CN212579543U

CN212579543U - Urban air aerocar

Info

Publication number: CN212579543U
Application number: CN202021818505.6U
Authority: CN
Inventors: 熊俊; 吕万韬; 陶刘远
Original assignee: Cetc Wuhu Diamond Aircraft Manufacture Co ltd; Cetc Wuhu General Aviation Industry Technology Research Institute Co ltd
Current assignee: Cetc Wuhu Diamond Aircraft Manufacture Co ltd; Cetc Wuhu General Aviation Industry Technology Research Institute Co ltd
Priority date: 2020-08-26
Filing date: 2020-08-26
Publication date: 2021-02-23
Anticipated expiration: 2030-08-26

Abstract

The utility model discloses an urban air flying automobile, which comprises a pair of foldable front wings and a pair of tiltable coaxial reversal dual-rotor systems which are arranged on a front fuselage and are symmetrical about the fuselage, a main coaxial reversal dual-rotor system arranged on a rear fuselage and a pair of foldable main wings which are symmetrical about the fuselage; when the automobile rises and flies, the two pairs of foldable wings are parallel to the body, and a double-rotor system provides lift force; when the automobile lands and runs on the ground, the two pairs of foldable wings are folded to be vertical to the body, and a plurality of small wheels at the edges of the foldable wings extend out to support the body to run on the ground; in the process, forward thrust, backward reverse thrust and rolling force are provided by the tiltable coaxial reverse rotation double-rotor system. The utility model discloses a scheme that triaxial tilting rotor and high lift wing combined together has improved driving system thrust-weight ratio, and hovercar overall scheme resistance is little, and flight speed is fast. The front wing and the rear wing are designed to be foldable, and can serve as landing gears when landing, and the structural efficiency is improved.

Description

Urban air aerocar

Technical Field

The utility model relates to a vehicle field, in particular to city air aerocar.

Background

At present, the development of urban air taxi projects is emerging, and great domestic and overseas aviation companies such as Boeing, air passenger and small entrepreneurship companies all invest a large amount of resources for research and development. For example, Boeing PAV products of Boeing company, 8 propellers are arranged on longitudinal beams of landing gears on two sides of an airplane to provide vertical take-off and landing lift force, and 1 propeller is adopted at the rear part of a fuselage to provide advancing power of the airplane. According to the scheme, the landing gear beam body does not generate lift force in normal flight of the airplane, and the structural efficiency is low. For example, the City Airbus product of French Airbus company installs 4 fan ducts on both sides of the airplane, adopts 4 pairs of coaxial contra-propeller propellers to provide vertical take-off and landing lift force, realizes the inclination of the propellers through a torque conversion mechanism, and converts part of the lift force into the advancing power of the airplane. The scheme is similar to a helicopter, and has large flight resistance and low flight speed. The Lilium Jet of the Lilium aviation of the German venture company adopts 12 tiltable ducted fans on the left wing and the right wing respectively, 6 tiltable ducted fans are adopted on two sides of the front fuselage respectively, and 36 ducted fans provide the vertical take-off and landing lift force and the forward thrust force of the airplane. The ducted fans adopted by the scheme are more in number, the power efficiency is lower, and the thrust weight is smaller. The German Volocopter adopts 18 rotor wings to provide the lift force and the advancing power of the airplane, and the proposal adopts a plurality of ducted fans, so that the power efficiency is lower, the thrust weight is smaller, and the resistance of the airplane is larger. The Guangzhou Yihang in China adopts 4-shaft 8-rotor wings to provide aircraft lift force, realizes the inclination of a propeller through a torque conversion mechanism, and converts part of components of the lift force into aircraft advancing power. The scheme is similar to a helicopter, and has large flight resistance and low flight speed.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to the problem that above-mentioned prior art exists, provide a can improve aircraft power system thrust-weight ratio, reduce the resistance, improve the aerial hovercar in city of advantages such as flying speed and structural efficiency.

