RU2534112C1 - Vertical take-off and landing aircraft - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: this aircraft comprises lifting device, fuselage, parachute-type rescue system, side supports, outer beams to support elevators and rudders and rear legs connecting the fuselage to lifting device. Lifting device consists of nacelle arranged atop said fuselage to house the propeller arranged ahead of or behind the grid wing (multiplane). Said grid wing features negative extension of profile elements that vary the angle of attack around transverse axis to turn about lengthwise axis to create the lift larger than or commensurable with propeller thrust. Power plane is articulated with said propeller and extra generator. Nacelle varies its position by turning about crosswise axis. Fuselage is composed of streamlined airframe to house aircraft payload and systems. Outer supports arranged at fuselage nose have two undercarriage front legs.

EFFECT: improved manoeuvrability, higher reliability.

10 cl, 5 dwg

Description

The invention relates to aviation, and in particular to devices designed to provide vertical take-off and landing, moving in the horizontal plane, moving on hard surfaces.

From the prior art, a vertical take-off and landing aircraft is known as VTOL, in which jet engines are extended beyond the front edge of the wing and have a rotary nozzle nozzle of a slotted type, and is also equipped with a nozzle guide device aimed at blowing the wing (see RF patent No. 2406652, B64C 29/00, 09/10/2009).

A disadvantage of this type of apparatus is the low magnitude of the generated lifting force, since most of the jet stream is scattered in the space around a single wing due to the distance of the source of the high-speed jet and only a small part of it is blown. Engines are positioned horizontally, and traction from engines is not involved in creating vertical force.

Also known apparatus having a jet engine slotted air collector, in the cavity of which is located the inner wing (see RF patent No. 2389653, B64C 29/00, 05/20/2010).

This feature of the analogue at the possible speeds of the air flow relative to a single wing cannot realize vertical take-off and landing, but can only serve as a means of creating additional lifting force of the device. Engines are only involved in creating horizontal traction. The input device to the engine is basically designed to direct and equalize the flow at the engine inlet. Any additional disturbances and uneven flow will lead to unstable operation of the gas turbine engine.

Also known is an aircraft in which forcedly blown, aerodynamic surfaces are placed in air intake channels located along the perimeter of the hull and radially converging into a trough-shaped cavity open downward (see Patent No. 2172705, B64C 29/00, 08/27/2001, Bull. No. 24) .

The disadvantage of the prototype is the large relative mass of the structure when creating the proposed disk-shaped body. Traction forces from the screws do not participate in the creation of vertical lifting force and cancel each other out. Complex propeller installation.

Also known is an aircraft with a lattice wing designed according to the aerodynamic design of the blade lattice of the compressor impeller in relative motion. The wing consists of two keel posts mounted with the possibility of rotation in a vertical plane and between which rotary profile elements with a negative offset are located. When the wing is raised, the polyplane is converted into an aircraft, and when it is lowered, into a land vehicle (see RF patent No. 2025295, B60F 5/02, 12/30/1994).

One of the variants of the method for calculating the geometry of the trellised wing is shown. Flight of the aircraft is possible only at a certain translational speed, vertical take-off from a place is impossible.

Also known aircraft vertical takeoff and landing. The aircraft contains an air flow generator in the form of counter-rotating fans, aerodynamic surfaces, a cabin, a power plant, control and stabilization systems. Aerodynamic surfaces are gratings of a multifaceted wing installed at a positive angle of attack relative to the forced air flow. The rectangular parts of the duct are connected with sockets to the ring in which the fans are located. At least two gratings of a multifaceted wing are installed in the rectangular part of the duct (see RF patent No. 2459746, B64C 29/00, 08/21/2012).

The disadvantages of the prototype are the large relative mass of the structure, the mode of hovering in place is impossible. Changing the direction of flow after multifaceted wings, the effect of flow on the air duct leads to the appearance of centrifugal forces directed against the lifting force of the wings, which can make take-off impossible, fans do not participate in creating vertical lifting force, which requires a significant increase in the power of the propulsion system.

