阅读说明：本技术 一种直升平飞车 (Vertical lifting flying vehicle ) 是由 朱上翔 于 2021-08-06 设计创作，主要内容包括：本发明提出了一种直升平飞车,涉及飞行汽车的技术领域。包括用于提供动力的动力系统,提高升力的翼型车身,车身下部安装四轮起落架,供地面行驶。翼型车身包括车身前缘部和车身后缘部,为升降和巡航提供动力的可倾转倾转涵道风扇发动机,倾转涵道风扇发动机设置于车身后缘部上,和尾翼组件组成一体。尾翼组件置于车身后缘部和可倾转倾转涵道风扇发动机协同工作,并利用两台风扇发动机推力矢量纠正飞机偏航；其多用途旋翼既能够让使飞行器稳定地进行垂直起降或悬停；又能在进行水平飞行时,将转动的旋翼转化为固定机翼,同时将倾转倾转涵道风扇发动机的推力矢量转动到水平方向,整架飞行器变成固定机翼构型,可提高飞行器的巡航性能。(The invention provides a vertical lift flat aerodyne, and relates to the technical field of aerocars. The four-wheel lifting vehicle comprises a power system for providing power and a wing-shaped vehicle body for improving lift force, wherein a four-wheel undercarriage is arranged at the lower part of the vehicle body and is used for running on the ground. Wing section automobile body includes automobile body leading edge portion and automobile body trailing edge portion, for the duct fan engine that verts that can vert that goes up and down and cruise and provide power, the duct fan engine that verts sets up on automobile body trailing edge portion, and it is integrative to constitute with the fin subassembly. The empennage assembly is arranged at the rear edge part of the vehicle body and cooperates with the tiltable and tiltable ducted fan engines, and the thrust vectors of the two fan engines are utilized to correct the aircraft yaw; the multipurpose rotor wing can enable the aircraft to stably take off and land vertically or hover; and when horizontal flight is carried out, the rotating rotor wing is converted into the fixed wing, meanwhile, the thrust vector of the tilting and tilting ducted fan engine is rotated to the horizontal direction, the whole aircraft is converted into a fixed wing structure, and the cruising performance of the aircraft can be improved.)

1. A helicopter flying vehicle including a power system for providing power, comprising:

a wing body including a body front edge portion and a body rear edge portion;

the multifunctional rotor wing is used for converting the rotor wing and the fixed wing; the multifunctional rotor wing is arranged in the middle of the vehicle body;

the tilting ducted fan engine is arranged on the rear edge part of the vehicle body and used for providing power for the flying vehicle after the multifunctional rotor wing is converted into a fixed wing;

a tail assembly disposed on the rear edge portion of the vehicle body.

2. The helicopter flying vehicle of claim 1, further comprising a rotating mechanism for directionally adjusting the tilt ducted fan engine, wherein the rotating mechanism comprises a telescopic member and a support frame for fixing the tilt ducted fan engine, the support frame is hinged to the rear edge of the vehicle body, one end of the telescopic member is connected to the rear edge of the vehicle body, and the other end of the telescopic member is connected to the support frame.

3. The helicopter-flying vehicle of claim 1, wherein the multifunctional rotor comprises a wing mounting bracket, a telescopic driving shaft, two foldable rotor blades and a first transmission mechanism for driving the rotor blades to change into fixed wings, one end of the driving shaft penetrates through the front edge part of the vehicle body and is connected with the power system, and the other end of the driving shaft is connected with the wing mounting bracket; one of them the rotor blade with installing support fixed connection, another the rotor blade passes through first drive mechanism with the wing mounting bracket rotates to be connected.

4. A helicopter flying vehicle according to claim 3, wherein said rotor blade comprises a second transmission, a link and a folding member, said folding member being articulated to said link by said second transmission.

