CN114104280A

CN114104280A - Safe and efficient electric vertical take-off and landing aircraft

Info

Publication number: CN114104280A
Application number: CN202111541901.8A
Authority: CN
Inventors: 吴田丰
Original assignee: Changzhou Jinzhi Machinery Co ltd
Current assignee: Changzhou Jinzhi Machinery Co ltd
Priority date: 2021-04-09
Filing date: 2021-12-16
Publication date: 2022-03-01

Abstract

The invention belongs to the technical field of aviation, and particularly relates to a safe and efficient electric vertical take-off and landing aircraft which comprises an aircraft body, a first driving part, a second driving part, a main wing, an aileron, two front landing gears, an empennage and a rear landing gear.

Description

Safe and efficient electric vertical take-off and landing aircraft

Technical Field

The invention belongs to the technical field of aircrafts, and particularly relates to a safe and efficient electric vertical take-off and landing aircraft.

Background

With the development of economy and the progress of science and technology, automobile civilization has developed to the tripod period, so a series of traffic problems are brought, meanwhile, the sea level is raised due to the climate warming problem caused by the rapid development of human civilization and the unreasonable utilization of resources, and a novel city concept is proposed. The method provides opportunity and power for the design and development of the urban aircraft. The development of the urban aircraft becomes another significant revolution in the development history of the trip modes of human beings.

Aircraft construction must be on a safety basis, which is the result of human flight history summaries. On the basis, the urban aircraft must give priority to flexibility and high efficiency, and the urban manned aircraft currently under development mainly has the following defects: firstly, the safety is not high, and secondly the maneuverability of the aircraft is not sufficient and the flying speed is low.

Disclosure of Invention

The invention provides a safe and efficient electric vertical take-off and landing aircraft, and aims to solve the problem that the existing aircraft is low in safety.

The invention is realized in this way, and provides a safe and efficient electric vertical take-off and landing aircraft, which comprises an aircraft body, wherein a personnel cabin is arranged at the front end of the aircraft body;

the first driving component comprises two groups of first driving devices for driving the aircraft to take off, land and fly, and the first driving devices are fixedly connected to the front part of the aircraft body and symmetrically arranged at two sides of the personnel cabin; the first driving device ensures the take-off and landing or the flight of the aircraft by changing the direction of the driving force;

the second driving component comprises two groups of second driving devices for driving the aircraft to take off, land and fly, and the second driving devices are fixedly connected to the rear part of the aircraft body and symmetrically arranged on two sides of the rear part of the aircraft body; the second driving device ensures the take-off and landing or the flight of the aircraft by changing the direction of the driving force;

the two main wings are of a forward-swept structure and are symmetrically and foldably connected to two sides of the fuselage;

the two front landing gears are respectively and symmetrically arranged on the outer sides of the two main wings; so that when the aircraft is landing, the main wings fold down and the nose landing gear contacts the ground;

the tail wing is vertically hinged to the rear part of the fuselage, and the left and right flying headings are changed by adjusting the deflection of the tail wing; and

a rear landing gear connected to a lower portion of the tail wing;

when the aircraft flies ahead or takes off and lands, the main wings extend outwards or fold downwards.

The invention provides a safe and efficient electric vertical take-off and landing aircraft, wherein a main wing is of a forward-swept upper single-wing foldable structure.

The invention provides a safe and efficient electric vertical take-off and landing aircraft, wherein a nose landing gear is arranged at the outer side end of a main wing.

The invention provides a safe and efficient electric vertical take-off and landing aircraft, wherein a first driving device is a first inclinable ducted lift fan, the air outlet direction of the first inclinable ducted lift fan inclines towards the rear part of an aircraft body when taking off or landing, the included angle between the first inclinable ducted lift fan and the vertical direction is more than or equal to 5 degrees and less than or equal to 15 degrees, and the air outlet direction of the first inclinable ducted lift fan is consistent with the running direction when flying normally.

The invention provides a safe and efficient electric vertical take-off and landing aircraft, wherein the first driving part further comprises two groups of first motors, and the two groups of first motors respectively drive two groups of first inclinable ducted lift fans.