The aim of this invention is to provide a compact, simple and reliable vehicle for movement in any direction, both in an urbanized environment and in areas with no infrastructure.

This problem is solved due to the fact that the claimed vertical take-off and landing apparatus contains a lifting device (PU), a fuselage, a parachute rescue system, remote consoles, remote beams with an elevator, rudders and rear landing gears located on them, connecting the fuselage to a lifting device, and the lifting device consists of a gondola located on top of the fuselage, with a screw installed in it, located before the trellised wing (polyplane) or after the trellised wing (polyplane), trellised wing (polyp anom), with a negative extension of the profile elements, changing the angle of attack around the transverse axis and rotating around the longitudinal axis, creating a lifting force that is larger in magnitude or commensurate with the propeller thrust, a power plant kinematically connected with the propeller and an additional generator, at the same time the gondola changes its position by rotation around the transverse axis, while the entire high-speed flow from the propeller passes through the trellised wing (polyplane) and all elements of the trellised wing (polyplane) are under high-speed flow from the propeller, and the fuselage is a streamlined body where the payload and necessary systems of the device are located, and the parachute-rescue system, designed to save the device and payload in case of engine failure, is located in the upper part of the nacelle, and the remote consoles, located in front of the fuselage, have front landing gear legs at the ends.

The screw is a fan heater.

The line of action of the resulting aerodynamic force on the trellised wing, the line of action of the thrust force from the propeller, and the transverse axis of rotation of the nacelle intersect at one point.

On the chassis supports, wheels are installed, closed by fairings, having a braking system and rotary mounted on remote consoles.

The wheels on the remote consoles have built-in electric motors.

It is possible to break the kinematic connection of the power plant with the screw.

It is possible to connect and disconnect an additional generator to the power plant.

The lifting coefficient of the lattice in the angle of attack of the wing (polyplane) is 2.0 and higher.

Remote consoles are made in the form of aerodynamic surfaces and provide additional lifting force and balancing of the device in horizontal flight.

The lifting device has the ability to move relative to the fuselage in the longitudinal and transverse directions.

The technical result provided by the given set of features is a vertical take-off and landing apparatus, the properties of which allow moving forward, backward, sideways, upward, downward with a payload in the air without changing and with a change in the longitudinal axis of the apparatus, moving along a solid surface of the earth, taking off and sit on unprepared surfaces.

The invention is illustrated by schematic drawings of an apparatus for vertical take-off and landing:

figure 1 - General view of the apparatus of vertical take-off and landing;

figure 2 is a longitudinal section (layout Option 1);

figure 3 is a longitudinal section (layout Option 2);

figure 4 - Diagram of the action of forces in horizontal flight;

figure 5 - Scheme of action of forces in the modes of vertical take-off, hovering and landing.

The vertical take-off and landing apparatus comprises a lifting device (PU) 1, a fuselage 2, a parachute rescue system 3, remote consoles 4, remote beams 5 with an elevator 7 and rudders located on them 8. The lifting device consists of a gondola with installed screw 9, trellised wing (polyplane) 6, power plant 10.

The apparatus of vertical take-off and landing as follows.

The rotation of the screw creates traction. The entire high-speed flow from the screw is directed to the trellised wing (polyplane). As a result of interaction with the flow, we obtain lift on the wing. The lattice wing (polyplane) has the ability to change position (angle of attack) relative to the incoming air flow from the propeller in a vertical plane, the ability to rotate relative to the longitudinal axis of the nacelle. Changing the position of the wing allows you to change the magnitude of the lifting force, to obtain a transverse force to change the direction of movement of the apparatus without changing the position of the longitudinal axis of the apparatus. This design feature allows you to have wide maneuvering capabilities both at the take-off and landing stages, and at the horizontal flight stage.