5. The helicopter flying vehicle of claim 4, wherein the second transmission mechanism comprises a motor, a speed reducer, a first driving gear, a second driving gear and a hinge, the motor is arranged on the connecting piece, an output shaft of the motor is connected with an input shaft of the speed reducer, an output shaft of the speed reducer is connected with the first driving gear, the first driving gear is meshed with the second driving gear, and the second driving gear is connected with the folding piece through the hinge.

6. The helicopter-flying vehicle of claim 1, wherein said front edge portion of said vehicle body is provided with one said multi-function rotor and said rear edge portion of said vehicle body is provided with another said multi-function rotor.

7. The helicopter of claim 6, further comprising a tail assembly disposed on the rear edge portion of the body, the tail assembly being slidably connected to the rear edge portion of the body.

8. The helicopter-flying vehicle of claim 1, wherein the wing body is in the shape of a lower flat upper convex wing.

9. The helicopter-flying vehicle of claim 1, wherein the wing-end standing vortex lift-increasing device is arranged on the side wall of the wing-shaped vehicle body.

10. The helicopter-flying vehicle of claim 1, wherein said multifunctional rotor is provided with a wingtip standing vortex lift-increasing device.

Technical Field

The invention relates to the technical field of aerocars, in particular to a vertical lift flat aerocar.

Background

Currently, the aeronautical field of aircraft generally falls into two main categories: the helicopter or the gyroplane realizes horizontal forward flight by virtue of the projections of the total lift force generated by the tilting paddle disk in the forward direction. These two types of aircraft each have their advantages and disadvantages. Each has its own primary purpose. Since the aircraft appeared for more than 100 years, there has been no attempt to produce a new model of aircraft that combines the advantages of both types of aircraft: the multifunctional all-in-one machine can take off and land in situ and has high efficiency and horizontal cruising. However, this goal has not been fully achieved to date. In recent decades, with the great development of advanced technologies such as automatic control, internet, artificial intelligence, new energy, new materials and intelligent transportation, the development of EVTOL (electric power vertical take-off and landing) aircrafts adapted to UAM (modern urban three-dimensional transportation) development based on DEP (distributed power) concepts has been promoted. To date, many large companies around the world, such as internet companies like boeing, airline for air, UBER's transportation service, google, and hundredths; traditional automotive companies such as Toyota, Honda, Benz, BMW, Jili, etc.; the technology is researched by Xiaopeng, Tesla and other new energy automobile companies and the like. Almost all aspects of modern transportation equipment manufacturing, operation, service are covered. Mainly, EVTOL is taken as a vertical lifting device in a broad sense, and the advantages of environmental protection (cleanness, no carbon dioxide emission and noise reduction) are highlighted. In addition, the urban land is short and expensive, and airports cannot be built everywhere, which is also a big factor for promoting EVTOL. The EVTOL just meets the requirements of modern urban intelligent three-dimensional traffic. The efficiency of the current EVTOL flat flight is still low. Due to the influence of low energy density of the battery and the characteristic of being limited by the movement mode of the helicopter, the EVTOL flight device has great use limitation, mainly focuses on poor horizontal navigation (cruising) performance, and still has the problems of low speed and short range.

