CN112046740A

CN112046740A - Vertical take-off and landing aircraft and flight method

Info

Publication number: CN112046740A
Application number: CN202010805056.XA
Authority: CN
Inventors: 粟善飞; 栾涛; 邱西志
Original assignee: Taizhou Research Institute Of South University Of Science And Technology
Current assignee: Taizhou Research Institute Of South University Of Science And Technology
Priority date: 2020-08-12
Filing date: 2020-08-12
Publication date: 2020-12-08

Abstract

The invention relates to the technical field of vertical take-off and landing aircrafts, and discloses a vertical take-off and landing aircraft and a flight method. The VTOL aerial vehicle includes a fuselage, a propeller, and an elevator. The propeller is positioned at the top of the fuselage and used for driving the vertical take-off and landing aircraft to take off vertically; the elevating rudder is positioned on the aircraft body and can swing relative to the aircraft body for driving the hovering vertical take-off and landing aircraft to turn or overturn. In the process of taking off the vertical take-off and landing aircraft, the vertical take-off and landing aircraft can take off vertically through the propellers, when the vertical take-off and landing aircraft takes off to a certain height, the vertical take-off and landing aircraft can move horizontally, turn to or turn over through changing the angle of the elevator and the rotating speed of the propellers on the vertical take-off and landing aircraft, and therefore the vertical take-off and landing aircraft can carry out normal flight movement through a simple structure. The flight method comprises a takeoff step, a cruise step and a landing step.

Description

Vertical take-off and landing aircraft and flight method

Technical Field

The invention relates to the technical field of aircrafts, in particular to a vertical take-off and landing aircraft and a flight method.

Background

With the development of unmanned aerial vehicle technology, it all has extensive effect in aspects such as high altitude aerial photography, remote monitoring, commodity circulation transportation and frontier defense patrol. Due to the requirements of users, unmanned aerial vehicles with a plurality of types of combined rotor wings and fixed wings appear in the market in recent years, the unmanned aerial vehicles comprise two types, one type is the unmanned aerial vehicle which can cruise through the integral rotation of a motor by 90 degrees, the unmanned aerial vehicle is complex in structure, and the technical cost and the potential safety hazard of the unmanned aerial vehicle are increased; the power system for taking off and the power system for cruising of the other unmanned aerial vehicle are independent systems, so that part of the power system (such as the power system for taking off) can be idle during cruising, and the dead load and cruising resistance are increased.

Disclosure of Invention

The present invention is directed to solving at least one of the problems of the prior art. Therefore, the invention provides the vertical take-off and landing aircraft with a simple structure and provides a flight method, so that the vertical take-off and landing aircraft can carry out normal flight motion through a simpler structure.

The invention also proposes a vertical take-off and landing aircraft comprising:

a body;

the propeller is positioned at the top of the fuselage and used for driving the vertical take-off and landing aircraft to take off vertically and hover at a preset height;

the elevator, the elevator is located the fuselage, and the air current that the screw formed can blow to the elevator, and the elevator can swing relatively the fuselage for the flight gesture of adjustment VTOL aircraft.

The vertical take-off and landing aircraft provided by the embodiment of the invention at least has the following beneficial effects: in the process of taking off the vertical take-off and landing aircraft, the vertical take-off and landing aircraft can take off vertically through the propeller, when the vertical take-off and landing aircraft takes off to a certain height, the vertical take-off and landing aircraft can move horizontally, turn to or turn over through changing the swing angle of the elevator and the rotating speed of the propeller on the vertical take-off and landing aircraft, a mechanism for driving a motor to rotate is omitted, a plurality of sets of driving systems are not required to be arranged, and the vertical take-off and landing aircraft can simplify the structure of the whole aircraft under the premise of normal flight.

In other embodiments of the VTOL aerial vehicle according to the present invention, the elevators are located at the bottom of the fuselage.

In accordance with further embodiments of the present invention, a VTOL aerial vehicle, having an elevator capable of swinging an angle relative to a fuselage, has an outer surface capable of being flush with an outer surface of the fuselage.