The invention provides a safe and efficient electric vertical take-off and landing aircraft, wherein a second driving device is a second inclinable ducted lift fan and is used for controlling the aircraft to pitch in a normal flight state; and when taking off or landing, the air outlet direction of the second tiltable ducted lift fan inclines towards the front part of the aircraft body, and the included angle between the second tiltable ducted lift fan and the vertical direction is more than or equal to 5 degrees and less than or equal to 15 degrees.

The invention provides a safe and efficient electric vertical take-off and landing aircraft, wherein the second driving part further comprises two groups of second motors, and the two groups of second motors drive two groups of second inclinable ducted lift fans.

The invention provides a safe and efficient electric vertical take-off and landing aircraft, wherein a first driving part and a second driving part are arranged on the aircraft in an inverted triangle mode in a horizontal plane.

The invention provides a safe and efficient electric vertical take-off and landing aircraft, which further comprises two ailerons, wherein the two ailerons are connected to the front ends of the main wings in a foldable manner; the function is as follows: 1. when taking off, the aircraft is folded inwards, namely folded to one side of the aircraft body, so that high-speed airflow flows towards the aircraft body, thereby assisting in taking off; 2. during normal flight, the ailerons are used to control the pitch and yaw of the aircraft.

The power system consisting of the forward-swept type foldable upper single-wing type pneumatic layout and the ducted lift fan driven by the direct-current permanent magnet motor and the tiltable ducted vector thrust structure are the biggest characteristics of the invention. The contents of these technical features are explained in detail below.

The invention has the beneficial effects that: the invention provides a safe and efficient electric vertical take-off and landing aircraft which comprises:

1. the forward swept main wing has the following advantages:

the structure is advantageous: the forward swept wing structure can ensure better connection between the wings and the fuselage, and can ensure that the airplane has very good pneumatic performance when flying at low speed, thereby greatly improving the maneuverability of the airplane in an elevation angle state.

The lift force advantage is as follows: compared with the sweepback wing aircraft with the same wing area, the sweepback wing aircraft has larger lift force, thereby reducing the wing area of the aircraft and reducing the head-on resistance and the structural weight of the aircraft; the aircraft trim resistance is reduced, and the range of the aircraft is enlarged; and the low-speed maneuvering performance of the airplane is improved.

The control advantages are as follows: the forward swept wing structure can improve the controllability of the airplane during low-speed flight, improve the aerodynamic efficiency in all flight states, reduce the stall speed and ensure that the airplane is not easy to enter a helix, thereby greatly improving the safety and reliability of the airplane.

2. The main wing has the following advantages by adopting the upper single wing layout:

the structure is advantageous: the upper single wing can be integrally formed, and is connected with the fuselage without a fuselage wing box, so that the structural strength is high. Pneumatic advantages: the upper surface of the upper single wing and the upper surface of the fuselage are basically flush, and the low-pressure areas of the flow field of the airplane do not interfere with each other and are not easy to separate. The natural wing has the advantage of body-wing fusion, and the configuration with high lift-drag ratio is easy to form. The stability advantage is as follows: the gravity center of the upper single-wing aircraft is arranged below the wing, the distance between the gravity center and the lift center is long, the natural rolling stability can be achieved, and the aircraft has strong automatic recovery flight attitude stability.

3. The main wing has the advantages brought by adopting a lower folding form:

the structure is advantageous: the airplane body is supported by combining with the rear wheel to form a rear three-point undercarriage, so that the airplane can move slowly on the paved ground, the width of the airplane in the landing ground state is greatly reduced, and the airplane can flexibly meet the landing requirements of more fields. Pneumatic advantages: after the main wings on the two sides are folded downwards, the main wings, the middle cabin and the inward folded auxiliary wings form a semi-closed structure, so that when the high-speed airflow is sprayed out of the front duct, the high-speed airflow is wrapped to form a high-pressure air cushion, and the airplane can be lifted and landed efficiently.

4. The provision of foldable flaps has the advantages: when taking off, the aircraft is folded inwards, namely folded to one side of the aircraft body, so that high-speed airflow flows towards the aircraft body, thereby assisting in taking off; during normal flight, the ailerons are used to control the pitch and yaw of the aircraft.