The bottleneck of the dual-purpose aircraft which can simultaneously meet the requirements of high-efficiency flight of vertical take-off and landing-horizontal cruise cannot be developed at present, and the root cause of the problem is found out by analyzing the special movement mode of the helicopter, namely, the mode of relying on the rotary wings. The largest soft rib of the helicopter has poor efficiency when the helicopter is in horizontal flight. The reason for this is that the first, two types of aircraft have different flight principles: helicopters generate a vertically upward lift force through a rotor, and when the generated lift force is greater than the weight of an airplane, the helicopter can ascend or hover. The requirement on a power device system is high, and the thrust weight is large. When the helicopter flies forwards and horizontally, the paddle disk tilts forwards to generate a horizontal component force pointing forwards, so that horizontal acceleration is generated, and the horizontal flying speed is obtained. At the same time, more power needs to be generated to obtain a greater vertical pull-up force in order to balance the weight of the aircraft. The horizontal speed of helicopters is subject to various limitations. Aside from the power limitations of the fuel or electricity carried, it is also limited by the maximum speed of rotation at which shock waves are generated in order to prevent tip overspeed. In addition, the configuration of the helicopter and the jet of the main blade wash down stream onto the fuselage can present significant additional aerodynamic drag. The two parts of additional resistance, together with the normal resistance of the whole aircraft, are far larger than the aerodynamic resistance of the fixed-wing aircraft during the flat-flying movement, which can obviously reduce the forward flying speed of the rotorcraft. The maximum fly-flat speed of a conventional helicopter is typically 200 and 340 km/h. The maximum flat flight speed of the fixed wing aircraft with the same engine power can reach 700-900 km/h. Some even break through the sound barrier and fly at supersonic speed. In order to increase the level flight speed of the helicopter, an aeronautical engineer designs a hybrid high-speed helicopter, and the maximum level flight speed is increased to 436 km/h. The flying speed is improved by 28.2 percent. Tilting, heave-and-horizon aircraft, such as V-22, have been developed later. The maximum flat flying speed is further increased to 556 km/h, and is increased by 63.5 percent compared with a helicopter. But still have less cruise performance than fixed wing aircraft.

Disclosure of Invention

The invention aims to provide a vertical lift flat aerocar, which can not only enable an aircraft to take off and land vertically, but also convert a rotating rotor wing into a fixed wing during horizontal flight, thereby improving the cruising performance of the aircraft.

The embodiment of the invention is realized by the following steps:

the embodiment of the application provides a vertical lifting flying vehicle, which comprises a power system for providing power,

the wing-shaped vehicle body comprises a vehicle body front edge part and a vehicle body rear edge part;

the multifunctional rotor wing is used for changing the rotor wing and the fixed wing;

the tilting ducted fan engine is arranged on the rear edge part of the vehicle body and used for providing power for cruising after the multifunctional rotor wing is converted into the fixed wing;

the fin subassembly sets up on automobile body rear edge portion, provides stability and maneuverability for the aircraft.

In some embodiments of the present invention, the tilt ducted fan engine further includes a rotating mechanism for performing direction adjustment on the tilt ducted fan engine, the rotating mechanism includes a telescopic member and a support frame for fixing the tilt ducted fan engine, the support frame is hinged to the rear edge portion of the vehicle body, one end of the telescopic member is connected to the rear edge portion of the vehicle body, and the other end of the telescopic member is connected to the support frame.

In some embodiments of the invention, the multifunctional rotor comprises a wing mounting frame, a telescopic driving shaft, two foldable rotor blades and a first transmission mechanism for converting the driving blades into fixed wings, wherein one end of the driving shaft penetrates through the front edge part of a vehicle body and is connected with a power system, and the other end of the driving shaft is connected with the wing mounting frame; one of the rotor blades is fixedly connected with the mounting bracket, and the other rotor blade is rotatably connected with the wing mounting bracket through a first transmission mechanism.

In some embodiments of the invention, the rotor blade includes a second transmission, a link, and a folder, the folder being hinged to the link via the second transmission.

In some embodiments of the present invention, the second transmission mechanism includes a motor, a reducer, a first driving gear, a second driving gear, and a hinge, the motor is disposed on the connecting member, an output shaft of the motor is connected to an input shaft of the reducer, an output shaft of the reducer is connected to the first driving gear, the first driving gear is engaged with the second driving gear, and the second driving gear is connected to the folding member through the hinge.

In some embodiments of the invention, the front edge of the vehicle body is provided with a multifunctional rotor, and the rear edge of the vehicle body is provided with a multifunctional rotor.

In some embodiments of the present invention, the vehicle further comprises a tail assembly disposed on the rear edge portion of the vehicle body, the tail assembly being slidably connected to the rear edge portion of the vehicle body.

In some embodiments of the invention, the aerofoil body is of a downwardly flat and upwardly convex aerofoil shape.

In some embodiments of the invention, the wing-end standing vortex and lift increasing device is arranged on the side wall of the wing-shaped vehicle body.