According to other embodiments of the invention, the vertical take-off and landing aircraft comprises a first lifting assembly and a second lifting assembly, wherein the first lifting assembly and the second lifting assembly respectively comprise propellers with the same number, a first vertical line is set as a vertical line capable of equally dividing the horizontal length of the fuselage, and the first lifting assembly and the second lifting assembly are symmetrically arranged along the first vertical line.

According to other embodiments of the invention, the VTOL aerial vehicle further comprises a camera, and the camera is located on the fuselage.

According to other embodiments of the invention, the VTOL aerial vehicle further comprises a navigation system and a control system, the fuselage comprises a cavity, and the navigation system and the control system are located in the cavity.

According to other embodiments of the VTOL aerial vehicle of the present invention, the outer wall of the fuselage is covered with an absorbent film.

According to other embodiments of the present invention, the VTOL aerial vehicle further comprises a first battery pack and a second battery pack, both of which are capable of powering the VTOL aerial vehicle.

There is also provided, in accordance with an embodiment of the present invention, a method for flying a VTOL aerial vehicle, including:

taking off: vertically taking off the vertical take-off and landing aircraft through a propeller positioned on the fuselage and hovering at a specified height;

cruising: the posture and the direction of the vertical take-off and landing aircraft are changed and cruise is carried out through the propeller and the elevator positioned on the aircraft body;

a landing step: after the vertical take-off and landing aircraft is in a hovering state through the propeller and the elevator, the vertical take-off and landing aircraft vertically lands through the propeller.

According to another embodiment of the invention, in the cruising step, the VTOL aerial vehicle is advanced in a vertical direction perpendicular to a line on which the propellers are arranged by adjusting the direction of the elevators, changing the angle of the VTOL aerial vehicle, and changing the rotation speed of the propellers.

Drawings

FIG. 1 is a schematic mechanical diagram of one embodiment of a VTOL aerial vehicle;

FIG. 2 is a front view of FIG. 1;

FIG. 3 is a diagram of a vertical take-off and landing aircraft in use;

FIG. 4 is another state diagram of a VTOL aerial vehicle.

Reference numerals: the aircraft comprises a fuselage 101, a propeller 102, an elevator 103, a nose 104, a motor 105, a wing tip support 106, a camera 107, a first lifting assembly 108 and a second lifting assembly 109.

Detailed Description

The concept and technical effects of the present invention will be clearly and completely described below in conjunction with the embodiments to fully understand the objects, features and effects of the present invention. It is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and those skilled in the art can obtain other embodiments without inventive effort based on the embodiments of the present invention, and all embodiments are within the protection scope of the present invention.

In the description of the embodiments of the present invention, if an orientation description is referred to, for example, the orientations or positional relationships indicated by "upper", "lower", "front", "rear", "left", "right", etc. are based on the orientations or positional relationships shown in the drawings, only for convenience of describing the present invention and simplifying the description, but not for indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention.

In the description of the embodiments of the present invention, if a feature is referred to as being "disposed", "fixed", "connected", or "mounted" to another feature, it may be directly disposed, fixed, or connected to the other feature or may be indirectly disposed, fixed, connected, or mounted to the other feature. In the description of the embodiments of the present invention, if "a number" is referred to, it means one or more, if "a plurality" is referred to, it means two or more, if "greater than", "less than" or "more than" is referred to, it is understood that the number is not included, and if "greater than", "lower" or "inner" is referred to, it is understood that the number is included. If reference is made to "first" or "second", this should be understood to distinguish between features and not to indicate or imply relative importance or to implicitly indicate the number of indicated features or to implicitly indicate the precedence of the indicated features.

Unmanned aerial vehicle that combines at current rotor and stationary vane includes two kinds, one kind is that it drives the propeller through the rotatory 90 degrees of motor, makes its unmanned aerial vehicle that cruises, and this kind of unmanned aerial vehicle need set up revolution mechanic to realize the rotatory operation of motor, whole quick-witted structure is comparatively complicated, increases producer's manufacturing cost, and causes certain potential safety hazard to unmanned aerial vehicle's structure. Another kind of unmanned aerial vehicle controls unmanned aerial vehicle's lift and cruise respectively through two sets of systems, and this kind of unmanned aerial vehicle can have the idle problem of driving system at the in-process of flight, has increased unmanned aerial vehicle's dead load and movement resistance.

