large-deflection wing 402 is rotatably provided with a motor wheel 403, each motor wheel 403 can support the rear part of the rectifying shell 1, and the hubs of the motor wheels 403 are arranged in a propeller arrangement mode;

the nose landing gear system 5 comprises a rotating shaft 501 arranged inside the lower portion of a front shell of the rectifying shell 1 and a motor 503 arranged in the front shell of the rectifying shell 1, wherein the motor 503 controls the rotating angle of the rotating shaft 501, two ends of the rotating shaft 501 extend out of the front shell of the rectifying shell 1, two ends of the rotating shaft 501, which are positioned outside the front shell of the rectifying shell 1, are respectively provided with a large-deflection landing gear 502 extending forwards, the front end of the large-deflection landing gear 502 is rotatably provided with a brake wheel 506, and the brake wheel 506 can support the front portion of the rectifying shell 1.

In the present embodiment, the power system 2 may adopt the invention name of application No. 202110271364.5: the patent of vortex hydrogen flame magnetohydrodynamic power generation/jet engine integrated machine and power generation method. Of course, those skilled in the art can adopt other structural forms of the power component according to actual needs.

As shown in fig. 6 and 7, the present invention further provides a specific embodiment of the rectifying casing 1, that is, fuselage tail vertical wings 101 are respectively disposed on both sides of the upper edge of the rear end of the rear casing of the rectifying casing 1, the upper portions of the fuselage tail vertical wings 101 on both sides are folded, a fuselage tail horizontal tail wing 102 is disposed between the upper ends of the fuselage tail vertical wings 101 on both sides, a splitter plate 103 is disposed between the middle portion of the fuselage tail horizontal tail wing 102 and the lower edge of the rear end of the rear casing of the rectifying casing 1, ducts are formed between the splitter plate 103 and the fuselage tail horizontal tail wing 102 as well as between adjacent fuselage tail vertical wings 101, and a duct fan 104 is disposed in each duct.

Wherein the vertical wing 101 at the tail part of the fuselage is connected with the horizontal tail wing 102 at the tail part of the fuselage (integrally formed or welded at the later stage), and the middle part is separated by the splitter plate 103. The ducted fans 104 are distributed at the tail of the engine of the power system 2 in a bilateral symmetry manner, and the two ducted fans 104 rotate from top to bottom to suck and discharge airflow above the rear shell of the rectifying shell 1, so that the airflow stability of the upper surface of the rear shell of the rectifying shell 1 is improved, and a lifting surface is formed on the upper surface of the rectifying shell 1.

Specifically, the opening at the rear end of the rear casing of the rectifying casing 1 is divided into two regions by the flow distribution plate 103, a fuselage tail guide plate 105 is arranged below the middle of each region along the up-down direction, and the turning angle of all the fuselage tail guide plates 105 can be adjusted. The tail guide plate 105 of the aircraft body is positioned at the lower part of the duct, so that mutual interference with airflow formed by duct fans 104 in the duct can be avoided as far as possible, and flight control stability is enhanced.

As shown in fig. 5, the present invention further provides a connection manner between the rotation shaft 501 and the motor 503, that is, the rotation shaft 501 and the motor 503 are connected through a worm gear mechanism 504. Specifically, a turbine mechanism is coaxially arranged in the middle of the rotating shaft 501, a worm mechanism is coaxially arranged at the output end of the motor 503, and the turbine mechanism and the worm mechanism are matched with each other, so that the rotating shaft 501 is driven to rotate, and the large-deflection undercarriage 502 is further driven to rotate in the vertical direction.

In a specific application, the rotating shaft 501 is located in front of the wing folding and unfolding system 4. In this embodiment, the brake wheel 506 is located at the forward end of the large deflection landing gear 502, and the shaft portion of the brake wheel 506 is provided with a corresponding brake mechanism.

Further, a buffer damper 505 is disposed between the motor 503 and the body. In this embodiment, the damping damper 505 is fixedly connected to the body, and the damping damper 505 is movably connected to the motor 503. When the large-deflection undercarriage is impacted, the worm gear mechanism is pushed backwards to extrude the buffer damper 505, so that the shock absorption effect is achieved. The large deflection landing gear 502 acts as a pedal mechanism at takeoff; the large-deflection undercarriage 502 in the cruise state becomes a longitudinal wing lifting surface by the action of the turbofan of the power system 2.