5. The first driving device and the second driving device adopt the advantages of the ducted lift fan:

the safety advantage is that: the fan blades rotating at high speed are wrapped by the outer duct, and the safety is higher than that of an open rotor wing. Pneumatic advantages: at certain diameters, ducted fans can provide greater thrust while better facing complex airflow environments.

The structure is advantageous: it is particularly suited to complex urban environments due to its greater safety and efficiency, compactness, and lower noise.

6. The second driving device adopts the advantages of tilting vector thrust:

the structure is advantageous: by using vector thrust, the horizontal tail wing can be eliminated, the operating mechanism is reduced, the complexity is reduced, and the airplane efficiency is improved.

Pneumatic advantages: after the horizontal tail wing is eliminated, the resistance is reduced, and the flying speed is improved.

The design takes the safest fixed wing aircraft structure as the basis, and is matched with the efficient and compact ducted lift fan, so that the safe, efficient and flexible aircraft is formed. The flexible vertical take-off and landing low-energy-consumption high-speed flight in the urban environment can be realized, so that a choice is added for solving the problem of unsmooth point-to-point traffic of urban traffic.

Drawings

FIG. 1 is a top view of a safe and efficient electric VTOL aerial vehicle of the present invention during flight;

FIG. 2 is a right side view of a safe and efficient powered VTOL aerial vehicle of the present invention during takeoff or landing;

FIG. 3 is a front view of the safe and efficient electric VTOL aerial vehicle of the present invention during flight;

FIG. 4 is a front view of a safe and efficient powered VTOL aerial vehicle of the present invention during takeoff or landing;

fig. 5 is a schematic structural diagram of a safe and efficient electric VTOL (vertical take-off and landing) aircraft comprising two first tiltable ducted lift fans.

Wherein: a body 10; a personnel space 11; a main wing 20; a first driving device 31; a second driving device 41; a nose landing gear 50; a vertical tail 60; a rear landing gear 70; the flap 80.

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 present invention, it should be noted that the terms "upper", "lower", "left", "right", "vertical", "sealing liquid level", "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 usually place when in use, and are only used for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," "fourth," "fifth," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "connected," and "mounted" 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 an intermediate medium, or they may be connected internally between two members. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Referring to fig. 1 to 5, the present invention provides a safe and efficient electric vertical take-off and landing aircraft, which includes a fuselage 10, a first driving part, a second driving part, two main wings 20, two front landing gears 50, a tail wing 60, a rear landing gear 70, and an aileron 80; wherein, the front end of the fuselage 10 is provided with a personnel cabin 11; the first driving component comprises two groups of first driving devices 31 for driving the aircraft to take off and land and two groups of first motors for driving the first driving devices 31, wherein the first driving devices 31 are first tiltable ducted lift fans which are fixedly connected to the front part of the aircraft body 10 and symmetrically arranged at two sides of the personnel cabin 11, when the aircraft takes off or lands, the air outlet direction of the first tiltable ducted lift fans inclines towards the rear part of the aircraft body 10, the included angle between the first tiltable ducted lift fans and the vertical direction is more than or equal to 5 degrees and less than or equal to 15 degrees, when the aircraft normally flies (namely, under other states except take-off and landing states), the air outlet direction of the first tiltable ducted lift fans is consistent with the movement direction, and the aircraft pitching is controlled by controlling the air direction of the first tiltable ducted lift fans; the second driving component comprises two groups of second driving devices 41 for driving the aircraft to take off, land and fly and two groups of second motors for driving the second driving devices 41, wherein the second driving devices 41 are second tiltable ducted lift fans which are fixedly connected to the rear part of the fuselage 10 and symmetrically arranged on two sides of the rear part of the fuselage 10; when taking off or landing, the air outlet direction of the second tiltable ducted lift fan inclines towards the front part of the aircraft body 10, the included angle between the second tiltable ducted lift fan and the vertical direction is more than or equal to 5 degrees and less than or equal to 15 degrees, and when the aircraft normally flies, the pitching of the aircraft is controlled by controlling the air direction of the second tiltable ducted lift fan; the main wings 20 are of a forward sweep type upper single wing foldable structure downwards, and the two main wings 20 are symmetrically and foldably connected to two sides of the fuselage 10; two nose landing gears 50, i.e., nose landing gears, are symmetrically disposed on the two main wings 20, respectively; referring to FIG. 4, when the aircraft is landing, the main wings 20 fold down into the aft landing gear 50 to contact the ground; the rear wing 60 is vertically hinged at the rear of the body 10, and the left and right directions are controlled by changing the position of the rear wing 60; wherein the tail wing 60 is hinged with the rear part of the fuselage 10 through an axle, the rear landing gear 70, namely the rear landing gear, is connected with the lower part of the tail wing 60, the two ailerons 80 are connected with the front ends of the main wings 20 in a folding way, and when taking off, the ailerons 80 are folded inwards towards the fuselage 10, and form an airflow channel with the fuselage 10 and the main wings 20 to assist taking off.

