WO2019108091A1

WO2019108091A1 - Personal aircraft (variants) and flight methods thereof

Info

Publication number: WO2019108091A1
Application number: PCT/RU2018/000715
Authority: WO
Inventors: Дмитрий Валентинович РУКАВИЦЫН
Original assignee: Дмитрий Валентинович РУКАВИЦЫН
Priority date: 2017-12-01
Filing date: 2018-10-31
Publication date: 2019-06-06
Also published as: RU2671447C1

Abstract

The invention relates to the field of aviation, and more particularly to designs and flight methods for manned aircraft. A personal aircraft comprises an X-shaped body, and two retractable wings equipped with flaps and fastened to the front ends of the body such as to be pivotable about an axis perpendicular to the plane of the body, or four folding wings fastened to the front and rear ends of the body. The four wings are designed to be capable of unfolding into the plane of the body from a position perpendicular to the plane of the body. The aircraft comprises a vertical stabilizer, and hand and foot-operated control elements situated in the front and rear parts of the body respectively. Four power units are designed to be rotatable and are attached in pairs to the ends of the body. Each power unit is comprised of an engine with propellers in a protective casing. The body is designed to accommodate a pilot in a position in which the coronal plane of the pilot is parallel to the plane of the body. The result is improved aerodynamic characteristics as a result of a reduction in drag.

Description

Individual aircraft (options) and methods of its flight.

The group of inventions relates to the field of aviation technology and can be used in the design of manned individual aircraft (LA), which can carry out vertical take-off and landing.

Known individual aircraft and method of its flight (US 2003094537 A1, 05.22.2003), selected as a prototype. The aircraft includes a hull, two wings fitted with flaps and fixed in the central part of the hull, a vertical stabilizer equipped with a rudder, manual and foot controls located in the cabin of an individual LA, and four rotary power units made on the wings so that the power units are the sides are arranged symmetrically with respect to the longitudinal axis of the body of the power units of the other side, each power unit being an engine with propellers and made with POSSIBILITY rotation in place of the fastening around the axis perpendicular to the longitudinal axis of the housing and lying in its plane, wherein the aircraft is configured for placement in its seated cockpit.

The method is characterized by the fact that the power units of an aircraft on the supporting surface on the chassis are located in the plane of the body and carry out a vertical take-off, then, turning the power units into a vertical position, they fly in horizontal and vertical directions, using changes in the rotational speeds of the engines with propellers, rudder, flaps and elevators.

This unit is a light-engined aircraft with engines with propellers made on its wings. The flight method does not provide the possibility of maneuvering without sufficient horizontal speed. LA is bulky and not intended for urban environments. In addition, its design is clearly unreliable.

The present invention is to create a compact, principally different individual aircraft with vertical take-off and landing capabilities, as well as flying in various modes to choose a pilot: on the basis of an airplane or on the basis of an aircraft such as a quadcopter, while providing ease of use due to its small size. The technical result is an increase in usability due to the compactness of the proposed solution, as well as providing higher aerodynamic characteristics of the proposed aircraft due to lower drag and improved aerodynamic stability.

The technical results achieved can be attributed to improving the reliability of the design due to the implementation of a single aerodynamic X-shaped hull with integrated rotary power units at its ends and expanding the functionality of the aircraft due to various take-off options and, accordingly, landing and flight modes.

Technical results are achieved by the fact that an individual aircraft contains an X-shaped hull, two sliding wings, fitted with flaps and fixed at the front ends of the hull with the possibility of rotation along an axis perpendicular to the plane of the hull at the point of their attachment, or four folding wings fixed at the front ends bodies with flaps and at the rear ends with elevators and made with the possibility of folding into the plane of the body from a position perpendicular to the plane of the body, vertical stabilize p, equipped with a rudder, manual and foot controls located in the front and rear parts of the body, respectively, and four power units, made rotatable and fixed to the ends of the body so that the power units of one side are symmetrically located relative to the longitudinal axis of the body power units of the other side, each power unit is an engine with propellers in a protective casing. In this case, the body is made with the possibility of placing on it the pilot in a position in which the frontal plane of the pilot is parallel to the plane of the body.