Realize the utility model discloses the technical solution of purpose does: an urban air flying automobile comprises a main body, a pair of front wings and a pair of vertical tails, a pair of foldable front wings and a pair of tiltable coaxial reversing dual-rotor systems, a main coaxial reversing dual-rotor system and a pair of foldable main wings, wherein the pair of front wings and the pair of vertical tails are respectively positioned on a front fuselage and a rear fuselage and are symmetrical relative to the fuselage;

when the automobile is lifted and flies, the pair of foldable front wings and the pair of foldable main wings are parallel to the body, and the pair of tiltable coaxial reverse dual-rotor systems cooperate with the main coaxial reverse dual-rotor system to provide lift force for the main body;

when the automobile lands and runs on the ground, the pair of foldable front wings and the pair of foldable main wings are folded to be perpendicular to the body, and meanwhile, the foldable front wings and the plurality of small wheels arranged on the edges of the foldable main wings extend out to support the body to run on the ground;

in the process, a pair of tiltable coaxial reverse rotation double-rotor systems provides forward thrust, backward reverse thrust and rolling force for the main body.

Furthermore, the front wing is of a polygonal frame structure, and is used for supporting the foldable front wing and simultaneously surrounding and protecting the foldable front wing by a tiltable coaxial contrarotation dual-rotor system, and the cross section of the polygonal frame structure is an airfoil section.

Furthermore, the pair of tiltable coaxial counter-rotating dual-rotor systems are respectively arranged at two ends of a rotating shaft positioned at the lower part of the front fuselage, the rotating shaft is fixed at the lower part of the front fuselage through two ball bearings symmetrically arranged on the shaft, and a driving rotating tooth is arranged between the two ball bearings on the shaft; the rotating shaft is driven to rotate by a driving system.

Furthermore, the driving system comprises a double-shaft motor arranged at the lower part of the front machine body and a pair of gears arranged on torque output shafts at two ends of the motor, and the gears are meshed with the driving rotating teeth; the double-shaft motor drives the rotating shaft to rotate in forward/reverse directions so as to change the thrust direction of the tiltable coaxial reverse double-rotor system into forward thrust or backward reverse thrust, and when the automobile is lifted, the axial line of the tiltable coaxial reverse double-rotor system is upward.

Furthermore, the main coaxial reverse rotation dual-rotor system comprises an upper set of rotor system and a lower set of rotor system which are opposite in rotation direction and coaxial, wherein the upper rotor system comprises a group of upper rotor blades arranged on the side surface of an upper rotor spindle, and the spindle is driven to rotate by an upper motor fixed on an upper motor support stator; the lower rotor system comprises a group of lower rotor blades arranged on the side surface of a lower rotor spindle, and the spindle is driven to rotate by a lower motor fixed on a lower motor support stator; the support stator is fixed on the rear machine body.

Furthermore, the folding structures of the foldable front wing and the foldable main wing comprise retractable actuating cylinders respectively arranged in the fixed wing and the foldable wing, and a telescopic buffer gas spring arranged between the outer sides of the fixed wing and the foldable wing, and after the foldable wing is folded relative to the fixed wing, the three form a stable triangular structure for supporting; the folding wing is a foldable front wing or a foldable main wing, and the fixed wing is a front wing or a rear fuselage.

Furthermore, a deflectable control surface is arranged on the vertical fin, and pitching and yawing control moment is provided for the flying of the automobile.

Further, the electric power of each part of the flying automobile is provided by a power battery system, and the power battery system comprises a power battery I area arranged on the foldable front wing, a power battery II area arranged on the foldable main wing, a power battery III area arranged at the rear part of the main body and a power battery IV area arranged on the vertical tail.

Compared with the prior art, the utility model, it is showing the advantage and is: the scheme that the three-axis tiltable rotor wing and the high lift wing are combined is adopted, the thrust-weight ratio of the power system of the flying automobile is improved, and the total scheme of the flying automobile is small in resistance and high in flying speed; the front wing and the rear wing are designed to be foldable, and can serve as landing gears when landing, and the structural efficiency is improved.

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

Drawings

FIG. 1 is a top view of an embodiment of an urban air vehicle in flight.

FIG. 2 is an elevation view of an embodiment of an urban air vehicle in flight.

FIG. 3 is a side view of an embodiment of an urban air vehicle in flight.

FIG. 4 is a side view of an embodiment of an urban air vehicle in a landing or ground travel position.