In view of the above problems, an embodiment of the present invention proposes a vertical take-off and landing aircraft, which includes a fuselage 101, a propeller 102, and an elevator 103, as shown in fig. 1. Wherein, the propeller 102 is positioned on the top of the fuselage 101, and when the propeller 102 rotates, the vertical takeoff and landing aircraft can take off vertically. The elevator 103 is located on the fuselage 101 and the elevator 103 can be swung relative to the fuselage 101 to change the direction of the VTOL aerial vehicle in cooperation with the propeller 102 on the VTOL aerial vehicle.

In the use process, firstly, the VTOL aerial vehicle is positioned on the ground, then the switch of the VTOL aerial vehicle is turned on, so that the propeller 102 starts to rotate, at the moment, the propeller 102 rotates to provide vertical upward thrust for the VTOL aerial vehicle, so that the VTOL aerial vehicle can take off along the vertical direction, and the purpose of vertical take-off of the VTOL aerial vehicle is realized. When the vertical take-off and landing aircraft flies to a certain height, the rotating speed of the propeller 102 of the vertical take-off and landing aircraft is adjusted, so that the lift force provided by the propeller 102 for the vertical take-off and landing aircraft is consistent with the gravity of the vertical take-off and landing aircraft, the vertical take-off and landing aircraft enters a hovering state, at the moment, the direction of the machine head 104 on the machine body 101 can be adjusted by adjusting the angle of the elevator 103 relative to the machine body 101, the propeller 102 of the vertical take-off and landing aircraft inclines at a certain angle, and finally, the flight attitude and the movement condition of the vertical take-off and landing aircraft can be adjusted by matching the propeller 102 with the elevator. The position of the elevator 103 corresponds to the propeller 102 in the Z-axis direction, and the correspondence may not be absolute correspondence, and there may be an appropriate positional deviation between the two as long as the airflow generated by the rotation of the propeller 102 can flow through the elevator 103, and therefore, the attitude of the body 101 can be adjusted by the elevator 103. When the propellers 102 and the elevators 103 are provided in plurality, the elevators 103 may be in one-to-one correspondence with the propellers 102, or may have a certain positional deviation, so that the wind blown out by the propellers 102 may flow toward the elevators 103, which facilitates the elevators 103 to change the flight attitude of the vtol aircraft.

In the above embodiment, the flight attitude of the vtol aircraft can be adjusted by the cooperation of the propeller elevators. Specifically, as shown in fig. 1 and 2, the vtol aerial vehicle further includes a motor 105, and the motor 105 is located at the top of the fuselage 101 and is used for driving the propeller 102 to rotate. When the VTOL aerial vehicle is not taking off, the VTOL aerial vehicle stands on the ground as shown in FIG. 2. The switch is then turned on, causing the motor 105 to start rotating and driving the propeller 102 to rotate, thereby allowing the VTOL aerial vehicle to take off vertically. In this embodiment, the motor 105 is in a horizontal state during the takeoff process, even if a certain inclination is generated due to weather, the direction of the fuselage 101 can be adjusted through the rotating speeds of the elevator 103 and the propeller 102 located at the bottom of the fuselage 101, so that the motor 105 does not deflect relative to the fuselage 101, compared with an unmanned aerial vehicle which needs to deflect the motor 105 by 90 degrees and drives the propeller 102 to cruise and fly, the unmanned aerial vehicle in this embodiment has low technical cost and higher safety.

