CN221067698U - Electric vertical take-off and landing aircraft - Google Patents

Abstract

The utility model relates to an electric vertical take-off and landing aircraft, which comprises a fuselage body, a landing gear, a horn and a propeller, wherein the propeller is connected around the fuselage body in a foldable manner through the horn, and the propeller is in transmission connection with flight driving equipment; the bottom of the body forms a hull, and the tail of the body is provided with water propulsion equipment; the landing gear can be retracted in the machine body, and a machine wheel on the landing gear is in transmission connection with land driving equipment; the flying driving device, the water propulsion device and the land driving device are all motors. The electric vertical take-off and landing aircraft realizes navigation on the water surface through the water propulsion equipment; the landing gear is driven by the land driving equipment to realize the running on land; the flight driving device drives the propeller to rotate so as to realize the air flight; can adapt to three use scenes of water, land and air, effectively improve the multi-environment adaptability of the electric vertical take-off and landing aircraft.

Description

Electric vertical take-off and landing aircraft

Technical Field

The utility model relates to the technical field of aircrafts, in particular to an electric vertical take-off and landing aircraft.

Background

EVTOL (electricVerticalTakeoffandLanding, electric vertical takeoff and landing aircraft) has attracted extensive attention including aerospace businesses, automotive industries, transportation industries, governments, military and academia. eVTOL future potential applications relate to various scene modes such as urban passenger transport, regional passenger transport, freight transport, personal aircrafts, emergency medical services and the like, and the most outstanding advantages of the aircraft are energy conservation, environmental protection, high efficiency, low energy consumption, realization of near zero emission, low noise and vibration level, good riding comfort and the like, and are real environment-friendly aircrafts.

At present, most eVTOL in the prior art cannot land on water, cannot run on water, and generally runs on the ground in a separated mode or is transported by adding a transport vehicle, so that eVTOL in the prior art is single in function and poor in environmental adaptability.

Disclosure of utility model

In order to solve the technical problems, the utility model provides an electric vertical take-off and landing aircraft, which can improve the multi-environment adaptability of the electric vertical take-off and landing aircraft.

In order to achieve the above purpose, the utility model provides an electric vertical take-off and landing aircraft, which comprises a fuselage body, a landing gear, a propeller and a horn, wherein the propeller is connected around the fuselage body in a foldable manner through the horn, and the propeller is in transmission connection with flight driving equipment; the bottom of the body forms a hull, and the tail of the body is provided with water propulsion equipment; the landing gear can be retracted in the machine body, and a machine wheel on the landing gear is in transmission connection with land driving equipment; the flying driving device, the water propulsion device and the land driving device are all motors.

In one embodiment of the utility model, the horn comprises a mounting base and a folding arm, wherein the mounting base is connected to the body, one end of the folding arm is connected with the mounting base in a folding way, and the other end of the folding arm is connected with the propeller.

In one embodiment of the utility model, at least four horn are provided, at least two flight driving devices and two propellers are provided on each horn, one propeller corresponds to one flight driving device, the horn at the front part of the fuselage body is folded towards the tail part of the fuselage body, the horn at the tail part of the fuselage body is folded towards the head part of the fuselage body, and the horn is not interfered with each other before and after folding.

In one embodiment of the utility model, the projection of the horn positioned at the front part of the fuselage body on the reference surface is a first projection, the projection of the horn positioned at the tail part of the fuselage body on the reference surface is a second projection, a preset distance is arranged between the first projection and the second projection along the vertical direction, and the reference surface is a plane perpendicular to the direction of the front part of the fuselage body pointing to the tail part.

In one embodiment of the utility model, the landing gear comprises one first landing gear arranged in front of the bottom of the fuselage body and two second landing gears arranged behind the bottom of the fuselage body, the two second landing gears being symmetrically arranged about the fuselage body, the first landing gear and the second landing gear forming a three-point landing gear.

In one embodiment of the present utility model, the wheels on the first landing gear are follower wheels, the wheels on the second landing gear are in transmission connection with the land driving device, and the wheels on the second landing gear are driving wheels.