Figure 5 is a schematic diagram of an embodiment of a tiltrotable coaxial contra-rotating dual rotor system.

Figure 6 is a schematic illustration of dual rotors in a primary coaxial contra-rotating dual rotor system according to one embodiment.

Figure 7 is a partial view of a foldable wing in one embodiment.

Fig. 8 is a schematic diagram of power battery partition in one embodiment.

Detailed Description

In order to facilitate understanding of the present invention, the present invention will be described more fully hereinafter with reference to the accompanying drawings. Preferred embodiments of the present invention are shown in the drawings. The invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.

It should be noted that, if directional indications such as up, down, left, right, front, and back … … are provided in the embodiment of the present invention, the directional indications are only used to explain the relative position relationship between the components, the motion situation, etc. in a specific posture as shown in the drawings, and if the specific posture is changed, the directional indications are changed accordingly.

In addition, if there is a description relating to "first", "second", etc. in the embodiments of the present invention, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, the technical solutions in the embodiments may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should not be considered to exist, and is not within the protection scope of the present invention.

In one embodiment, with reference to fig. 1 to 4, the present invention provides an urban air flying automobile, comprising a main fuselage 1, a pair of front wings 2 and a pair of vertical tails 5, which are respectively located on the front fuselage and the rear fuselage and are symmetrical with respect to the fuselage, a pair of foldable front wings 3 and a pair of tiltable coaxial contra-rotating dual-rotor systems 6, which are arranged on the front fuselage and are symmetrical with respect to the fuselage, a main coaxial contra-rotating dual-rotor system 7 arranged on the rear fuselage and a pair of foldable main wings 4, which are symmetrical with respect to the fuselage;

when the automobile is lifted and flies, the pair of foldable front wings 3 and the pair of foldable main wings 4 are parallel to the fuselage, and the pair of tiltable coaxial reverse dual-rotor systems 6 cooperate with the main coaxial reverse dual-rotor system 7 to provide lift force for the main fuselage 1;

when the automobile lands and runs on the ground, the pair of foldable front wings 3 and the pair of foldable main wings 4 are folded to be perpendicular to the automobile body, and meanwhile, a plurality of small wheels 12 arranged at the edges of the foldable front wings 3 and the foldable main wings 4 extend out to support the automobile body to run on the ground;

in the above process, a pair of tiltable coaxial counter-rotating dual rotor systems 6 provides forward thrust, backward reverse thrust and rolling force for the main body 1. Here, roll is achieved by providing differential lift by means of a tiltable coaxial counter-rotating dual rotor system in each case one 6 to the left and the right in the lower part of the front fuselage. When the automobile runs on the ground, the rolling force is the steering force.

Here, the main fuselage is designed as a wing-body fusion structure, the fuselage waistline is designed with strake wings 8 with smooth transition, the fuselage cockpit is designed with two to seven seats, the basic version can accommodate two passengers, and the home version can accommodate seven passengers at most.

Further, in one embodiment, the front wing 2 is a polygonal frame structure for supporting the foldable front wing 3 and surrounding and protecting the tiltable coaxial contra-rotating dual-rotor system 6, and the cross section of the polygonal frame structure is a wing profile, which can provide additional lift for the hovercar.

Further, in one embodiment, referring to fig. 5, the pair of tiltable coaxial contra-rotating dual rotor systems 6 are respectively disposed at two ends of a rotating shaft 10 located at the lower part of the front fuselage, the rotating shaft 10 is fixed at the lower part of the front fuselage through two ball bearings 33 symmetrically disposed on the shaft, and a driving rotary tooth 34 is disposed between the two ball bearings 33; the rotating shaft 10 is driven to rotate by a driving system.