Specifically, as shown in fig. 8, a hollow cavity is formed inside the large-deflection wing 402, a wing tip of the large-deflection wing 402 is of a closed structure, a wing root of the large-deflection wing 402 is communicated with the inside of the rear shell of the rectification shell 1, the wing root of the large-deflection wing 402 is hermetically connected with the rear shell of the rectification shell 1, a leading edge of the large-deflection wing 402 is of a closed structure, and an air suction gap 404 allowing an air flow to enter is formed above a trailing edge of the large-deflection wing 402. The trailing edge of the large-deflection wing 402 is bent upwards and forwards to form an air suction gap 404, and the airflow entering the large-deflection wing 402 through the air suction gap 404 further enters the rear shell of the rectification shell 1, so that the airflow in the power system 2 is improved.

In this embodiment, the support 401 is located at a transition position between the front casing and the rear casing of the fairing casing 1, the large-deflection wing 402 rotates along the support 401, specifically, in a retracting state and a deploying state, when the large-deflection wing 402 retracts backwards, the large-deflection wing cooperates with the electric locomotive wheel 403 to serve as a vehicle chassis suspension, and when the large-deflection wing deploys forwards, the large-deflection wing can be locked by the pin lock mechanism to serve as a sweepforward flying wing.

In this embodiment, the high deflection wing 402 has a thin tip and a thick root. And the propeller arrangement of the hub of the electric locomotive wheel 403 is in the form of propeller blades. When the motor wheel 403 rotates, the propeller of the hub has a propeller suction effect.

As shown in fig. 6, the middle upper portion of the rear end of the front casing of the rectifying casing 1 is connected to the middle upper portion of the inner edge of the front end of the rear casing of the rectifying casing 1 through at least three support rods 106, and the lower portion of the rear end of the front casing of the rectifying casing 1 is connected to the lower portion of the inner edge of the front end of the rear casing of the rectifying casing 1 in a sealing manner.

As shown in fig. 11, the deployed high-deflection wing 402 is disposed gradually upward from the inside to the outside.

As shown in fig. 9, the front casing of the rectifying casing 1 is flush with the lower edge of the front casing of the rectifying casing 1.

Further, the rear casing upper surface of the fairing casing 1 is in a streamline arc shape gradually inclining downwards from front to back.

In use, the cabin system 3 further comprises a canopy 303, a luggage compartment 304, and a door 305, wherein the seats 302 are arranged in a three-seater tandem arrangement. In this embodiment, the cabin system 3 is located in a front housing of the fairing housing 1, and the fairing housing 1, i.e. the fuselage, the umbrella cabin 303, the steering device 301, the seats 302, and the luggage cabin 304 are sequentially arranged from front to back, wherein the seats 302 in each row correspond to one vehicle door 305, the front two vehicle doors 305 in the direction of the nose open forward, the rear vehicle doors 305 open backward, and the doors of the luggage cabin 304 open upward. The streamlined nacelle becomes a lifting surface under the suction action of the turbofan of the power system 2.

The following provides a specific use method of the eVTOL flying vehicle with the folding wings and the suspension being reused in the embodiment:

the vertical lifting working process comprises the following steps:

(1) the aerocar is horizontally parked (as shown in the state of fig. 9), a motor 503 in the nose landing gear system 5 drives a worm gear mechanism 504 to rotate so as to drive the large-deflection landing gear 502 to be unfolded backwards, and the aerocar is supported to be in a large-angle takeoff state (as shown in fig. 11);

(2) the power system 2 works, the turbine blades of the power system 2 suck air from the front of the aircraft body, the tail gas is sprayed downwards after power generation, the aircraft is pushed to take off, after the aircraft is lifted off the ground, motor wheels 403 symmetrically distributed in the wing folding and unfolding system 4 rotate outwards, thrust is generated by air suction of a propeller hub to drive a large-deflection wing 402 to unfold, the tail airflow of the large-deflection wing 402 is sucked into the large-deflection wing 402 of the hollow cavity through an air suction gap 404 at the rear edge of the large-deflection wing 402, and finally the airflow enters the power system 2 through a rear shell of the rectifying shell 1, and the large-elevation take-off is realized under the suction effect of a boundary layer;

(3) when the large-deflection wing is completely unfolded, the large-deflection undercarriage 502 of the nose undercarriage system 5 is retracted under the action of the motor 503 and the worm gear mechanism 504, and the whole body of the airplane is leveled into a flying state (as shown in fig. 10) by deflecting the tail guide plate 105 of the airplane body in the flight control system downwards, and the motor wheels 403 are turned outwards to counteract the wing tip effect.