Referring to fig. 5, when each set of first driving devices 31 for driving the aircraft to take off and land includes 2 first tiltable ducted lift fans, power redundancy can be increased, and safety performance is higher.

Referring to fig. 2 and 4, the aircraft takes off or lands in the same airflow direction, and during landing, the airflow gradually decreases, and during taking off, the airflow gradually increases; taking take-off as an example, the following is illustrated: when the aircraft takes off, the main wings 20 are folded downwards, the ailerons 80 are folded inwards towards the fuselage 10 to form an airflow channel, wherein the airflow direction driven by the first driving device 31 is shown as A in the drawing, and the airflow direction driven by the second driving device 41 is shown as B in the drawing, when the aircraft takes off, a plurality of ducted lift fans simultaneously wind downwards, the front downwash and the main wings 20 folded downwards on the two sides of the fuselage are in a semi-enclosed state to form a semi-closed state of the fuselage ground of the downfolded wing, and the front fan and the rear fan spray high-speed downwash airflow downwards and are launched upwards by the ground to form a fountain effect, and the fountain effect acts on the lower surface of the fuselage to form an upward lift. The ground effect is utilized to generate the reflection lift force, the high-speed airflow is fully utilized to do work, the power of the motor can be reduced, and the vertical takeoff is easy to realize.

The product of the invention functionally belongs to a vertical take-off and landing type, and is a multi-type multifunctional aircraft. The concrete description has the following characteristics: the product lifting drive comes from the first and second tiltable ducted lift fans. The aircraft linear flight power comes from a plurality of groups of inclinable ducted lift fans, and the lift comes from the main wing 20 after being unfolded. The fan is driven by lithium batteries and adopts a plurality of groups of ducted fans with high lift force. The fan comprises a plurality of fan blade fixed-distance fans, and a plurality of high-power motors are used for driving the ducted lift fan. The motors are arranged on the machine body in an inverted triangle manner, wherein a plurality of motors are fixed with the front end of the machine body, and the rear end motor is arranged on the rotary fulcrum shaft. The second tiltable ducted lift fan can be required to wind downwards or backwards according to different working conditions. When the aircraft is lifted, the plurality of ducted lift fans simultaneously exhaust air downwards, the front downwash and the main wings 20 on the two sides of the aircraft body are in a semi-surrounding state, a semi-closed state of the ground of the aircraft body of the downward-folded aircraft wing is formed, high-speed airflow generates a high-pressure air cushion between the lower part of the aircraft body and the ground by utilizing the ground effect, the high-speed airflow is fully utilized to do work, the aircraft body generates supporting force which is beneficial to lifting, the power of a motor is reduced, and the lifting is easy to realize. When the vertical lift reaches a certain height, the main wings 20 on both sides are unfolded upwards. The second inclinable ducted lift fan propels backward at 45 degrees, so that the machine slowly advances forward. In the process, the rotation speed of the first two groups of ducted fans is slowly reduced, when the speed of the aircraft rises to the point that the main wings 20 generate enough lift force, the first tiltable ducted lift force fan can reduce power output, and the second tiltable ducted lift force fan enters backward air outlet to generate thrust, so that the aircraft enters a pure forward flight state. When the aircraft is about to land, it needs to decelerate to a proper speed and reduce a certain height, at the same time, the first inclinable ducted lift fan is turned on to generate a proper amount of downward thrust, and at the same time, the second inclinable ducted lift fan rotates downward at a slow speed from a horizontal backward air-out state to generate a downward thrust, and the second inclinable ducted lift fan and the first inclinable ducted lift fan together overcome the problem of insufficient lift of the main wing 20. When lowered to a small ground clearance, the main wings 20 fold down, forming a rear three-point landing gear support aircraft with the fuselage 10 and the rear landing gear 70. The paving ground is driven by the rear wheel when moving slowly.