In some embodiments of the invention, the multifunctional rotor wing tip is provided with a tip standing vortex lift-increasing device.

Compared with the prior art, the embodiment of the invention has at least the following advantages or beneficial effects:

a vertical lift flat flying vehicle comprises a power system for providing power, a wing-shaped vehicle body, a lifting device and a lifting device, wherein the wing-shaped vehicle body comprises a vehicle body front edge part and a vehicle body rear edge part; the multifunctional rotor wing is used for changing the rotor wing and the fixed wing; the ducted fan engine verts, and ducted fan engine verts sets up on automobile body rear edge portion for behind the multi-functional rotor transform for the stationary vane, for cruise and provide power. The fin subassembly sets up on automobile body rear edge portion, provides stability and maneuverability for the aircraft.

In order to realize a vertical lift and horizontal flight aerocar and obtain excellent flight performance, the most critical problem is whether to properly solve the negative influence caused by conversion when the vertical lift flight mode is transited to the horizontal flight mode. In addition, when climbing and horizontal cruise, proper treatment is good for rotor and engine vector direction, and is very important for improving cruise flight efficiency. In the history of aviation development, in order to improve the cruising flight efficiency, some people try to adopt a fixed wing flight configuration in the cruising section. The fixed wing is obtained by converting a rotor wing for vertical take-off and landing into a fixed wing through the transmission of a mechanical structure. However, this idea has not been successfully implemented. In order to successfully realize the design concept, the inventor has conducted intensive research on the key component of the multipurpose rotor, and the problem of switching between the rotor and the fixed wing is solved. The detailed description is referred to another invention (application No. 202110538541X) of the present inventor. This embodiment just adopts the wing subassembly that application number is mentioned in 202110538541X as the multi-functional rotor of this design for hovercar can adopt the rotor to go up and down at the in-process that goes up and down, and when hovercar is in cruise status, pass through mechanical structure's conversion with the rotor, become the fixed wing, through the duct fan engine that verts that sets up at its tail end, provide aircraft power, thereby reach and let hovercar utilize the fixed wing to cruise, make full use of the high lift-drag ratio advantage of wing, realize energy saving and emission reduction green flight. Wherein the power system in the flying automobile is the prior known technology. Therefore, compared with the prior art that the helicopter cruises by utilizing the inclination angle of the rotor wing, the energy utilization rate of the helicopter is improved, so that the cruises speed, the voyage and the time of voyage are greatly improved, and in addition, the aerocar in the design adopts a wing-shaped car body. Meanwhile, wing-end standing vortex lift-increasing devices are mounted on two sides of the vehicle body and two ends of the wings, and the flying vehicle aims to increase the whole aircraft lift force, increase the lift-drag ratio of the flying vehicle, fully utilize the aerodynamic characteristics of the flying vehicle and improve the flying performance of the flying vehicle.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

FIG. 1 is a schematic structural view of a helicopter of the present invention in a cruising state;

FIG. 2 is a schematic structural view of a vertical lift flying car in a lifting state according to the present invention;

FIG. 3 is a schematic structural view of a rotating mechanism according to the present invention;

FIG. 4 is a schematic view of the multifunctional rotor according to the present invention;

FIG. 5 is an enlarged view of a portion A of FIG. 4;

FIG. 6 is a schematic diagram of a helicopter flying vehicle of the present invention driving on land;

fig. 7 is another schematic structural diagram of a helicopter flying vehicle according to the present invention.

Icon: 1. a wing-shaped vehicle body; 11. a vehicle body front edge portion; 12. a vehicle body rear edge portion; 13. a wing end standing vortex lift-increasing device; 2. a multifunctional rotor wing; 21. a rotor blade; 211. a connecting member; 212. a folding member; 213. a second transmission mechanism; 2131. a motor; 2132. a speed reducer; 2133. a first drive gear; 2134. a second drive gear; 2135. a hinge; 22. a drive shaft; 23. a wing mount; 3. a tilt ducted fan engine; 4. a tail assembly; 5. a rotating mechanism; 51. a support frame; 52. a telescoping member.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the 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.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the embodiments of the present invention, it should be noted that, if the terms "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or the orientations or positional relationships that the products of the present invention are usually placed in when used, the terms are only used for convenience of description and simplification of the description, and do not indicate or imply that the devices or elements indicated must have specific orientations, be constructed and operated in specific orientations, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.

