RU2531432C2 - Development of vtol aircraft drive forces and aircraft to this end - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, namely, to VTOL aircraft. proposed method consists in directing of gas jet tangentially to airfoil top convex surface. Outflowing flat pulsating gas jet is formed in transient super sound ejector composed by the system of two inlet channels communicated with constant-area air intake slits atop the airfoil surface, mixing chamber and jet nozzle as discharge slit atop said airfoil. Aircraft comprises airfoil section with top bulged surface. Said transient super sound ejector arranged inside the wing is composed by the set of channels communicating the constant-are air intake slit that makes the cruise inlet and constant-area air intake slit that makes the launch inlet arranged at top point of airfoil section. Airflows are connected in fuel manifold zone while combustion products outflow via slitted nozzle arranged at wing top surface between starting inlet and section trailing edge.

EFFECT: higher efficiency, better aerodynamics.

2 cl, 2 dwg

Description

The invention relates to aviation, and in particular to methods of creating a system of forces and aircraft of vertical take-off and landing and free flight.

A known method of controlling the boundary layer on the aerodynamic surface of an aircraft (RF patent 2015941 from 07.15.1994, B64C 21/08) by suctioning air from the cavities of the vortex cells formed in the aft part of the surface, while during the suction process, the air sampling rate is gradually increased until formation attached vortices, at which the complete attachment of the boundary layer to the aircraft surface is achieved, after which the suction level is reduced to the minimum at which continuous flow around the aircraft surface takes place.

The disadvantages of the method of controlling the boundary layer is a developed system of vortex cells, which complicates the design of the aircraft.

A known aircraft with a control system for suction of the boundary layer, a control system for blowing into the boundary layer (RF patent 2033945 from 04.30.95, B64C 39/10, B64C 29/00, B64C 21/00, B60V 1/00) containing the fuselage in the form carrier wing, a power plant located inside the fuselage, a gas-dynamic boundary layer control system, equipped with a device for optimizing the flow of the working fluid in the process of impact on the parietal section, a device for fixing the position of the flow from the trailing edge, the take-off and landing device in the form of an air ears, which, like the border layer control system, is functionally connected with the motion control system and the power plant, the motion control and stabilization system in the form of nozzle blocks mounted on the side surfaces of the aircraft.

An aircraft with such a boundary layer control system does not have the ability to take off and land vertically.

Known aircraft vertical take-off and landing (RF patent 1709690 from 04/10/1996, B64C 29/00), containing the fuselage, a round wing with a central radial slot nozzle and mechanization, vertical tail and a jet engine mounted on a vertical tail above the top the surface of a round wing, the outlet of the gas generator of which is connected by a pipe to the inlet of the central radial-slot nozzle, from which the gas jets flow out tangentially to the upper surface of the wing.

An aircraft of this design has high drag and low aerodynamic quality.

Closest to the proposed group of inventions relates to a method of creating traction and apparatus for movement in a fluid medium (RF patent 2374133 from 08.25.2008, B64C 21/04), selected as the closest analogue (prototype).

The thrust generation method used in the present invention (Coanda effect) is characterized in that pressure jets of fluid from nozzles moving at an angle relative to the direction of the jets are directed tangentially to the upper convex surface of the wing of the aerodynamic section. This leads to a decrease in pressure in the region of motion of the jets formed when the source of the jet moves at an angle to its direction (“deployed jet”) and, consequently, to the formation of low-pressure jets twisted into a spiral behind the nozzles, which during centrifugal movement to the perimeter of the wing involve a large volume of the surrounding fluid in a swirling motion, significantly reducing pressure above the wing.

Various options are proposed for implementing the thrust generation method (jet outflow and simultaneous rotation of the rotor with nozzles, reciprocating or oscillatory movement of nozzles) in which a system of infinite vortex cords is generated, moving from nozzles to the peripheral part of the wing. Vortex cords during movement capture and carry away large masses of ambient air, which leads to a decrease in air pressure above the wing.

The implementation of the proposed method increases the efficiency of the thrust, providing high speeds.