Specifically, as shown in fig. 2 and 3, in the process of taking off the vertical take-off and landing aircraft, if the airframe 101 is deviated due to weather, if the airframe 101 is deviated to the Y-axis forward direction shown in fig. 2, and the state shown in fig. 3 is reached, the elevator 103 is also deviated to the Y-axis forward direction shown in fig. 3, as shown in fig. 3, so that the airflow in the air can form pressure on the side surface of the elevator 103 facing the Y-axis forward direction, and finally the vertical take-off and landing aircraft is slowly restored to the state shown in fig. 2, thereby ensuring the vertical take-off of the vertical take-off and landing aircraft.

Specifically, as shown in fig. 1, the propellers 102 on the VTOL aerial vehicle are all arranged along the Y-axis direction. The flight attitude of the VTOL aerial vehicle can be adjusted by the rotation speed of the propeller 102.

Specifically, as shown in fig. 2, the vtol aerial vehicle further includes a wing tip support 106, and the wing tip support 106 is located at the bottom of the fuselage 101 of the vtol aerial vehicle, and the vtol aerial vehicle can stand on the ground through the wing tip support 106 when the vtol aerial vehicle is located on the ground.

As another example, as shown in fig. 2, the elevator 103 is located at the bottom of the fuselage 101, and when the propeller 102 of the vtol aircraft rotates, the wind passing through the propeller 102 flows toward the elevator 103 through the outer wall of the fuselage 101, so that the elevator 103 can better adjust the direction of the vtol aircraft by the airflow flowing toward it. And because when the elevator 103 is located at the bottom of the fuselage 101, the elevator 103 can drive the fuselage 101 to turn, compared with the elevators 103 located at other positions of the fuselage 101, the elevator 103 located at the bottom of the fuselage 101 can drive the vertical take-off and landing aircraft fuselage 101 to turn by a larger angle when rotating by a fixed angle.

In some embodiments, the elevator 103 located at the bottom of the fuselage 101 can be flush with the surface of the fuselage, so that the elevator can be smoothly connected with the surface of the fuselage 101, and when the elevator 103 is not swung relative to the fuselage 101, the two side surfaces of the elevator 103 can be smoothly screwed with the outer surface of the fuselage 101, so that the wind resistance is reduced. When the elevator 103 swings with respect to the fuselage 101, both side surfaces of the elevator 103 can rotate with respect to the fuselage 101, thereby adjusting the flying attitude of the vtol aircraft.

Specifically, as shown in fig. 1, the length direction of the vtol aircraft is arranged along the X-axis direction shown in fig. 1, the straight line where the center line of the X-axis length direction of the vtol aircraft is located is a first perpendicular line, the vtol aircraft may include a set of elevators 103 symmetrically arranged along the first perpendicular line, and may also include a plurality of sets of elevators 103, and when the vtol aircraft includes a set of elevators 103, the angle of the elevators 103 relative to the fuselage 101 may be adjusted, so as to adjust the flight attitude of the vtol aircraft. When the VTOL aerial vehicle comprises a plurality of groups of elevators 103, the direction of the VTOL aerial vehicle can be adjusted by matching the elevators 103 with the propellers 102, and the motion balance of the VTOL aerial vehicle can be adjusted by the motion of each elevator 103.

Specifically, the elevator 103 has an outer surface that can be flush with the outer surface of the fuselage 101. The outer surface may be acted upon by the airflow to alter the attitude of the VTOL aerial vehicle and reduce the drag of the VTOL aerial vehicle.

Specifically, as shown in fig. 1, a notch is formed in the bottom of the fuselage 101, the elevator 103 is located in the notch, and the elevator 103 can swing relative to the notch, so that the flight attitude of the vtol aircraft is changed.

For example, as shown in fig. 1 and 2, the vtol aerial vehicle includes 4 elevators 103, which are a first elevator, a second elevator, a third elevator, and a fourth elevator in order along the X-axis from the negative direction to the positive direction. When the nose 104 of the VTOL aerial vehicle deflects towards the positive direction of the Y-axis, the first elevator, the second elevator, the third elevator and the fourth elevator can all deflect towards the positive direction of the Y-axis, so that the nose 104 of the VTOL aerial vehicle deflects towards the negative direction of the Y-axis, and the shape of the VTOL aerial vehicle is adjusted. Or, under the condition that the Z-axis rotational balance of the vtol aircraft needs to be ensured, as shown in fig. 4, the first elevator and the second elevator rotate around the X axis in the positive direction of the Y axis, the third elevator and the fourth elevator rotate around the X axis in the negative direction of the Y axis, and at this time, the forces of the airflow on the first elevator, the second elevator, the third elevator and the fourth elevator reach a balance, so that the vtol aircraft does not rotate around the Z axis. And then the vertical take-off and landing aircraft moves in other directions by matching with different rotating speeds of the propeller 102 in the vertical take-off and landing aircraft.