In one embodiment of the utility model, the body is provided with a containing space, and the landing gear is retracted in the containing space.

In one embodiment of the utility model, the landing gear is housed within the fuselage body when the electric vertical takeoff and landing aircraft is on the surface, and the horn is folded around the fuselage body or the horn is unfolded around the fuselage body.

In one embodiment of the utility model, the landing gear is placed outside the fuselage body and the horn is folded around the fuselage body while the electric vertical takeoff and landing aircraft is traveling on land.

In one embodiment of the utility model, the landing gear is housed within the fuselage body and the horn is deployed around the fuselage body when the electric vertical takeoff and landing aircraft is flying in the air.

Compared with the prior art, the technical scheme of the utility model has the following advantages:

According to the electric vertical take-off and landing aircraft, navigation of the electric vertical take-off and landing aircraft on the water surface is realized through the water propulsion equipment and/or the propeller; the landing gear is driven by the land driving equipment to realize the running of the electric vertical take-off and landing aircraft on land; the flight driving device drives the propeller to rotate so as to realize the air flight of the electric vertical take-off and landing aircraft; therefore, the electric vertical take-off and landing aircraft can adapt to three use scenes of water, land and air, and effectively improves the multi-environment adaptability of the electric vertical take-off and landing aircraft.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings required for the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present utility model, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a front view of an extended configuration of an electric vertical takeoff and landing aircraft of the present utility model;

FIG. 2 is a side view of an extended configuration of the electric vertical takeoff and landing aircraft of the present utility model;

FIG. 3 is a top view of the deployed configuration of the electric vertical takeoff and landing aircraft of the present utility model;

FIG. 4 is a front view of a folding structure of the electric vertical takeoff and landing aircraft of the present utility model;

FIG. 5 is a side view of a folding structure of the electric vertical takeoff and landing aircraft of this utility model;

Fig. 6 is a top view of the folding structure of the electric vertical takeoff and landing aircraft of the present utility model.

Description of the specification reference numerals:

1. A fuselage body; 2. landing gear; 3. a propeller; 4. a horn; 5. a mounting base; 6. a folding arm; 7. a first landing gear; 8. a second landing gear; 9. an accommodating space; 10. a cockpit; 11. a cabin; 12. and (5) an equipment cabin.

Detailed Description

In order to make the objects, technical solutions and advantages of the present utility model more apparent, the technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model. It will be apparent that the described embodiments are only some, but not all, embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

Referring to fig. 1 to 6, the electric vertical take-off and landing aircraft comprises a fuselage body 1, a landing gear 2, a horn 4 and a propeller 3, wherein the propeller 3 is connected around the fuselage body 1 in a foldable manner through the horn 4, and the propeller 3 is in transmission connection with flight driving equipment; the bottom of the body 1 forms a hull, and the tail of the body 1 is provided with water propulsion equipment; the landing gear 2 can be retracted and released in the machine body 1, and a wheel on the landing gear 2 is in transmission connection with land driving equipment; the flying driving device, the water propulsion device and the land driving device are all motors.