Furthermore, the terms "horizontal", "vertical" and the like do not require that the components be absolutely horizontal or overhanging, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the embodiments of the present invention, "a plurality" represents at least 2.

In the description of the embodiments of the present invention, it should be further noted that unless otherwise explicitly stated or limited, the terms "disposed," "mounted," and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; 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 by those skilled in the art according to specific situations.

Example 1

Referring to fig. 1, fig. 1 shows a vertical lift flying vehicle according to an embodiment, which includes a power system for providing power,

the wing type vehicle body 1 comprises a vehicle body front edge part 11 and a vehicle body rear edge part 12;

the multifunctional rotor wing 2 is used for changing the rotor wing and the fixed wing;

the tilt ducted fan engine 3 is arranged on the rear edge part 12 of the vehicle body, and is used for providing power for cruising after the multifunctional rotor wing 2 is changed into a fixed wing;

the tail assembly 4, which is disposed on the rear edge portion 12 of the vehicle body, provides stability and maneuverability to the aircraft.

In some embodiments of the present invention, in order to achieve good flight performance for a helicopter flying car, it is most critical to address a safe and reliable transition from the vertical lift flight mode to the horizontal flight mode. Meanwhile, when climbing and horizontal cruise are carried out, the problem of improving the cruise flight efficiency is solved. The invention adopts a method for converting the whole aircraft into a fixed wing configuration in climbing (descending) and horizontal cruising stages. The fixed wing is obtained by converting a rotor wing for vertical take-off and landing into a fixed wing through the transmission of a mechanical structure. Horizontal flight power is obtained by tilting the thrust vector parallel to the longitudinal axis of the fuselage. Please refer to another invention of the present inventor (application No. 202110538541X), which is an embodiment of the present invention for converting a rotor wing into a fixed wing. Through the full-mechanical configuration conversion, the flying automobile climbs (descends) and cruises horizontally by using the fixed wings. The high lift-drag ratio advantage of the wings is fully utilized, and energy-saving and emission-reducing green flight is realized. As shown in fig. 2. When the aerocar climbs and cruises horizontally, the rotor wing is changed into a fixed wing through the conversion of a mechanical structure, and the aircraft power is provided through a tilting ducted fan engine 3 arranged at the tail end of the fixed wing and a horizontal thrust vector, as shown in figure 1. The power system in the interior of an aerocar is well known in the art. Compared with the helicopter in the prior art which utilizes the rotor wing to incline for climbing and level cruising, the range and cruising speed are greatly improved. In addition, the flying automobile in the design adopts a wing-shaped automobile body 1 and a wing end standing vortex lift-increasing device; the rotor wing or the fixed wing is also provided with a wing end standing vortex lift increasing device, and the device aims to increase lift force, reduce resistance and increase the lift-drag ratio of the aerocar, thereby fully utilizing the aerodynamic characteristics of the aerocar and improving the whole flight efficiency.

In some embodiments of the present invention, the wing assembly of application No. 202110538541X is used as a rotor of a helicopter, and can be used as an emergency life saving device in case of a failure. The specific implementation mode is that the fixed wing in the cruise process is converted into a free rotor wing working mode, the paddle disc is inclined backwards to form an included angle of 5 degrees with the vertical direction, and meanwhile, if possible, the jet orifice of the tilting ducted fan engine 3 is downward, so that the falling speed of the vertical lift flat aerodyne is reduced in the falling process, the impact load on an automobile body and passengers is reduced, the casualties of the personnel can be avoided or reduced, and the safety is improved.