Further, in one embodiment, referring to fig. 5, the driving system includes a two-shaft motor 32 disposed at the lower portion of the front body, and a pair of gears 35 mounted on torque output shafts at both ends of the motor, both engaging with the driving rotary teeth 34; the dual-axis motor 32 clockwise/counter-rotates to drive the rotating shaft 10 to rotate so as to change the thrust direction of the tiltable coaxial counter-rotating dual-rotor system 6 into forward thrust or backward counter-thrust (the rotating shaft rotates to drive the tiltable coaxial counter-rotating dual-rotor system to rotate forward and backward, the forward direction is the direction toward the automobile, the maximum rotation angle is 90 degrees as shown in fig. 3 and 4), and when the automobile rises, the axis of the tiltable coaxial counter-rotating dual-rotor system 6 is upward as shown in fig. 2. After the automobile is lifted off, the aerocar slowly obtains forward thrust and flight speed by rotating the tiltable coaxial reversing dual-rotor system 6 forwards, and when the speed V is gradually increased, the foldable front wing 3 and the foldable main wing 4 obtain enough lift force to compensate the reduction of the aerocar lift force caused by the forward tilting of the tiltable coaxial reversing dual-rotor system 6.

Further, in one embodiment, and with reference to fig. 6, the primary coaxial contra-rotating dual rotor system 7 comprises upper and lower sets of counter-rotating, coaxial rotor systems, wherein the upper rotor system comprises a set of upper rotor blades 13 disposed laterally to an upper rotor mast 19 (or blade mounting flange) that is driven in rotation by an upper motor 15 secured to an upper motor support stator 17; the lower rotor system includes a set of lower rotor blades 14 disposed laterally of a lower rotor mast 20 (or blade mounting flange) that is driven in rotation by a lower motor 16 secured to a lower motor support stator 18; the support stator is fixed on the rear machine body.

Here, the number of rotor blades per group is preferably three to six.

Further, in one embodiment, referring to fig. 7, the folding structure of the foldable front wing 3 and the foldable main wing 4 includes retractable actuating cylinders respectively disposed in the fixed wing 23 and the foldable wing 24, and a retractable buffer gas spring 27 disposed between the outer sides of the fixed wing 23 and the foldable wing 24, and the foldable wing 24 forms a stable triangular structure for supporting after being folded relative to the fixed wing 23; the folding wing 24 is a foldable front wing 3 or a foldable main wing 4, and the fixed wing 23 is a front wing 2 or a rear fuselage.

Further, in one embodiment, the folding wing 24 is hinged with respect to the fixed wing 23, such as the front wing hinge line 21 and the main wing hinge line 22 shown in fig. 4.

Further preferably, in one embodiment, the vertical fin 5 has a V-shaped structure.

By adopting the scheme of the embodiment, the lateral stability of the automobile can be improved, and the anti-crosswind capability is improved.

Further preferably, in one embodiment, the vertical fin 5 is provided with a deflectable control surface 11 to provide a pitch and yaw moment for the car to fly.

Further, in one embodiment, referring to fig. 8, the power of the components of the flying car is provided by a power battery system, which comprises a power battery I area 28 arranged on the foldable front wing 3 (power batteries are arranged in the wing box of the foldable front wing), a power battery II area 29 arranged on the foldable main wing 4 (power batteries are arranged in the wing box of the foldable main wing), a power battery III area 30 arranged on the rear part of the main body (power batteries are arranged on the rear part of the cockpit), and a power battery IV area 31 arranged on the vertical tail 5 (power batteries are arranged in the wing box of the vertical tail).

Preferably, the power battery is a chargeable and dischargeable lithium ion battery or a hydrogen fuel battery.

To sum up, the utility model discloses a scheme that triaxial can tilt rotor and high lift wing combined together has improved hovercar driving system thrust-weight ratio, and hovercar overall scheme resistance is little, and flight speed is fast. The front wing and the rear wing are designed to be foldable, and can serve as landing gears when landing, and the structural efficiency is improved. The air traffic trip solution can be provided for the large-scale cities of millions of population levels at present, and the problem of difficult trip of the large-scale cities due to traffic congestion is solved.