In order to improve the adaptability of an electric vertical take-off and landing aircraft, the application provides an amphibious electric vertical take-off and landing aircraft, which comprises a fuselage body 1, a landing gear 2 and a propeller 3. The bottom of the body 1 forms a hull, the tail of the body 1 is provided with water propulsion equipment, the body 1 floats on the water surface through the hull formed at the bottom of the body, the landing gear 2 is retracted, the landing gear 2 is accommodated in the body to reduce water resistance, the electric vertical take-off and landing aircraft is pushed to advance through the water propulsion equipment arranged at the tail of the body 1, meanwhile, the folding or unfolding of the horn can be selected according to the actual running space and the water surface condition, the air resistance of the horn 4 during the folding can be reduced, and the lifting force can be provided through the propeller 3 during the unfolding of the horn 4 to reduce the water resistance, so that the sailing of the electric vertical take-off and landing aircraft on the water surface is realized; when the marine propulsion system is sailing on water, the marine propulsion equipment and the propeller can be used independently or in combination. The landing gear 2 is used for realizing the running of the electric vertical take-off and landing aircraft on the ground, specifically, the landing gear 2 can be retracted in the body 1, and when the electric vertical take-off and landing aircraft sails on the water surface or flies in the sky, the landing gear 2 needs to be accommodated in the body 1 (specifically, the accommodating space 9); when the electric vertical take-off and landing aircraft needs to travel on land, the landing gear 2 needs to be opened outside the body 1 (specifically the accommodating space 9), the land driving equipment is in transmission connection with the wheels on the landing gear 2, and the wheels on the landing gear 2 are driven by the land driving equipment, so that the electric vertical take-off and landing aircraft can travel on land. The fuselage body 1 is provided with the horn 4, the propeller 3 is connected around the fuselage body 1 in a foldable way through the horn 4, and as shown in figures 4, 5 and 6, when the electric vertical take-off and landing aircraft runs on land or sails on water, the propeller 3 can be folded around the fuselage body 1 through the horn 4; when the electric vertical take-off and landing aircraft needs to fly in the air, the landing gear 2 is retracted, the propeller 3 is unfolded around the airframe body 1 through the horn 4, as shown in fig. 1, 2 and 3, the propeller 3 is in transmission connection with the flight driving equipment, the propeller 3 is driven to rotate through the flight driving equipment, the propeller 3 provides lift force, and the forward flight and the turning are realized by controlling the rotating speeds of the propellers 3 with different directions, so that the air flight of the electric vertical take-off and landing aircraft is realized. In addition, the electric vertical take-off and landing aircraft can be switched between two control modes of unmanned operation and unmanned operation, and not only can the electric vertical take-off and landing aircraft be controlled by sending a radio signal through the ground station, but also a control lever and a steering wheel can be controlled manually by a driver. An electric vertical take-off and landing aircraft is provided with an emergency complete machine parachute, when the propeller 3 fails, the parachute is thrown out quickly by virtue of a rocket, and the parachute is opened until the aircraft lands safely by virtue of the descending speed, so that the safety is improved. The flight driving equipment, the water propulsion equipment and the land driving equipment are all motors, so that the energy-saving and environment-friendly device is energy-saving, high in efficiency and low in energy consumption, low-carbon emission is realized, the noise and vibration level is very low, and the riding comfort is good. Among them, the flying drive device is preferably a brushless motor.

According to the electric vertical take-off and landing aircraft, navigation of the electric vertical take-off and landing aircraft on the water surface is realized through the water propulsion equipment and/or the propeller; the landing gear 2 is driven by land driving equipment to realize the running of the electric vertical take-off and landing aircraft on land; the flight driving device drives the propeller 3 to rotate so as to realize the air flight of the electric vertical take-off and landing aircraft; therefore, the electric vertical take-off and landing aircraft can adapt to three use scenes of water, land and air, and effectively improves the environment adaptability of the electric vertical take-off and landing aircraft.

In one embodiment, the arm 4 includes a mounting base 5 and a folding arm 6, the mounting base 5 is connected to the body 1, one end of the folding arm 6 is connected to the mounting base 5 in a folding manner, and the other end of the folding arm 6 is connected to the propeller 3.