The disadvantages of the known method of creating traction include:

- difficulties in generating “deployed jets” (rotation of the rotor with nozzles, reciprocating or oscillatory movement of the nozzles);

- the effect on the level of air pressure only above the wing.

A known aircraft that implements the proposed method of creating thrust (RF patent 2374133 from 08.25.2008, B64C 21/04) containing an aerodynamic wing with an upper convex surface, a high pressure source of fluid, interconnected with a means for forming pressure jets from nozzles directed tangent to the upper convex surface of the wing, in which according to the invention it is equipped with a nozzle rotation drive of said means, which is made in the form of a hollow axis rotor mounted coaxially to the longitudinal axis of the wing New with the possibility of forming pressure jets with vortices. Various options for the implementation of the aircraft are proposed, depending on the selected version of the method for creating thrust and a variant of the means for forming pressure jets. These include:

- means for forming pressure jets made in the form of a block of fixed nozzles connected to a pulsating jet engine and simulating the movement of nozzles around a circle with the possibility of forming pressure jets with vortices;

- means for forming pressure jets made in the form of a block installed in the plane of the longitudinal axis of the wing of the wing with a hollow axis and nozzles configured to form pressure jets with vortices and connected to the reciprocating movement mechanism;

- means for forming pressure jets made in the form of bent nozzles articulated and connected to a pulsating air-jet engine, configured to form pressure jets with vortices and to return to their original position by means of springs;

- the means for forming pressure jets is made in the form of fixed nozzles mounted in the plane of the longitudinal axis of the wing of the unit, connected to a pulsating jet engine with the ability to reciprocally change the place of flow of nozzles of pressure jets of a fluid that swirl around the surrounding fluid from the nozzles;

- means for forming pressure jets made in the form of a perpendicular to the longitudinal axis of the wing of the rotor with a hollow axis and nozzles mounted symmetrically on the end face at an angle to the end with the ability to capture vortices of the surrounding fluid pressure jets.

A centrifugal or axial compressor may serve as a source of high pressure fluid, in addition to a pulsating jet engine.

The disadvantages of such aircraft include the following:

- means for forming pressure jets are movable structural elements (rotor with a hollow axis, articulated curved nozzles) requiring the use of a rotation drive or a mechanism for returning the nozzles to their original position;

- in the case of the use of blocks of fixed nozzles, the use of reciprocating movement mechanisms is required;

- sources of high pressure fluid do not allow to obtain a value of the flow velocity above 400 m / s.

Additional mechanisms complicate the design of the aircraft, which can lead to a decrease in the reliability of its operation. The relatively low speed of the pressure jet will not significantly increase the overall efficiency of the transport system, which includes the thermal efficiency of the engine, propulsion, and the generation efficiency of the air stream.

A physical effect is known that allows solving the above problems - “The phenomenon of an abnormally high increase in thrust in a gas ejection process with a pulsating active jet” (USSR discovery No. 314 of July 2, 1951).

The task of the group of inventions is to eliminate these drawbacks and create an aircraft of vertical take-off and landing, more simple in design, more economical, more manageable and reliable in operation.

The task is realized by the method of creating a system of forces for an aircraft of vertical take-off and landing and an aircraft for its implementation.

To increase the overall efficiency and aerodynamic quality of the aircraft, a group of inventions is proposed, united by a single inventive concept.

The group of inventions includes:

- a method of creating a system of forces, consisting in the direction from the nozzle of the gas stream tangentially to the upper convex surface of the wing of the aerodynamic section, characterized in that the flowing out flat pulsating gas jet is formed in a non-stationary supersonic ejector formed by a system of two inlet channels connected with air inlets of constant area located on the upper surface of the aerodynamic profile, the mixing chamber and the jet nozzle in the form of an exit slit on the upper surface of the aerodynamic amicheskogo profile;

- an aircraft containing an aerodynamic wing with an upper convex surface, characterized in that the non-stationary supersonic ejector located inside the wing is formed by a system of channels connecting a constant-area air intake gap, which is a marching inlet device located at the front edge of the profile and an air intake gap of a constant the area, which is the starting intake device, located at the top of the aerodynamic profile; air flows are connected in the area of the fuel manifold, and the combustion products formed in the mixing chamber flow out through a slotted nozzle placed on the upper surface of the wing between the starting intake device and the trailing edge of the profile.