Referring to fig. 3, in some embodiments of the present invention, the present invention further includes a rotating mechanism 5 for performing direction adjustment on the tilt ducted fan engine 3, the rotating mechanism 5 includes a telescopic member 52 and a supporting frame 51 for fixing the tilt ducted fan engine 3, the supporting frame 51 is hinged to the rear edge portion 12 of the vehicle body, one end of the telescopic member 52 is connected to the rear edge portion 12 of the vehicle body, and the other end of the telescopic member 52 is connected to the supporting frame 51.

In some embodiments of the present invention, the helicopter mainly has the multifunctional wing located at the front edge 11 of the vehicle body to work in a rotor mode during the vertical takeoff and landing stage, and the working state is very complicated as the rotor of a conventional helicopter, and in order to maintain the full-aircraft balance, in addition to the torque conversion and the roll tendency of the auto-balance, the yaw moment generated by the single rotor needs to be overcome. It is common practice to add a tail rotor at the tail of the fuselage. In the overall configuration of the invention, the tail rotor is eliminated. The present embodiment uses the thrust vector roll of the tilt ducted fan engine 3 for yaw adjustment. The roll stabilization is performed by utilizing the differential of the thrust vectors of the two fan engines. The specific embodiment is that after the supporting frame 51 is hinged to the rear edge part 12 of the vehicle body, the telescopic member 52 is used for driving the supporting frame, wherein the telescopic member 52 can be a hydraulic telescopic rod, and can also be a linear pushing motor 2131, and in this embodiment, a hydraulic pushing rod is used, so that the supporting frame 51 can rotate on a vertical plane.

Referring to fig. 2 and 4, in some embodiments of the present invention, the multifunctional rotary wing 2 includes a wing mounting bracket 23, a telescopic driving shaft 22, two foldable rotary wing blades 21, and a first transmission mechanism for driving the blades to change into fixed wings, wherein one end of the driving shaft 22 passes through the front edge portion 11 of the vehicle body and is connected to the power system, and the other end of the driving shaft 22 is connected to the wing mounting bracket 23; one of the rotor blades 21 is fixedly connected with the mounting bracket, and the other rotor blade 21 is rotatably connected with the wing mounting bracket 23 through a first transmission mechanism.

In some embodiments of the present invention, the lateral space occupied on the road is limited for existing car driving, and thus, the airworthiness regulations may limit the spanwise size of the flying car. The span of the flying vehicle cannot exceed the width of a lane. For this reason, the inventor of the present invention has made an improvement on a wing assembly of another invention application No. 202110538541X, wherein the first transmission mechanism still uses the transmission mechanism of the wing assembly of 202110538541X, and the improvement is that the first transmission mechanism is configured as a foldable rotor blade 21 for effectively storing the rotor during road running, so as to avoid affecting other running vehicles and enhance the appearance. In addition, a telescopic driving shaft 22 is arranged, and in the lifting process of the vertical lifting flying car, in order to reduce the pneumatic interference of the washing flow generated by the rotor wing during working on the car body, the working height of the rotor wing is set to be higher than the car body by a certain distance in the lifting stage. When the aerocar enters climbing and horizontal cruising at the end of the vertical take-off and landing stage, the length of the driving shaft 22 is contracted to enable the fixed wing to be close to the upper surface of the aerocar body. The profile when driving on a road surface is shown in fig. 6.

Referring to fig. 4, in some embodiments of the present invention, rotor blade 21 includes a second transmission mechanism 213, a connecting member 211, and a folding member 212, and folding member 212 is hinged to connecting member 211 via second transmission mechanism 213.

In some embodiments of the present invention, the folding of the blade mainly aims to reduce the occupied space during road driving and transportation, and in order to ensure the structural strength of the rotor blade 21, the present embodiment adopts a mode that the wing tips are folded up and down, and adopts a hinged mode to connect the connecting piece 211 and the folding piece 212, so as to ensure the structural strength.