In order to reduce the air resistance of the electric vertical take-off and landing aircraft when the aircraft is sailing on water or on land, the arm 4 is connected to the fuselage body 1 in a foldable manner. Specifically, the horn 4 includes a mounting base 5 and a folding arm 6, as shown in fig. 3 and 5, the mounting base 5 is attached to the fuselage body 1, and then the folding arm 6 is foldably attached to the mounting base 5 to achieve the attachment of the folding arm 6 to the fuselage body 1 through the mounting base 5. The other end of the folding arm 6 which is not connected with the mounting base 5 is connected with the propeller 3, the propeller 3 is provided with a power source by a flight driving device, and the lifting force generated by the propeller 3 drives the whole electric vertical take-off and landing aircraft to fly in the air through the folding arm 6, the mounting base 5 and the fuselage body 1 in sequence. The foldable horn 4 can be folded around the body 1 when the electric vertical take-off and landing aircraft sails on water or runs on land, so that the windward area of the horn 4 is reduced, the air resistance when the electric vertical take-off and landing aircraft sails on water or runs on land is reduced, and the adaptability of the electric vertical take-off and landing aircraft is improved. Furthermore, the foldable horn 4 facilitates transport and storage of the electric vertical takeoff and landing aircraft.

In one embodiment, at least four horn 4 are disposed, at least two flight driving devices and two propellers 3 are disposed on each horn 4, one propeller 3 corresponds to one flight driving device, the horn 4 located at the front part of the fuselage body 1 is folded towards the tail part of the fuselage body 1, the horn 4 located at the tail part of the fuselage body 1 is folded towards the front part of the fuselage body 1, and the horns 4 do not interfere with each other before and after folding.

At least four of the arms 4 are provided, preferably, as shown in fig. 3, four of the arms 4 are provided; at least two propellers 3 are arranged on each horn 4, preferably, as shown in fig. 3, two propellers are arranged on each horn 4, the electric vertical take-off and landing aircraft forms a four-axis eight-propeller configuration, and the four-axis eight-propeller aircraft is small and flexible in shape and strong in adaptability. Further, because the horn 4 is connected around the fuselage body 1 in a foldable manner, the horn located at the front part of the fuselage body 1 is folded towards the tail part of the fuselage body 1, the horn located at the tail part of the fuselage body 1 is folded towards the front part of the fuselage body 1, and the horns 4 are not interfered with each other before and after being folded, so that the air resistance of the electric vertical take-off and landing aircraft during water navigation or land traveling can be reduced, and the adaptability of the electric vertical take-off and landing aircraft is improved. The horn 4 is designed with two clamping positions, and when the ground is parked, the horn 4 is positioned at the retracted clamping position, and a limiting pin is manually inserted, so that the horn 4 is prevented from being abnormal in severe weather such as strong wind; before taking off in the air flight mode, the limiting pin is manually pulled out, the electric push rod of the arm 4 is controlled to be unfolded to be clamped by the remote controller, and the limiting pin is manually inserted. In the land walking and water navigation modes, the load of the horn 4 is small, so that the electric push rod of the horn 4 is only required to be remotely controlled to a proper unfolding angle, and the electric push rod is utilized to be mechanically self-locked without inserting a limiting pin.

In one embodiment, the projection of the horn 4 located at the front part of the body 1 on the reference plane is a first projection, the projection of the horn 4 located at the tail part of the body 1 on the reference plane is a second projection, a preset distance is set between the first projection and the second projection along the vertical direction, and the reference plane is a plane perpendicular to the direction of pointing the front part to the tail part of the body 1.

A plane perpendicular to the direction in which the front portion of the fuselage body 1 points to the tail is defined as a reference plane, and the direction in which the front portion of the fuselage body 1 points to the tail, that is, the axial direction of the fuselage body 1 in this direction. The projection of the horn positioned at the front part of the body 1 on the reference plane is a first projection, the projection of the horn positioned at the tail part of the body 1 on the reference plane is a second projection, and the first projection and the second projection have preset distances along the vertical direction. Because the direction of the front part of the fuselage body 1 pointing to the tail part is along the horizontal direction, the reference plane perpendicular to the direction is along the vertical direction, the first projection and the second projection are along the preset distance in the vertical direction, and the preset distance exists between the horn at the front part of the fuselage body 1 and the horn at the tail part of the fuselage body 1 in the vertical direction, therefore, the horn 4 is not only arranged on the fuselage body 1 front and back, but also arranged in a staggered manner up and down, as shown in fig. 5, after the horn 4 is folded, the front part of the fuselage body 1 is positioned below the tail horn of the fuselage body 1, and the horn at the front part of the fuselage body 1 is staggered up and down with the horn at the tail part of the fuselage body 1, so that interference is prevented when the fuselage body is folded, and the arrangement mode can enable the structure of the electric vertical take-off and landing aircraft to be more compact, and the adaptability of the electric vertical take-off and landing aircraft is improved.