The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims

1. An urban air flying automobile comprises a main body (1), a pair of front wings (2) and a pair of vertical tails (5), wherein the front wings and the vertical tails are respectively positioned on a front body and a rear body and are symmetrical relative to the main body, and is characterized by further comprising a pair of foldable front wings (3) and a pair of tiltable coaxial reversing dual-rotor systems (6) which are arranged on the front body and are symmetrical relative to the main body, a main coaxial reversing dual-rotor system (7) and a pair of foldable main wings (4) which are symmetrical relative to the main body, wherein the main wings and the vertical tails are arranged on the front body and the rear body;

when the automobile is lifted and flies, the pair of foldable front wings (3) and the pair of foldable main wings (4) are parallel to the body, and the pair of tiltable coaxial reverse dual-rotor systems (6) cooperate with the main coaxial reverse dual-rotor system (7) to provide lift force for the main body (1);

when the automobile lands and runs on the ground, the pair of foldable front wings (3) and the pair of foldable main wings (4) are folded to be perpendicular to the automobile body, and meanwhile, a plurality of small wheels (12) arranged at the edges of the foldable front wings (3) and the foldable main wings (4) extend out to support the automobile body to run on the ground;

in the process, a pair of tiltable coaxial reverse rotation double-rotor systems (6) provides forward thrust, backward reverse thrust and rolling force for the main body (1).

2. Urban air-craft according to claim 1, characterized in that the front wing (2) is a polygonal frame structure, designed to support the foldable front wing (3) while being protected around the tiltable coaxial contra-rotating twin-rotor system (6), and in that the polygonal frame structure cross section is an aerofoil profile.

3. The city aerocar according to claim 1, wherein said pair of tiltable coaxial contra-rotating dual-rotor systems (6) are respectively disposed at both ends of a rotating shaft (10) located at the lower part of the front body, the rotating shaft (10) is fixed at the lower part of the front body by two ball bearings (33) symmetrically disposed on the shaft, and a driving rotary gear (34) is disposed between the two ball bearings (33) on the shaft; the rotating shaft (10) is driven to rotate by a driving system.

4. The city air-flying automobile as claimed in claim 3, wherein the driving system comprises a double-shaft motor (32) arranged at the lower part of the front fuselage, and a pair of gears (35) arranged on torque output shafts at two ends of the motor, which are meshed with the driving rotating teeth (34); the double-shaft motor (32) drives the rotating shaft (10) to rotate in forward/reverse directions so as to change the thrust direction of the tiltable coaxial reverse rotation double-rotor system (6) into forward thrust or backward reverse thrust, and when the automobile is lifted, the axis of the tiltable coaxial reverse rotation double-rotor system (6) is upward.

5. Urban air-borne vehicle according to claim 1, characterized in that said main coaxial contra-rotating twin-rotor system (7) comprises an upper and a lower set of coaxial rotor systems with opposite directions of rotation, wherein the upper rotor system comprises a set of upper rotor blades (13) arranged laterally to an upper rotor mast (19) driven in rotation by an upper motor (15) fixed to an upper motor-supporting stator (17); the lower rotor system comprises a set of lower rotor blades (14) arranged laterally to a lower rotor mast (20) which is driven in rotation by a lower motor (16) fixed to a lower motor support stator (18); the support stator is fixed on the rear machine body.

6. The city air-borne bus according to claim 1, wherein the folding structure of the foldable front wing (3) and the foldable main wing (4) comprises retractable cylinders respectively arranged in the fixed wing (23) and the foldable wing (24), and a telescopic buffer gas spring (27) arranged between the outer sides of the fixed wing (23) and the foldable wing (24), and the foldable wing (24) forms a stable triangular structure for supporting after being folded relative to the fixed wing (23); the folding wing (24) is a foldable front wing (3) or a foldable main wing (4), and the fixed wing (23) is a front wing (2) or a rear fuselage.

7. Urban air-craft according to claim 6, characterized in that the folding wing (24) is hinged with respect to the part folded against the fixed wing (23).

8. Urban air-craft according to claim 1, characterized in that said vertical fin (5) is of V-shaped configuration;

the vertical fin (5) is provided with a deflectable control surface (11) to provide pitching and yawing control moment for the automobile flight.

9. The city air-borne vehicle according to claim 1 or 8, characterized in that the power of the various components of the vehicle is provided by a power battery system, which comprises a power battery I area (28) arranged on the foldable front wing (3), a power battery II area (29) arranged on the foldable main wing (4), a power battery III area (30) arranged at the rear part of the main body and a power battery IV area (31) arranged on the vertical tail (5).

10. The city air-borne vehicle according to claim 9, wherein the power battery is a rechargeable lithium ion battery or a hydrogen fuel cell.