One of the embodiments of the present invention on the front of the body is made aerodynamic fairing pilot.

In another embodiment, the hull is provided with pilot-securing elements.

In the third variant, chassis can be made at the ends of four folding wings.

Also, these technical results are achieved in the method of flight of an individual aircraft, including the vertical take-off of the aircraft, the body of which is located vertically relative to the supporting surface and is arranged to accommodate the pilot on it in a position in which the frontal plane of the pilot is parallel to the plane of the body. Next, by turning power units in the plane of the body translate it from a vertical position to a horizontal one and either fly, maneuver by changing the rotational speed of each engine with propellers of the power unit / or changing the position of each power unit relative to the body, pushing the two wings with flaps or spreading four wings with flaps and elevators and fly, maneuvering with the help of something one, the whole set or a combination of several of the following: changes in speed rotation of each motor with propellers, each change of position of the power unit relative to the housing, the rudder on the vertical stabilizer, a flap, the elevators.

In addition, these results are achieved in the method of flight of an individual aircraft, including the take-off of the aircraft, standing on the supporting surface on four folded folding wings directly, or on the chassis, made at their ends, in a horizontal position, while the body of the aircraft is designed to accommodating the pilot on it in a position in which the frontal plane of the pilot is parallel to the plane of the hull. Then either fly, maneuvering by changing the speed of rotation of the engine with propellers of each power unit and / or changing the position of each power unit relative to the hull, or folding wings with flaps and elevators and flying, maneuvering with one thing, all combination or several of the following: changes in the speed of rotation of each engine with propellers, changes in the position of each power unit relative to the body, steering I'm on the vertical stabilizer, flaps, elevators.

In this way, a vertical takeoff can be performed.

They can also carry out a horizontal takeoff.

X-shaped hull, performed mostly by a streamlined aerodynamic shape, in other words, a hull-wing with four swiveling power units at its ends and folding or sliding wings provide compactness, higher aerodynamic characteristics, improved maneuvering and the ability to select the flight mode for various purposes . Possible take-off from the vertical and horizontal positions of the apparatus relative to the ground, as well as landing. The flight can be carried out with folded wings, and spread out like a quadcopter. With the wings of the proposed LA spread out can fly like a normal plane, turning the power units after reaching a certain speed perpendicular to the plane of the body, downstream.

The proposed design of the aircraft and methods of take-off and landing allows it to be compact and take up less parking space, compared to a car, right up to home accommodation. This significantly improves the usability.

Thus, the proposed group of inventions provides increased usability due to the compactness of the aircraft, higher aerodynamic characteristics due to the described design and take-off and flight modes.

Under the "front ends of the case" and "rear ends of the case" should be understood the final branches of the X-shaped case in its front and rear parts, respectively, on which the power units are placed. Due to the fact that the body is X-shaped, it means that it has four ends. In this case, the front and rear parts of the body are two parts, which are formed by separating the body in half with a cross section and lie closer to the edges of the body so that between them one can distinguish the middle part of the body.

It will be obvious to a person skilled in the art that a vertical stabilizer is positioned with a rudder at the rear of the hull between two power units at its rear ends.

By “frontal plane” is meant the generally accepted (in particular in medicine) term for the section plane of a person. In other words, the pilot rests or rests with his whole body on the body of the aircraft, depending on the initial position of the aircraft relative to the supporting surface - the ground.

By “supporting surface” is meant flat, flat terrain, the ground on which the aircraft is standing or relative to.

By "vertical position" is meant such a position of the aircraft body in which it stands vertically on the ground, resting on the vertical stabilizer and the rear parts of the body. The power units at the same time rotated parallel to the ground - the supporting surface. In this position, the vertical takeoff.