As another example, as shown in FIG. 1, the VTOL aerial vehicle includes a first lift assembly 108 and a second lift assembly 109, each of the first lift assembly 108 and the second lift assembly 109 including one or more propellers 102, respectively. As shown in fig. 1, the length direction of the vtol aircraft is along the X-axis direction shown in fig. 1, a straight line of a center line of the vtol aircraft in the X-axis length direction is a first vertical line, the first vertical line divides the vtol aircraft body 101 into two equal-length parts in the X-axis direction, the first lifting assembly 108 and the second lifting assembly 109 are symmetrically arranged on two sides of the first vertical line with the first vertical line as a center line, and the first lifting assembly 108 and the second lifting assembly 109 respectively include the same number of propellers 102. When the vertical take-off and landing aircraft takes off, the propellers 102 in the first lifting assembly 108 and the propellers 102 in the second lifting assembly 109 are in opposite directions, and the rotation of the propellers 102 in opposite directions can counteract the moment and the rotation of the propellers in the Z-axis direction, so that the vertical take-off and landing aircraft can take off vertically, the rotation of the aircraft body around the Z axis is avoided while taking off, and the stable take-off is kept.

Specifically, as shown in fig. 1, the first lifting assembly 108 and the second lifting assembly 109 each include two propellers 102, and it is contemplated that the first lifting assembly 108 and the second lifting assembly 109 may include other numbers of propellers 102, for example, both of the first lifting assembly 108 and the second lifting assembly 109 include one propeller 102 and three propellers 102, as long as the first lifting assembly 108 and the second lifting assembly 109 are symmetrically disposed on both sides of the first vertical line and the first lifting assembly 108 and the second lifting assembly 109 include the same number of propellers 102. And in the above embodiment, the symmetry of the first lifting assembly 108 and the second lifting assembly 109 along the first vertical line includes the following meaning that any one propeller 102 in the first lifting assembly 108 can find a propeller 102 in the second lifting assembly 109 to be arranged symmetrically with the propeller 102 along the first vertical line.

The motion condition of the vertical take-off and landing aircraft can be adjusted through the propeller 102 and the elevator 103 of the vertical take-off and landing aircraft, so that the vertical take-off and landing aircraft can perform actions such as horizontal movement, climbing or landing.

For example, when the VTOL aerial vehicle is in a hovering state, the VTOL aerial vehicle can be moved along an arc-shaped trajectory by adjusting the rotation speed of a portion of the propeller 102 of the VTOL aerial vehicle.

For example, when the vtol aircraft is hovering, the elevator 103 of the vtol aircraft can be adjusted to rotate around the Z axis to the position shown in fig. 3 in the Y axis direction, and the rotation speed of the propeller 102 is accelerated, so that the climbing of the vtol aircraft can be completed.

For example, when the VTOL aerial vehicle needs to perform a linear motion, the elevator 103 of the VTOL aerial vehicle can be adjusted to rotate around the Z axis to the Y axis direction to the position of FIG. 3, and the VTOL aerial vehicle can be moved to the Y axis direction by adjusting the rotation speed of the propeller 102.

As another embodiment, the vtol aircraft further includes a camera 107, and the vtol aircraft can perform aerial photography, surveying, cruising and other tasks through the camera 107.

Specifically, as shown in fig. 1, the camera 107 is located between the first lifting component 108 and the second lifting component 109, and the camera is embedded in the nose 104 of the fuselage 101, so that when the VTOL aerial vehicle inclines at a certain angle towards the Y-axis direction, the situation of the two sides of the VTOL aerial vehicle along the Z-axis direction can be photographed through the camera 107.