Referring to fig. 5, in some embodiments of the present invention, the second transmission mechanism 213 includes a motor 2131, a reducer 2132, a first driving gear 2133, a second driving gear 2134, and a hinge 2135, which are disposed on the connecting member 211, an output shaft of the motor 2131 is connected to an input shaft of the reducer 2132, an output shaft of the reducer 2132 is connected to the first driving gear 2133, the first driving gear 2133 is engaged with the second driving gear 2134, and the second driving gear 2134 is connected to the folding member 212 through the hinge 2135.

In some embodiments of the present invention, for the specific folding manner of the multifunctional rotor 2, the motor 2131 is mainly used as a driving power source, then the reducer 2132 is used to adjust the required rotation speed or torque, and the first driving gear 2133 and the second driving gear 2134 are used to cooperate with the hinge 2135 to rotate the connecting member 211 and the folding member 212 upwards or downwards.

As shown in fig. 7, in some embodiments of the present invention, the multifunctional rotor 2 may be disposed in the middle of the airfoil body, and the two ducted fans at the tail may be distributed in a distributed manner, and the wider the distance between the ducted fans, the less influence the ducted fans on each other, and the better the effect of providing thrust.

Example 2

Referring to fig. 7, in the present embodiment, based on the technical solution of embodiment 1, it is proposed that a front edge portion 11 of a vehicle body is provided with one multifunctional rotor 2, and a rear edge portion 12 of the vehicle body is provided with another multifunctional rotor 2.

In some embodiments of the invention, in order to generate sufficient upward pulling force during the lifting process of the helicopter flying vehicle, a plurality of rotary wings are arranged in the embodiment. The specific embodiment is that a multifunctional rotor 2 with a larger size is arranged at the front edge part 11, a multifunctional rotor 2 with a smaller size is arranged at the rear edge part 12, the multifunctional rotor 2 with the larger size is mainly used for balancing most of the gravity of the helicopter flyer, the multifunctional rotor 2 with the smaller size at the rear edge part 12 and the ducted fan engine 3 are used for balancing the rear gravity, wherein the multifunctional rotor 2 with the smaller size at the rear edge part 12 is arranged at the position, close to the rear body, of the helicopter flyer, the rotating direction of the rear rotor is opposite to that of the front rotor, the yawing moment generated by most of the front rotor is eliminated, the remaining yawing moment which is not completely eliminated is deflected by the thrust vectors of the two tilted ducted fan engines at the rear part, the yawing moment is completely eliminated, and the safety is improved.

Referring to fig. 7, in some embodiments of the present invention, the present invention further includes a tail assembly 4, the tail assembly 4 is disposed on the rear edge portion 12 of the vehicle body, and the tail assembly 4 is slidably connected to the rear edge portion 12 of the vehicle body.

In some embodiments of the invention, the empennage is provided to ensure that the aircraft is at an optimum attitude when the helicopter is flying in a fixed wing aircraft configuration, using the empennage assembly 4 to control the direction, roll and pitch angles of the aircraft. The empennage assembly 4 is connected with the rear edge part 12 in a sliding mode, the length of a vehicle body is limited due to the fact that the helicopter is required to run on the ground, the control surface is close to the center of gravity of the whole aircraft, therefore, the empennage assembly 4 slides on the rear edge part 12, the focus position of the whole aircraft is adjusted conveniently, and the control and stability characteristics of the helicopter in the flying process meet the airworthiness requirements.

Referring to fig. 1, in some embodiments of the present invention, the wing body 1 is a wing type with a flat lower part and a convex upper part.

Referring to fig. 1, in some embodiments of the present invention, a wing tip standing vortex lift-increasing device 13 is disposed on a sidewall of an airfoil body 1.