Under the "horizontal" position during takeoff should be understood the position of the body of the aircraft, based on the four folding wings in the folded state; because front wings can be made longer than the rear, the body will be at some angle to the support surface. The take-off in this case may be vertical, the engines are rotated parallel to the ground. Also, the take-off can be horizontal on a suitable surface, i.e. according to the principle of an ordinary aircraft, if the landing gear is made at the ends of the wings.

The essence of the invention is illustrated in figure 1-8.

On figa-1b presents the proposed drawings LA in a vertical position on the support surface for the version with two sliding wings.

On figa-2b presents the drawings of the proposed LA in a horizontal position for the version with two spread out folding wings.

On fig.Za-Sv presents the drawings of the proposed aircraft for the version with two sliding wings and with the power units turned perpendicular to the plane of the hull.

On figa-4b shows the drawings of the proposed LA in a horizontal position with the wing spread shown.

On figa-5b shows the drawings of the proposed LA in a horizontal position with four spread folding wings.

On figa-bv shows drawings of the proposed aircraft, standing on four folding wings from the chassis during a vertical or horizontal takeoff.

In Fig.7 depicts a principal view of the proposed LA in a vertical position on the support surface for the variant with two sliding wings.

On Fig depicts a principal view of the proposed LA in a horizontal position for the version with two spread out folding wings.

The individual aircraft is an X-shaped body 4, on which, according to the first embodiment, two sliding wings 3, fitted with flaps 11 and can be rotated along an axis perpendicular to the plane of the body 4 in the place of their attachment, can be fixed to the front ends (FIG. 4a ). According to the second variant, there can be four folding wings 3 fixed on the front ends of the body 4 with flaps 1 1 and on the rear ends with the rudders of height 12 and made possible to fold into the plane of the body 4 from a position perpendicular to the plane of the body 4 (FIG. 5-6 ). The wings 3 at the rear ends of the hull can be made of either different or the same length as compared with the wings 3 at the front ends. In the rear part of the housing 4 between the two power units there is a vertical stabilizer with a rudder direction 6. Manual 10 controls are located in the front of the housing 4, foot 8 controls in the rear of the housing 4, joysticks can be used as such elements in the hands area with pushbutton switches, and in the foot zone - movable pedal platforms. Four rotary power units are fixed at the ends of the housing 4 so that the power units of one side are symmetrically located relative to the longitudinal axis of the housing 4 of the power units of the other side, each power unit being an engine 1 with propellers 2 in a protective casing 7. As engines 1 it is proposed to use electric motors. The power units are rotated using gear motors 9, while turning is carried out at the attachment point of such units, so they can be rotated around an axis perpendicular to the longitudinal axis of the body 4 and lying in its plane.

All controls, including electronic, electrical and mechanical parts, as well as batteries, are proposed to be placed inside the wing body 4 and wings 3. The individual aircraft itself, in particular its body 4, is arranged to place the pilot 5 on it in a position in which the frontal plane the pilot is parallel to the plane of the body 4, that is, the pilot 5 approaches the aircraft and lies on it (rests on the entire surface of the body), located on the foot 8 and manual 10 controls. The invention may include fastening elements of insurance, such as seat belts, which can be made in the middle part of the body. Also on the housing 4 can be made aerodynamic fairing pilot 5 of a transparent material (Fig.7). In addition, at the ends of the four folding wings 3 can be the chassis 13 (fig.ba-bv).

Case 4 has an aerodynamic shape of the wing and can be a hollow carrier structure made of composite materials based on carbon fiber with integrated bearing and fastening elements, as well as elements of rotation of power units, mechanisms for pushing or unfolding wings 3, compartments for control electronics, batteries and rescue parachute of the proposed device. The upper surface of the body-wing 4 is anatomical and may have special grooves and protrusions for comfortable placement of the pilot 5 on the aircraft. The lower surface is a part of the entire aerodynamic surface of the device, which, together with the wings 3 and power units, creates the main lift force during flight with the horizontal position of the hull 4.