In one embodiment, the landing gear 2 includes a first landing gear 7 and two second landing gears 8, where the first landing gear 7 is disposed in front of the bottom of the fuselage body 1, the two second landing gears 8 are disposed behind the bottom of the fuselage body 1, the two second landing gears 8 are symmetrically disposed with respect to the fuselage body 1, and the first landing gear 7 and the second landing gears 8 form a three-point landing gear.

The landing gear 2 adopts a three-point landing gear, specifically, the landing gear 2 includes a first landing gear 7 and two second landing gears 8, the first landing gear 7 is disposed in front of the bottom of the fuselage body 1, and the two second landing gears 8 are disposed behind the bottom of the fuselage body 1, so that the first landing gear 7 and the two second landing gears 8 form the three-point landing gear, as shown in fig. 1 and 4. Further, the two second landing gears are symmetrically arranged with respect to the fuselage body 1, the center of gravity of the whole electric vertical take-off and landing aircraft is located in the range of the three-point landing gear, and the landing gears 2 enable the electric vertical take-off and landing aircraft to realize land traveling. The landing gear 2 is welded by adopting an aluminum pipe, and the aluminum pipe has the characteristics of light weight and high strength.

In one embodiment, the wheels on the first landing gear 7 are driven wheels, the wheels on the second landing gear 8 are in transmission connection with the land driving device, and the wheels on the second landing gear 8 are driving wheels.

In order to improve the running capability of the electric vertical take-off and landing aircraft on the land, the wheels on the second landing gear 8 are in transmission connection with the land driving device, and then the land driving device can drive the wheels to rotate, so that the wheels on the second landing gear 8 are driving wheels, the wheels on the first landing gear 7 are trailing wheels, and running power is provided for the electric vertical take-off and landing aircraft through the driving wheels in transmission connection with the land driving device as shown in fig. 2 and 5. Further, the wheels on the two second landing gears 8 can be respectively provided with independent land driving devices, so that the wheels on the two second landing gears 8 can be independently controlled, for example, an in-wheel motor is built in the wheels of the second landing gears 8, so that functions of differential steering and the like are realized, and the adaptability of the electric vertical take-off and landing aircraft on land is improved. The electric vertical take-off and landing aircraft adopts a vertical take-off and landing mode, the load of the machine wheel is small, the electric push rod for controlling the retraction of the machine wheel is moved to a proper deployment and retraction angle, and the mechanical self-locking of the electric push rod is utilized without designing an additional locking device.

In one embodiment, the body 1 is provided with a receiving space 9, and the landing gear 2 is retracted in the receiving space 9.

The fuselage body 1 is provided with a receiving space 9, as shown in fig. 2, in fig. 2 a receiving space 9 for the second landing gear 8, and the first landing gear 7 is also provided with a corresponding receiving space, not shown in the figure. When the electric vertical take-off and landing aircraft sails on the water surface or flies in the sky, the landing gear 2 can be accommodated in the accommodating space, so that the resistance of the electric vertical take-off and landing aircraft sailing on the water surface or flying in the sky can be reduced, and other things such as needed parts and the like can be placed in the accommodating space 9 besides the landing gear 2; when the electric vertical take-off and landing aircraft needs to travel on land, the landing gear 2 is opened outside the accommodating space, and the landing gear 2 is in a working state. The landing gear 2 can be unfolded and folded, so that not only is the resistance of the electric vertical take-off and landing aircraft when sailing on the water surface or flying in the sky reduced, but also the adaptability of the electric vertical take-off and landing aircraft is improved.