The group of inventions is illustrated by drawings: figure 1 shows a diagram of the organization of the adjacent stream and the attachment of air masses from the environment, and figure 2 shows a longitudinal section of an aircraft.

The proposed method for creating thrust allows the formation of a flat, low-pressure pulsating jet adhering to the upper surface of the wing behind a flat nozzle, which, when draining from the aerodynamic profile, increases circulation around it and involves significant air masses from the environment, increasing pressure under the wing.

This allows you to increase traction efficiency and provide significant lifting speeds. A positive effect is achieved by creating an aircraft more simple in design, more manageable and reliable in operation.

The method of creating a system of forces according to claim 1 consists in the direction from the nozzle of a flat pulsating gas jet 1 tangentially to the upper convex surface 2 of the wing of aerodynamic section 4, while the jet 1 is formed in a non-stationary gas ejector formed by a system of two inlet channels connected with air intake slots a constant area of 5 and 6, located on the upper surface of the aerodynamic profile, the mixing chamber 8 and the jet nozzle in the form of an exit slit 9 on the upper surface of the aerodynamic profile.

The aircraft according to claim 2, according to the method proposed above, comprises an aerodynamic wing 4 with an upper convex surface 2, a non-stationary supersonic ejector located inside the wing, formed by a system of channels connecting a constant-area air intake gap, which is the starting inlet device 5, a constant-area air intake gap, which is a marching inlet device 6, a fuel manifold 7, a mixing chamber 8, a slotted nozzle 9 from which a jet 1 flows, adhering to the surface 2.

The aircraft operates as follows. Air from the environment enters through the starting intake device 5 and the main intake device 6, entering the mixing chamber 8, where fuel is injected from the manifold 7 and where the fuel is ignited. Compression of the working fluid is carried out due to the available energy of the fuel mass in an unsteady supersonic ejector, which allows to increase the thermodynamic efficiency of heat generation during the interaction of chemically reactive jets. The flat pulsating jet 1 flowing through the slot nozzle 9 and the burning mixture of fuel and air adhere to the upper convex surface 2 of the wing under the influence of the Coanda effect. Flowing then from the guide surface of the aerodynamic profile, the jet involves low-velocity air masses 3 and creates the effect of increasing circulation around the profile. In this case, the vertical component of the traction force prevails over the horizontal component.

The outflow process acquires a pulsating character, due to the combination of the periodic locking of the nozzle 9 with the flickering mode of combustion in the mixing chamber 8 and the outer zone of the jet 1.

As the apparatus accelerates due to dynamic pressure, the pressure of the jet flowing through the marching input device 6 increases, and the contribution of the passive flow through the starting intake device 5 decreases. Due to this, at high speed modes, an air gap is formed on the lower wall of the mixing chamber 8 and the jet nozzle 9, sufficient for detaching the jet from the outer surface 2 of the aerodynamic profile, which provides favorable conditions for the expiration in a cruising horizontal flight mode.

Claims (2)

1. The method of creating thrust, consisting in the direction from the nozzle of the gas jet tangentially to the upper convex surface of the wing of the aerodynamic section, characterized in that the flowing out flat pulsating gas jet is formed in a non-stationary supersonic ejector formed by a system of two inlet channels connected with air inlets of constant area located on the upper surface of the aerodynamic profile, the mixing chamber and the jet nozzle in the form of an exit slit on the upper surface of the aerodynamic one profile. 2. An aircraft containing an aerodynamic wing with an upper convex surface, characterized in that the non-stationary supersonic ejector placed inside the wing is formed by a system of channels connecting a constant-area air intake gap, which is a marching inlet device located at the front edge of the profile and an air intake gap a constant area, which is the starting intake device, located at the top of the aerodynamic profile; air flows are connected in the area of the fuel manifold, and the combustion products formed in the mixing chamber flow out through a slotted nozzle placed on the upper surface of the wing between the starting intake device and the trailing edge of the profile.

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