A feature of the operation of the lifting device as part of the apparatus is the joint operation of the screw and wing to create total effort. Rotating the lifting device in a vertical plane allows you to set the desired mode of movement of the aircraft from horizontal flight forward with the creation of horizontal traction from the propeller and lifting force from the wing to vertical movement or movement back or sideways while creating vertical and horizontal forces from the screw and wing. The point of application of the resultant force from the lifting device does not change its position. The center of gravity of the apparatus is below the point of application of the resultant force from the lifting device. Thus, an aerodynamically stable scheme is obtained, regardless of disturbances, the system will tend to its original position (pendulum principle). Such a scheme greatly simplifies the piloting of the device.

Before takeoff, the pilot rotates the lifting device to the required angle (take-off position). Increasing engine speed, the pilot detaches the apparatus from the surface. By changing the position of the lifting device and the position of the wing, the pilot fights off the effects of gusts of wind on the device. With a decrease in the installation angle of the lifting device, the apparatus accelerates. When installing the lifting device at an angle greater than the take-off, the device brakes.

Take-off and landing of the device are made when the entire lifting device is deflected in a vertical plane by an angle determined by the aerodynamic perfection of the trellised wing. To move on the ground, the pilot turns off the screw and connect an additional generator. Electric motors in the wheels betray power to the wheels. The control of the device when moving on the ground is no different from driving.

Claims (10)

1. The vertical take-off and landing apparatus is characterized in that it contains a lifting device (PU), a fuselage, a parachute rescue system, remote consoles, remote beams with a rudder and rudders located on them and rear landing gears connecting the fuselage to the lifting device, and the lifting device consists of a nacelle located on top of the fuselage, with a screw installed in it, located before the trellised wing (polyplane) or after the trellised wing (polyplane), trellised wing (polyplane), with a negative the removal of profile elements, changing the angle of attack around the transverse axis and rotating around the longitudinal axis, creating a lifting force greater in magnitude or commensurate with the thrust of the screw, a power plant kinematically connected with the screw and an additional generator, at the same time, the nacelle changes its position by rotation around the transverse axis, while the entire high-speed flow from the screw passes through the trellised wing (polyplane) and all elements of the trellised wing (polyplane) are under the action of the high-speed out of the propeller, and the fuselage is a streamlined body, where the payload and the necessary systems of the device are located, and the parachute-rescue system, designed to save the device and payload in case of engine failure, is located in the upper part of the nacelle, and the remote consoles located in the front of the fuselage, have at the ends of the front landing gear. 2. The apparatus of vertical take-off and landing according to claim 1, characterized in that the screw is a fan heater. 3. The vertical take-off and landing apparatus according to claim 1, characterized in that the line of action of the resulting aerodynamic force on the trellised wing, the line of action of the thrust force from the screw, the transverse axis of rotation of the nacelle intersect at one point. 4. The apparatus of vertical take-off and landing according to claim 1, characterized in that the wheels of the chassis are fitted with wheels closed by fairings having a braking system, rotary mounted on remote consoles. 5. The apparatus of vertical take-off and landing according to claim 1, characterized in that the wheels on the remote consoles have built-in electric motors. 6. The vertical take-off and landing apparatus according to claim 1, characterized in that it is possible to break the kinematic connection of the power plant with the screw. 7. The vertical take-off and landing apparatus according to claim 1, characterized in that it is possible to connect and disconnect an additional generator to the power plant. 8. The vertical take-off and landing apparatus according to claim 1, characterized in that the lift coefficient of the trellised wing (polyplane) in terms of angle of attack is 2.0 and higher. 9. The vertical take-off and landing apparatus according to claim 1, characterized in that the remote arms are made in the form of aerodynamic surfaces and provide additional lifting force and balancing of the apparatus in horizontal flight. 10. The vertical take-off and landing apparatus according to claim 1, characterized in that the lifting device has the ability to move relative to the fuselage in the longitudinal and transverse directions.

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