In one embodiment, the fuselage body 1 includes a cockpit 10, a cabin 11 and an equipment cabin 12, and skins of the cockpit 10, the cabin 11 and the equipment cabin 12 are made of carbon fiber composite materials and PVC foam sandwich.

The cabin 10, the cabin 11 and the equipment cabin 12 are arranged in the body 1, as shown in fig. 2, the cabin 10 is positioned at the front part of the body 1, the cabin 11 is positioned at the bottom of the body 1, and the equipment cabin 12 is positioned at the tail part of the cabin 10. The skins of the cockpit 10, the cabin 11 and the equipment cabin 12 are made of carbon fiber composite materials and PVC foam sandwich. The carbon fiber composite material has light weight and high strength, not only can meet the strength requirement of the electric vertical take-off and landing aircraft, but also can lighten the weight of the electric vertical take-off and landing aircraft so as to improve the operability and performance of the electric vertical take-off and landing aircraft. The PVC foam sandwich is light in weight and has excellent flame retardant capability. Interior decorations and interior are arranged in the cockpit 10, cockpit doors are arranged on two sides of the cockpit 10, so that a driver and passengers can conveniently go in and out, and a windshield is arranged in front of the cockpit 10. The equipment bay 12 is provided with equipment bay doors to facilitate installation of on-board equipment or storage of items. The surface of the cabin 11 is coated with waterproof paint, and the seam at the opening of the cabin 11 is sealed by sealing strips and waterproof glue to prevent water from entering the cabin 11.

In one embodiment, both the cockpit 10 and the hold 11 are streamlined.

The cockpit 10 and the ship cabin 11 adopt streamline designs, so that the resistance of the electric vertical take-off and landing aircraft when the aircraft runs on the water surface or runs in the sky is reduced.

In one embodiment, the system further comprises an electrical system, an avionics system, a flight control system and a lighting system.

The electric system comprises power distribution equipment, a circuit breaker and the like, and is used for supplying and distributing power to the electric vertical take-off and landing aircraft. The avionic system comprises an integrated component, a sensor, a display and the like, and utilizes the technologies of electronics, control, information and the like to realize the openness, the comprehensiveness, the intellectualization and the modularization of the system structure, enhance the flight performance of the aircraft, ensure the safe flight, the guidance and the approach of the aircraft and ensure the safer and more efficient aircraft. The flight control system is used for controlling the attitude and the flight path of the aircraft. The illumination system is responsible for the illumination. Comprises the following accessories: a large storage battery for 9 blocks such as a propeller motor (corresponding to flight driving equipment), a hub motor (corresponding to land driving equipment), a water jet propeller motor (corresponding to water propulsion equipment) and the like; 1 small storage battery (for flight control); 8 screw motors; 8 sets of propeller motors are matched with an electric tuning device; 2 main hub motors; 2 sets of electric tuning are matched with the main hub motor; a motor 1 of the water spraying propeller; the electric adjustment of the motor of the water spraying propeller is matched with 1 sleeve; 4 left and right side navigation lights (left red, right green); tail navigation lights (white) 1; 1 navigation light voltage regulator; front headlight 1; 4 motor-driven push rods of the arm; 3 motor-driven push rods of the machine wheel; 1 motor arm electric push rod voltage regulator; 1 wheel electric push rod voltage regulator; 1 umbrella throwing mechanism (electric); 1 pressure regulator of the umbrella throwing mechanism; 1 flight control host; 2.4G antenna 1 pair; a data transmission antenna 1 pair; satellite antenna+GPS antenna 1 pair; the atmosphere data computer module 1 is sleeved; 1 data transmission receiver; the ground station system 1 is sleeved; 1 airspeed tube; 1 cockpit display; 1 steering wheel; 1 steering mechanism; 1 joystick; powering up the system 1 sleeve; a charging system 1 sleeve; all-in-one cables, aviation plugs, and the like. The vertical stabilizer is arranged above the tail of the machine body 1, so that the effect of stabilizing the heading is achieved.