More specifically, the camera 107 may be a 360-degree camera that allows the camera to complete the image of the target object even if the VTOL aerial vehicle is rotated by a small angle.

As another embodiment, a cavity is arranged inside the fuselage 101, the vtol aircraft further includes a navigation system and a control system, the navigation system is used for navigating the vtol aircraft, the control system is used for controlling the rotation condition of each propeller 102 and the rotation condition of the elevator 103 in the vtol aircraft, the navigation system and the control system are located in the cavity of the fuselage 101 of the vtol aircraft, and compared with an unmanned aerial vehicle located on the outer wall of the fuselage 101 by the navigation system and the control system, the unmanned aerial vehicle in this embodiment has a smooth outer wall and a streamlined design, and has no other parts, thereby greatly reducing the resistance generated by the high-speed airflow generated by the propellers 102 passing through the fuselage 101, improving the lift-drag ratio of the vtol aircraft, and improving the endurance of the vtol aircraft. The structure at least comprises the following technical effects: because the navigation system and the control system are both located in the inner cavity of the fuselage 101, the flight balance of the VTOL aircraft is easier to ensure. Furthermore, the control system and the navigation system are arranged in the fuselage such that the center of gravity of the VTOL aerial vehicle is located near (or on) the first vertical line of the fuselage 101, which helps to improve the stability of the fuselage.

In some embodiments, as shown in fig. 1 and 2, the fuselage 101 of the vtol aircraft is arranged smoothly along the Z-axis and has a decreasing length along the Y-axis, so that the airflow flowing from the propeller 102 in the forward direction toward the Z-axis can flow more easily toward the elevator 103, thereby facilitating the elevator 103 to adjust the flight attitude of the vtol aircraft.

As another embodiment, VTOL aircraft's outer wall still covers has the adsorption film, and the adsorption film is made by granule adsorbing material, can adsorb impurity or haze granule that are located the air, reaches air-purifying's effect to make VTOL aircraft can also purify the air at the in-process of flight.

Specifically, the outer surface of the adsorption film is provided with a pore structure, and the pore structure increases the specific surface area of the adsorption film, so that the adsorption capacity of the adsorption film on impurities in the air is enhanced.

Specifically, the vertical take-off and landing aircraft adopts a full-flying-wing design, in the design, wings and an aircraft body 101 form a whole, and compared with a traditional cabin and part of the wings, the vertical take-off and landing aircraft adopting the full-flying-wing design greatly reduces airflow separation due to the streamlined appearance, so that the lift-drag ratio is reduced, and the cruising ability of the vertical take-off and landing aircraft is enhanced.

In some embodiments, as shown in fig. 2 to 4, the shape of the fuselage 101 is a structure with a large top and a small bottom, specifically, the head of the fuselage 101 is an arc-shaped structure, and the thickness of the fuselage along the Y-axis direction gradually decreases from the head to the bottom of the fuselage, and a tip is formed at the bottom, so that the overall machine is in a streamline design, which helps to improve the lift force and reduce the wind resistance. Based on the embodiment, in some other embodiments, the elevator 103 is disposed at the bottom of the fuselage 101, specifically, a notch for installing the elevator 103 is disposed at the bottom of the fuselage 101, the number of the notches is correspondingly set according to the number of the required elevators 103, the elevator 103 is correspondingly installed in the notch, and the connection of the elevator 103 at the bottom of the fuselage is realized. The elevator 103 at the bottom can swing relative to the body toward both sides of the body in the Y-axis direction. During specific implementation, the elevator 103 can adopt an outer surface consistent with the tip of the bottom of the body, so that the two side surfaces of the elevator 103 are flush with the two side surfaces of the body, the outer surface of the elevator 103 can be smoothly screwed with the outer surfaces of other parts of the body 101, the smoothness of the outer surface is maintained, and the reduction of wind resistance is facilitated.