In some embodiments of the invention, the wing aspect ratio is also reduced because both vertical take-off and landing and cruise flight are required during cruise of such a helicopter aerodyne, and when applied to the field of aerocars, the spanwise dimension of the wing needs to be properly adjusted due to road restrictions. The low aspect ratio wing also has the additional advantages: the rigidity of the wing becomes strong, and the requirement of structural materials is reduced. The three-dimensional vertical lift line has the disadvantages that the slope of the three-dimensional vertical lift line is reduced, the lift force of the blade is greatly reduced, and the induced resistance is increased. In addition, the blade can be used as a rotor blade and a fixed wing blade at the same time, and the aerodynamic performance, particularly the lift-drag ratio K, of the blade is closely related to the flight performance. The lift-drag characteristics of the blades of the EVTOL and the resulting rotor power and lift-drag ratio of horizontal flight are particularly important. Due to various limiting conditions, the EVTOL has a short span length, a small aspect ratio and insufficient lift force, and in order to solve the problems, the embodiment adopts a wingtip standing vortex lift-increasing device 13 of another application number CN202011258085.5 of the inventor, so as to improve the flight performance of the vehicle body and the rotor during cruising.

In summary, the embodiments of the present invention provide a helicopter flying vehicle, which comprises a pair of rectangular or trapezoidal rotor wings (one on each of the left and right sides, and the rotor wings are axisymmetrically distributed), and the wing section is a symmetric wing with zero camber; the rotor wing has a short span length not more than 4 meters (equivalent to the width of a lane), is a wing with a small aspect ratio, and has low aerodynamic efficiency. In order to compensate for the loss of lift, the area of the rotor is slightly larger. By using a wingtip standing vortex lift-increasing device 13 of another patent application number CN202011258085.5 applied by the applicant, the lift force of the multifunctional rotor wing 2 with small aspect ratio is greatly improved. The induced resistance is reduced. When the multifunctional wing works as a rotor wing, the position is raised and is away from the body (vehicle body) by a certain distance, so that the interference of washing down is reduced; it is different from ordinary automobile in that its body is wing type, and the wing type is specially designed, and its thickness is large (greater than 20% -35% of aerodynamic chord), lift force is large and lift-drag ratio is very high (up to 200), and its aspect ratio is only 0.36. After the wing end standing vortex lift increasing technology is adopted, the lift force is increased to 4.3 times of the original lift force. The vehicle body can provide considerable lift. The back part is provided with two foldable and retractable ducted fans which can be tilted. There are three conditions of power distribution: in the lifting stage, the main rotor only bears one-half to two-thirds of the total load. And the differential motion of the ducted fan is utilized to correct the yawing moment caused by the single rotor. The rectification tail rotor is omitted. A V-shaped tail assembly is employed. The machine can move back and forth to ensure the longitudinal stability of the whole machine. The rotor is designed into a wing three-purpose configuration: when the rotor wing is vertically lifted, the front edge and the rear edge of the left wing and the rear edge of the right wing are 180 degrees apart; when the aircraft is cruising horizontally, the fixed wing is used as a fixed wing, and the front edge and the rear edge of the left wing and the right wing are in the same direction; when the emergency force landing is performed (through a switching mechanism), the self-rotating wing is taken as a self-rotating wing, and is unhooked with a power system, so that the lift force is generated to prevent the sinking speed of the whole aircraft, and the function of the life-saving parachute is similar. From the helicopter to the level flight mode. The ducted fan tilts, the rotor gradually stops rotating, and the left (or right) wing is converted into a state that the front edge and the rear edge are opposite. The wings are fixed to the fuselage. The whole process is completed by artificial intelligence software. The opposite is true for the landing process.

Incidentally, the following description: the present specification mainly illustrates the configuration and the working principle of the aerocar with vertical take-off and landing. Belonging to a vertical take-off and landing (VTOL) aircraft. If the aerocar is also the aerocar, the power of the power system is slightly reduced without installing the multifunctional wings, the tiltable ducted fan engine is changed into a fixed ducted fan engine, and the rest is unchanged, namely the short-range take-off and landing (STOL) aircraft which runs horizontally. The two flying automobiles with different configurations have different flight performance and different benefits, and can be respectively applied to different scenes to serve different purposes.

The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.