Note that the above is only a preferred embodiment of the present utility model and the technical principle applied. It will be understood by those skilled in the art that the present utility model is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the utility model. Therefore, while the utility model has been described in connection with the above embodiments, the utility model is not limited to the embodiments, but may be embodied in many other equivalent forms without departing from the spirit or scope of the utility model, which is set forth in the following claims.

Claims (10)

1. An electric vertical take-off and landing aircraft, characterized in that: the aircraft comprises an aircraft body (1), an undercarriage (2), a propeller (3) and an arm (4), wherein the propeller (3) is connected around the aircraft body (1) in a foldable manner through the arm (4), and the propeller (3) is in transmission connection with flight driving equipment; the bottom of the body (1) forms a ship body, and the tail of the body (1) is provided with water propulsion equipment; the landing gear (2) can be retracted and released in the machine body (1), and a wheel on the landing gear (2) is in transmission connection with land driving equipment; the flying driving device, the water propulsion device and the land driving device are all motors.

2. The electric vertical takeoff and landing aircraft according to claim 1, characterized in that: the mechanical arm (4) comprises a mounting base (5) and a folding arm (6), wherein the mounting base (5) is connected to the machine body (1), one end of the folding arm (6) is connected with the mounting base (5) in a folding manner, and the other end of the folding arm (6) is connected with the propeller (3).

3. The electric vertical takeoff and landing aircraft according to claim 1, characterized in that: the aircraft arm (4) is at least provided with four, each aircraft arm (4) is provided with at least two flight driving devices and two propellers (3), one propeller (3) corresponds to one flight driving device, the aircraft arm (4) positioned at the front part of the aircraft body (1) is folded towards the tail part of the aircraft body (1), the aircraft arm (4) positioned at the tail part of the aircraft body (1) is folded towards the head part of the aircraft body (1), and the aircraft arms (4) are not interfered with each other before and after being folded.

4. An electric vertical takeoff and landing aircraft according to claim 3, characterized in that: the projection of the horn (4) positioned at the front part of the body (1) on the reference surface is a first projection, the projection of the horn (4) positioned at the tail part of the body (1) on the reference surface is a second projection, a preset distance is arranged between the first projection and the second projection along the vertical direction, and the reference surface is a plane perpendicular to the direction of the front part of the body (1) pointing to the tail part.

5. The electric vertical takeoff and landing aircraft according to claim 1, characterized in that: the landing gear (2) comprises a first landing gear (7) and two second landing gears (8), wherein the first landing gear (7) is arranged in front of the bottom of the fuselage body (1), the two second landing gears (8) are arranged behind the bottom of the fuselage body (1), the two second landing gears (8) are symmetrically arranged relative to the fuselage body (1), and the first landing gear (7) and the second landing gears (8) form a three-point landing gear.

6. The electric vertical takeoff and landing aircraft according to claim 5, characterized in that: the landing gear is characterized in that the wheels on the first landing gear (7) are driven wheels, the wheels on the second landing gear (8) are in transmission connection with the land driving equipment, and the wheels on the second landing gear (8) are driving wheels.

7. The electric vertical takeoff and landing aircraft according to claim 1, characterized in that: the landing gear is characterized in that a containing space (9) is formed in the machine body (1), and the landing gear (2) is retracted in the containing space (9).

8. The electric vertical takeoff and landing aircraft according to claim 1, characterized in that: when the electric vertical take-off and landing aircraft sails on the water surface, the landing gear (2) is contained in the body (1), and the arm (4) is folded around the body (1) or the arm (4) is unfolded around the body (1).

9. The electric vertical takeoff and landing aircraft according to claim 1, characterized in that: when the electric vertical take-off and landing aircraft runs on land, the landing gear (2) is arranged outside the fuselage body (1), and the horn (4) is folded around the fuselage body (1).

10. The electric vertical takeoff and landing aircraft according to claim 1, characterized in that: when the electric vertical take-off and landing aircraft flies in the air, the landing gear (2) is contained in the fuselage body (1), and the horn (4) is unfolded around the fuselage body (1).