The method of flight of an individual aircraft from the vertical position is implemented as follows. The pilot 5 fits vertically standing on the supporting surface of the aircraft (figa 1a-1b and 7), in other words, standing perpendicular to the supporting surface of the aircraft, which relies on the vertical stabilizer and the rear parts of the body, fits (lies) on the body 4 and starts the rotary power aggregates. Then performs a vertical take-off, the power units at the same time rotated parallel to the support surface. Next, by turning the power units in the plane of the housing 4 translates it (housing 4) from the vertical position to the horizontal.

Then you can fly in several modes: in the first mode for flying in different directions - maneuvering - use the thrust distribution of engines 1 and / or variable thrust vector, that is, maneuver by changing the speed of rotation of each engine 1 with propellers 2 and / or changing the positions of each power unit relative to the hull 4. In the second mode, depending on the modification of the proposed device, move two wings 3 with flaps 11 or four wings 3 with flaps 11 and elevators 12 and fly, maneuvering using the rudder 6, flap 11 (for the version with two sliding wings 3) or flap 11 and the elevators 12 (for the variant with four folding wings 3), however, you can maneuver by changing the speed rotation of each engine 1 with propellers 2 and / or changing the position of each power unit relative to housing 4. Depending on the desired direction of flight, use one thing, all together or a combination of several of the above maneuver devices that is obvious to a person skilled in the art.

All control of the aircraft is carried out through manual 10 and foot 8 controls.

Landing of an individual aircraft is carried out similarly to take-off, in the reverse sequence of control actions.

The method of flight of an individual aircraft from a horizontal position on the supporting surface, i.e. As noted earlier, the position in which LA stands on the ground on four folded folding wings 3 directly or on the chassis, made at their ends, is implemented as follows. The pilot approaches the aircraft, rests on his body 4 and starts the power units. Then, it performs a vertical take-off or a horizontal take-off on the chassis along the bearing surface, while turning the power units in proportion to the formation of lift and speed.

After takeoff, you can fly in several modes: in the first mode, for flying in different directions — maneuvering — use the thrust distribution of engines 1 and / or a variable thrust vector, that is, maneuver by changing the speed of rotation of each engine 1 with propellers 2 and / it changes in the position of each power unit relative to hull 4. In the second mode, four wings 3 are deployed with flaps AND and elevators 12 and fly, maneuvering, that is, changing the direction of flight, by changing rotational speeds of each engine 1 with propellers 2 and / or changes in the position of each power unit relative to the hull 4, as well as using the rudder 6, flap 11 and elevators 12. Depending on the desired direction of flight, use one thing, everything together or a combination of several of the above devices for maneuvering, which is obvious to a person skilled in the art.

Landing of the proposed aircraft in this way is carried out similarly to take-off, in the reverse sequence of control actions.

Thus, an individual aircraft of vertical or horizontal take-off / landing is proposed, which depends on the choice of the pilot when modifying the device with four folding wings. On such a device, you can fly with and without wings, depending on the flight conditions and the desire of the pilot. In particular, in both methods, with the wings spread apart or spread out 3 and the achievement of a certain horizontal speed, the power units can be rotated vertically, which will allow flight according to the type of aircraft (FIG. 3-Sv). You can change the flight direction - maneuver - using the thrust distribution of engines 1, rudders 6, flaps 11 or flaps 1 1 and elevators 12. On the ground, in an upright position, the aircraft with folded wings takes up little space, thereby ensuring its compactness.

The proposed solution works by the methods described above.

An individual aircraft may have the following characteristics. The body together with the power units may have a length of about 2.4 m, and between the axes of the lateral power units ~ 1.7 m. The distance between the axes of the power units at the front or rear ends is ~ 1.15 m. The width together with the wings spread out or spread ~ 3.7 m, without wings ~ 1.9 m. The diameter of the protective casing of the power unit is ~ 0.7 m.

