RU2258637C1 - Hybrid flying vehicle - Google Patents

Abstract

FIELD: lighter-than-air flying vehicles for aerostatic and aerodynamic flights.

SUBSTANCE: proposed flying vehicle has frame and envelope designed for creating aerostatic lifting force; it is mounted for rotation relative to frame; flying vehicle is provided with blades mounted on envelope in radial direction from axis and used for creating aerodynamic lifting force; flying vehicle is also provided with engine plant for rotation of envelope, tail boom equipped with reaction torque compensating unit and payload compartment. Engine plant includes hydrogen tank and at least two ramjet engines; each engine is mounted on envelope.

EFFECT: reduction of danger of contamination of environment.

7 cl, 2 dwg

Description

The invention relates to aircraft lighter than air, combining the principles of aerostatic and aerodynamic flight.

A hybrid aircraft is known, some of the gas compartments of which are filled with hydrogen as a gas lighter than air to create aerostatic lifting force / USSR Copyright Certificate No. 1740250, B 64 B 1/06, 1992 /.

The disadvantages of the known hybrid aircraft are large overall dimensions and the need to use ballast to control the lifting force.

Also known is a hybrid aircraft containing a frame, a shell designed to create aerostatic lifting force, made with an axis of symmetry and mounted to rotate relative to the frame, blades mounted on said shell mainly in the radial direction from the axis and designed to create aerodynamic lifting force, a propulsion system designed to rotate said shell; a tail boom having reactive torque compensation means -mentioned shell, and the payload bay / U.S. Patent №3976265, B 64 C 37/02, 1976 /.

The device combines the principles of aerostatic and dynamic flight, but hydrocarbon fuel is used for the operation of the propulsion system, when burned, harmful chemical compounds are formed in the engines, which pollute the atmosphere to the greatest extent during transient modes of operation when receiving cargo on board within a limited size area within settlement.

The objective of the invention is the use of hydrogen as fuel for the engines of a hybrid controlled aircraft designed to transport people and compact cargo while reducing the risk of environmental pollution.

The objective of the invention is the use of compartments with helium and hydrogen as gases lighter than air to create aerostatic lifting force, equal in magnitude to the weight of the mechanisms and design of the aircraft.

To solve the problem, a hybrid aircraft is proposed, comprising a frame, a shell designed to create aerostatic lifting force, made with an axis of symmetry and mounted to rotate relative to the frame, blades mounted on said shell mainly in the radial direction from the axis and designed to create an aerodynamic lifting forces, a propulsion system designed to rotate said shell, a tail boom having reactive moment compensation means ie rotation of said shell, and the payload bay.

A propulsion system includes a hydrogen tank and at least two engines, each of which is mounted on said shell, in the cavity of which said hydrogen tank is located.

Each engine is a direct-flow jet engine.

The blades are mounted with the possibility of rotation relative to the longitudinal axis located in the radial direction from the axis of the shell.

Inside the shell are units for controlling the supply of hydrogen to the engines.

The payload compartment is made in the form of a cabin, which is mounted on a rack of the frame, made in the form of a support for rotation of the outer shell.

The frame is made with three rods, at the ends of which landing bearings are installed.

The shell is located between the cab and the booms of the frame.

The invention is illustrated by drawings.

Figure 1 is a General view of a hybrid aircraft.

Figure 2 - the location of the engines on the shell.

The hybrid aircraft contains a frame 1, a shell 2, designed to create aerostatic lifting force, made with an axis of symmetry 3 and mounted for rotation relative to the frame 1, the blades 4 mounted on the said shell 2 mainly in the radial direction from the axis 3 and designed to create aerodynamic lifting force, a propulsion system designed to rotate said shell 2, a tail boom 5 having means 6 for reactive torque compensation from rotation is mentioned th shell 2, and compartment 7 payload.

The propulsion system includes a hydrogen tank 8 and eight engines 9, each of which is mounted on said shell 2, in the cavity of which said hydrogen tank 8 is located.

Each engine 9 is a ramjet engine.

The tank 8 is made in the form of a toroidal shell located inside the shell 2, made in the form of a flattened ellipsoid of revolution.

The blades 4 are mounted on the outer surface of the shell 2 with the possibility of rotation relative to the longitudinal axis located in the radial direction, perpendicular to the axis 3 of the shell 2.

Inside the shell 2 are units for controlling the supply of hydrogen to the engines 9.

The payload compartment 7 is made in the form of a cabin, which is mounted on the rack 10 of the frame 1, made in the form of a support for rotation of the outer shell.

Frame 1 is made with three rods 11, at the ends of which landing bearings 12 are installed.

The toroidal shell of the tank 8 and the shell 2 form a rigid structure, which by means of a hinge 13 is mounted on the rack 10 so that the shell 2 is located between the cab of the payload compartment 7 and the rods 11 of the frame 1.

The hinge 13 is located in the hole of the toroidal shell of the tank 8 and is connected to it by rods 14.

When the engines 9 are working together with the shell 2, the blades 4 rotate, creating aerodynamic lifting force.

Changing the angle of attack of the blades 4, control the magnitude and direction of the aerodynamic lift.

By controlling the total or cyclic pitch of the blades 4, provide the flight of the apparatus forward or backward, left or right.

Claims (7)

1. A hybrid aircraft containing a frame, a shell designed to create aerostatic lifting force, made with an axis of symmetry and mounted to rotate relative to the frame, blades mounted on the said shell mainly in the radial direction from the axis and designed to create aerodynamic lifting force, a propulsion system designed to rotate said shell; a tail boom having means for reactive moment compensation from rotation of said shell hibernation, and the payload compartment, characterized in that the propulsion system comprises a tank for hydrogen and at least two motors, each of which is mounted on said casing, which is located in the cavity, said hydrogen tank. 2. The hybrid aircraft according to claim 1, characterized in that each engine is a ramjet engine. 3. The hybrid aircraft according to claim 1, characterized in that the blades are mounted with the possibility of rotation relative to the longitudinal axis located in the radial direction from the axis of the shell. 4. The hybrid aircraft according to claim 1, characterized in that inside the shell are units for controlling the supply of hydrogen to the engines. 5. The hybrid aircraft according to claim 1, characterized in that the payload compartment is made in the form of a cabin, which is mounted on a rack of the frame, made in the form of a support for rotation of the outer shell. 6. The hybrid aircraft according to claim 5, characterized in that the frame is made with three rods, at the ends of which landing bearings are installed. 7. The hybrid aircraft according to claim 1, characterized in that the shell is located between the cabin and the rods of the frame.

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