And because the design of the full flying wing enables the fuselage 101 and the wings of the VTOL aerial vehicle to form a whole, the surface area of the fuselage 101 is enlarged, the area of the adsorption film covering the outer surface of the fuselage 101 is enlarged, and the air purifying capacity of the VTOL aerial vehicle is enhanced.

As another embodiment, the VTOL aerial vehicle further comprises a first battery pack and a second battery pack, and both the first battery pack and the second battery pack can supply power to the VTOL aerial vehicle, so that the endurance of the VTOL aerial vehicle is greatly increased.

Specifically, the first battery pack and the second battery pack can be operated independently, even if one of the battery packs is damaged, the work of the other battery pack is not delayed, and the operation safety of the VTOL aircraft is improved.

Specifically, the first battery pack and the second battery pack are symmetrically arranged on the fuselage, so that the vertical take-off and landing aircraft can be kept balanced more easily.

As another embodiment, the inner cavity of the VTOL aerial vehicle also comprises three sets of redundant systems, and when the control system cannot work, the redundant systems can replace the control system to work, so that the safety of the operation of the VTOL aerial vehicle is greatly improved.

As another embodiment, the fuselage 101 of the VTOL (vertical take-off and landing) aircraft adopts the integrated design of carbon fiber as a whole, the fuselage 101 is designed according to the equal strength principle, and in addition, according to the actual stress condition of the VTOL aircraft in the working process, the finite element analysis and the optimized design are carried out on the internal structures and the wall thicknesses of different parts of the VTOL aircraft, so that the weight of the whole aircraft is reduced to the maximum extent while the strength is ensured, the strength of the fuselage 101 of the VTOL aircraft is increased, and the safety of the VTOL aircraft is further improved.

The invention also discloses a flight method of the vertical take-off and landing aircraft, and the flight of the vertical take-off and landing aircraft comprises three steps, namely a take-off step, a cruising step and a landing step. In the taking-off step, the vertical take-off and landing aircraft vertically takes off through the propeller 102 and hovers after rising to a certain height, in the cruising step, the motion of the vertical take-off and landing aircraft is changed through the matching of the propeller 102 and the elevator 103 on the vertical take-off and landing aircraft, so that the vertical take-off and landing aircraft can perform horizontal motion, steering motion or overturning motion, and after the flying vertical take-off and landing aircraft hovers, the vertical take-off and landing aircraft lands through the propeller 102.

In the method, the VTOL aerial vehicle can hover after taking off to a certain height, and then can cruise under the cooperation of the propeller 102 and the elevator 103. Compared with an unmanned aerial vehicle which needs a lifting driving system and a horizontal pushing system, the vertical take-off and landing aircraft in the embodiment is lower in weight, and the cruising ability of the vertical take-off and landing aircraft is enhanced.

In the takeoff step, when the vertical takeoff and landing aircraft deflects due to weather and the like, the flight attitude and the flight direction of the vertical takeoff and landing aircraft can be adjusted through the cooperation of the elevator 103 and the propeller 102 on the vertical takeoff and landing aircraft. For example, as shown in fig. 3, when the nose 104 of the VTOL aerial vehicle deflects forward toward the Y-axis, the elevator 103 may rotate toward the Y-axis forward direction, thereby causing the VTOL aerial vehicle to gradually change to the state shown in fig. 2.

When the VTOL aerial vehicle completes the takeoff step and is in a hovering state, the VTOL aerial vehicle may begin flying using the cooperation of the propellers 102 of the VTOL aerial vehicle and the elevators 103 of the VTOL aerial vehicle. For example, when the vtol aircraft needs to start flying in the Y-axis forward direction, firstly, the rudder is shifted in the Y-axis direction, so that the nose 104 of the vtol aircraft rotates in the Y-axis forward direction, then the vtol aircraft is driven by the propeller 102 to start moving in the Y-axis forward direction, because the propeller 102 of the vtol aircraft has a certain angle at this time, while moving in the Y-axis direction, there may be rotation around the Z-axis direction, at this time, the elevator 103 may be adjusted, so that part of the elevator 103 rotates in the Y-axis forward direction, and part of the elevator 103 rotates in the Y-axis negative direction, so that the vtol aircraft can smoothly move in the Y-axis forward direction.