(4) When landing is needed, a tail guide plate 105 of a machine body in the flight control system deflects upwards, a machine head raises a large angle, meanwhile, a power system reduces working power, the machine body begins to descend, when the machine body descends to the position 1 m away from the ground, a motor wheel 403 in a wing folding and unfolding system 4 stops rotating, a large-deflection wing 402 retracts under the action of gravity, and a motor 503 and a worm gear mechanism 504 in a nose landing gear system 5 drive a large-deflection landing gear 502 to rotate backwards;

(5) after the large-deflection wing 402 and the large-deflection undercarriage 502 finish the retraction, the power system 2 increases the working power to ensure that the body does not stall due to the reduction of the lift force when the large-deflection wing 402 retracts, and at the same time, the flight control system dynamically adjusts the body posture to ensure the stable landing, and at the landing moment, the body gravity impacts the ground, so that the large-deflection wing 402 and the large-deflection undercarriage 502 serve as elastic damping structures to perform the damping function, and at the same time, the large-deflection undercarriage 502 drives the motor 503 and the worm gear mechanism 504 to move backwards to squeeze the buffer damper 505 to perform the damping and buffering function to finish the landing (as shown in fig. 11).

Short-distance taking off and landing process:

(1) the aerocar is horizontally parked (as shown in the state of fig. 9), under the action of the brake mechanism, the brake wheel 506 is not moved, the motor 503, the worm gear mechanism 504 and the motor wheel 503 act simultaneously, and the aerocar body is supported to a small-angle takeoff state (as shown in fig. 2);

(2) the engine of the power system 2 works to jet air backwards, the large-deflection undercarriage 502 is pedaled to the ground under the action of the motor 503 and the worm gear mechanism 504 to assist in taking off, the body of the airplane is lifted off the ground, the motor wheels 403 are reversely rotated to drive the large-deflection wings 402 to be unfolded, and the body of the airplane is leveled by the flight control system to enter a cruise state (as shown in fig. 10);

(3) when the airplane needs to land, the flight control system adjusts the airplane body to bow downwards, when the airplane falls to a certain height, the flight control system adjusts the airplane body to lift by a small angle, meanwhile, the motor wheels 403 rotate reversely to drive the large-deflection wings 402 to retract backwards, the motor 503 and the worm gear mechanism 504 drive the large-deflection undercarriage 502 to expand downwards, and the brake wheels 506 and the motor wheels 403 touch the ground;

(4) at the moment of touchdown, because the gravity of the body impacts the ground, the large-deflection wing 402 and the large-deflection undercarriage 502 serve as elastic damping structures to play a role in damping, and meanwhile, the large-deflection undercarriage 502 drives the motor 503 and the worm gear mechanism 504 to move backwards to extrude the buffer damper 505 to play a role in damping and buffering, so that the landing is completed.

A flight control process:

(1) active control

Pitch control: the tail guide plate 105 of the fuselage deflects up and down to generate a pitching moment to control the pitching of the fuselage;

yaw control: motor wheels 403 symmetrically distributed on the left and right in the wing folding and unfolding system 4 generate yawing moment through differential speed to control the yawing of the fuselage;

rolling: the airframe tail guide plates 105 which are symmetrically distributed left and right deflect independently, namely deflect up and down to generate roll moment to control airframe roll.

(2) Passive control

Pitching stabilization: the horizontal tail 102 at the tail of the fuselage passively controls pitching stability;

yaw stabilization: the vertical wing 101 at the tail of the airplane body passively controls yaw stability;

and (3) rolling stabilization: the deployed high-flexibility wing 402 is gradually arranged upwards from inside to outside, so that the deployed high-flexibility wing 402 is in a V shape, and the stability of roll is passively controlled.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.