The realized version of the aircraft has a weight of about 100 kg with batteries and without a pilot. The thrust of the four engines of about 300 kg. The payload (weight of the parachute pilot) is about 100 kg. Flight time can be from 30 to 60 minutes, depending on the flight modes. Flight range in quadrocopter mode from 50 to 100 km, in airplane mode about 300 km. These characteristics are estimates, cannot and should not narrow the claimed scope of rights.

Thus, an individual aircraft has been created, the use of which provides improved usability due to compactness, higher aerodynamic characteristics due to reduced frontal resistance and improved aerodynamic stability, which is achieved due to the shape of the hull, the location of power units and the ability to use wings. It also provides enhanced functionality of the aircraft due to various take-off / landing options and flight modes.

Claims

Claim.

1. An individual aircraft containing an X-shaped body 4, two sliding wings 3, fitted with flaps 11 and fixed on the front ends of the body 4 with the possibility of rotation along an axis perpendicular to the plane of the body 4 in the place of their attachment, or four folding wings 3 fixed on the front ends of the housing 4 with flaps 11 and on the rear ends with the rudders of height 12 and made with the ability to fold into the plane of the housing 4 from a position perpendicular to the plane of the housing 4, a vertical stabilizer equipped with a rudder 6, manual 10 and foot 8 controls located in the front and rear parts of the body 4, respectively, and four power units, made rotatable and fixed to the ends of the body 4 so that the power units of one side are symmetrically located relative to the longitudinal axis of the body 4 power units of the other side, each power unit is an engine 1 with propellers 2 in a protective casing 7, while the body 4 is designed to accommodate the pilot on it uu, wherein the pilot frontal plane parallel to the plane of the housing 4.

2. The aircraft according to claim 1, in which the aerodynamic fairing of the pilot is made on the front of the body 4.

3. The aircraft according to claim 1, in which the body 4 is provided with fastener elements-pilot insurance.

4. The aircraft according to claim 1, in which the ends of the four folding wings 3 are chassis.

5. The method of flight of an individual aircraft, including the vertical take-off of the aircraft, the body 4 of which is located vertically relative to the supporting surface and is arranged to accommodate the pilot on it in a position in which the pilot's frontal plane is parallel to the plane of the body 4, then by turning the power units into the plane body 4 translate it from a vertical position to a horizontal one, or either fly, maneuvering by changing the speed of rotation of each engine 1 s Air screws 2 of the power unit and / or changing the position of each power unit relative to the body 4, or pushing the two wings 3 with the flaps 11 or spreading the four wings 3 with the flaps AND and the elevators 12 and flying, maneuvering with something one, all a combination or several of the following: changes in the speed of rotation of each engine 1 with propellers 2, changes the position of each power unit relative to the body 4, the rudder 6 on the vertical stabilizer, flap 1 1, elevator 12.

6. The method of flight of an individual aircraft, including the take-off of an aircraft standing on a supporting surface on four folded folding wings 3 directly, or on a chassis made at their ends, in a horizontal position, while the body 4 of the aircraft is adapted to be placed on it the pilot in a position in which the frontal plane of the pilot is parallel to the plane of the body 4, then either fly, maneuvering by changing the speed of rotation of the engine 1 with propellers 2 each power unit and / or changing the position of each power unit relative to body 4, or spread wings 3 with flaps 11 and elevators 12 and fly, maneuvering with the help of something one, the entire set or a combination of several of the following: changes in the speed of rotation of each engine 1 with propellers 2, changing the position of each power unit relative to the body 4, rudder 6 on the vertical stabilizer, flap 1 1, elevators 12.

7. The method according to claim 6, in which the vertical takeoff.

8. The method according to claim 6, in which the horizontal takeoff.