The vtol aerial vehicle controls the vtol aerial vehicle to perform horizontal flight, climbing and the like through the propeller 102 and the elevator 103, for example, when the vtol aerial vehicle is in a hovering state, the rotation speed of the propeller 102 of the vtol aerial vehicle can be adjusted, so that the vtol aerial vehicle moves along an arc-shaped track. For example, when the vtol aircraft is hovering, the ascent of the vtol aircraft can be completed by adjusting the elevators 103 of the vtol aircraft to rotate around the Z axis toward the Y axis to the position shown in fig. 3 and accelerating the rotation speed of the propeller 102. For example, when the VTOL aerial vehicle needs to perform a linear motion, the elevator 103 of the VTOL aerial vehicle can be adjusted to rotate around the Z axis to the Y axis direction to the position of FIG. 3, and the VTOL aerial vehicle can be moved to the Y axis direction by adjusting the rotation speed of the propeller 102. After the work is completed, the VTOL aerial vehicle can perform a landing step, hover the VTOL aerial vehicle at a designated height and place through the propeller 102 and the elevator 103, and then gradually land the VTOL aerial vehicle through the propeller 102.

In the embodiment of above-mentioned VTOL aircraft, VTOL aircraft simple structure only needs can make VTOL aircraft accomplish vertical take-off and turn to, motion such as upset through the cooperation of screw 102 and elevator 103, compare in the unmanned aerial vehicle that needs two sets of driving system systems, the VTOL aircraft that above-mentioned embodiment provided is light in weight, and is small, can reduce the resistance in the VTOL aircraft motion effectively, promotes VTOL aircraft's duration, and can increase payload to a certain extent.

The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of those skilled in the art without departing from the gist of the present invention. Furthermore, the embodiments of the present invention and the features of the embodiments may be combined with each other without conflict.

Claims

1. A VTOL aerial vehicle, comprising:

a body;

the elevator, the elevator is located on the fuselage, just the air current that the screw formed can blow to the elevator, the elevator can be relative the fuselage swings for the flight gesture of adjustment VTOL aircraft.

2. The VTOL aerial vehicle of claim 1, wherein the elevators are located at the bottom of the fuselage.

3. The VTOL aerial vehicle of claim 2, wherein the elevator, which is swingable at an angle relative to the fuselage, has an outer surface that is capable of being flush with an outer surface of the fuselage.

4. The vtol aerial vehicle of claim 1, comprising a first lift assembly and a second lift assembly, each of the first lift assembly and the second lift assembly comprising a same number of the propellers, wherein a first vertical line is provided as a vertical line capable of dividing the horizontal length of the fuselage into equal parts, and wherein the first lift assembly and the second lift assembly are symmetrically disposed along the first vertical line.

5. The vtol aerial vehicle of claim 1, further comprising a camera positioned on the fuselage.

6. The vtol aerial vehicle of claim 1, further comprising a navigation system and a control system, wherein the fuselage comprises a cavity therein, and wherein the navigation system and the control system are located within the cavity.

7. The vtol aerial vehicle of claim 1, wherein an outer wall of the fuselage is covered with an absorbent film.

8. The vtol aerial vehicle of claim 1, further comprising a first battery pack and a second battery pack, each of the first battery pack and the second battery pack capable of powering the vtol aerial vehicle.

9. A flight method according to any one of claims 1 to 8, comprising:

taking off: vertically taking off the VTOL aerial vehicle and hovering at a specified height through the propeller on the fuselage;

cruising: changing the attitude and the direction of the VTOL aerial vehicle through the propeller and the elevator positioned on the fuselage, and cruising;

10. A method of flying as claimed in claim 9 wherein in the cruising step, the vtol vehicle is advanced in a vertical direction perpendicular to the line on which the propellers are aligned by adjusting the direction of the elevators, changing the angle of the vtol vehicle, and changing the speed of rotation of the propellers.