The present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The utility model provides a safe high-efficient electronic VTOL aircraft which characterized in that: comprises that

The device comprises a machine body (10), wherein a personnel cabin (11) is arranged at the front end of the machine body (10);

the first driving component comprises two groups of first driving devices (31) for driving the aircraft to take off and land, and the first driving devices (31) are fixedly connected to the front part of the aircraft body (10) and symmetrically arranged on two sides of the personnel cabin (11); the first driving device (31) ensures the take-off and landing or the flight of the aircraft by changing the direction of the driving force;

the second driving component comprises two groups of second driving devices (41) for driving the aircraft to take off, land and fly, wherein the second driving devices (41) are fixedly connected to the rear part of the aircraft body (10) and symmetrically arranged on two sides of the rear part of the aircraft body (10); the second driving device (41) ensures the take-off and landing or the flight of the aircraft by changing the direction of the driving force;

the two main wings (20), the main wings (20) are of a sweepforward structure, and the two main wings (20) are symmetrically and foldably connected to two sides of the fuselage (10);

the two front landing gears (50), the two front landing gears (50) are respectively and symmetrically arranged on the two main wings (20); such that when the aircraft is landing, the main wings (20) fold down the nose landing gear (50) into contact with the ground;

a tail wing (60), the tail wing (60) being vertically hinged to the rear of the fuselage (10) such that the position of the tail wing (60) is adjusted to change the left and right course of flight; and

a rear landing gear (70), the rear landing gear (70) being connected to a lower portion of the tail wing (60);

when the aircraft takes off or lands, the main wings (20) extend outwards or fold downwards.

2. A safe and efficient electric vertical take-off and landing aircraft as claimed in claim 1, wherein: the wing-shaped structure also comprises two ailerons (80), and the two ailerons (80) are connected at the front end of the main wing (20) in a foldable way.

3. A safe and efficient electric vertical take-off and landing aircraft as claimed in claim 1, wherein: the main wing (20) is of a forward-swept upper single-wing foldable structure.

4. A safe and efficient electric vertical take-off and landing aircraft as claimed in claim 1, wherein: the nose landing gear (50) is disposed at the outboard end of the main wing (20).

5. A safe and efficient electric vertical take-off and landing aircraft as claimed in claim 1, wherein: the first driving device (31) is a first tiltable ducted lift fan, when taking off or landing, the air outlet direction of the first tiltable ducted lift fan inclines towards the rear part of the aircraft body (10), the included angle between the first tiltable ducted lift fan and the vertical direction is more than or equal to 5 degrees and less than or equal to 15 degrees, and when flying normally, the air outlet direction of the first tiltable ducted lift fan is consistent with the running direction.

6. A safe and efficient electric VTOL aerial vehicle according to claim 5, wherein: the first driving part further comprises two groups of first motors, and the two groups of first motors respectively drive the two groups of first inclinable ducted lift fans.

7. A safe and efficient electric vertical take-off and landing aircraft as claimed in claim 6, wherein: the second driving device (41) is a second tiltable ducted lift fan and is used for controlling the pitching of the aircraft in a normal flight state; and when taking off or landing, the air outlet direction of the second tiltable ducted lift fan inclines towards the front part of the machine body (10), and the included angle between the second tiltable ducted lift fan and the vertical direction is more than or equal to 5 degrees and less than or equal to 15 degrees.

8. A safe and efficient electric vtol aircraft as claimed in claim 7, wherein: the second driving part also comprises two groups of second motors, and the two groups of second motors drive two groups of second inclinable ducted lift fans.

9. A safe and efficient electric vtol aircraft as claimed in claim 8, wherein: the first drive member and the second drive member are arranged in the aircraft in an inverted triangular form in a horizontal plane.