RU2621825C1 - Device for ascentional force generation - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: aircraft contains an even number of paired elements. Each element includes a rotor with blades and a rotor axis with a conical rotor gear. In each pair of elements an internal combustion engine with a shaft or an electric motor with a shaft is mounted, conical shaft gears are placed on shaft, which are configured to transfer the rotation of shaft of internal combustion engine or electric motor to the vertically placed rotor axis through conical rotor gears.

EFFECT: increasing reliability and durability of device, increasing efficiency.

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Description

The invention relates to the aircraft industry. The claimed device relates to means creating a lifting force, and can be used both in lifting devices and in aircraft, which are heavier than air and use engine power. The invention can be used in aircraft with vertical take-off and landing.

The prior art method of creating a lifting force, which use a circular, stationary horizontal surface, which is the bearing plane. Above it, using a jet of gas from a jet engine, a gas-air flow is generated, which is directed uniformly from the center in all directions in such a way that it contacts the surface only in its peripheral part, creating a closed space between the surface and the gas stream, in which an ejection is created some rarefaction, which due to the pressure difference under the plane and above it creates a lifting force (US patent No. 5031859).

The described method is implemented by a device comprising a housing with a bearing flat horizontal surface and means for creating a closed volume with reduced pressure above this surface, made in the form of a jet engine, the nozzle apparatus of which is made with an annular slot placed with a ledge above the middle part of this surface, so that between it and the gas stream creates a closed volume with reduced pressure (US patent No. 5031859).

The main disadvantage of this device is that the use of a hot air-gas mixture from a jet engine at the time of take-off and landing will require a lot of fuel, since the lifting force of the wings is excluded without translational horizontal speed, and jet gases will have to be used not at a height like jet aircraft, but above ground, at an aerodrome or ship.

There is also a known method of creating a lifting force by lowering the pressure in a closed volume above the bearing surface in the presence of atmospheric pressure under it, due to the difference of which a lifting force occurs. A closed volume is formed by blocking the upper open part of the chamber with a flat stream of liquid. (RU 2260545, IPC B64C 21/02, B64C 29/00, 09/20/2005).

A device for creating a lifting force is known, comprising at least one body with a bearing surface and at least one means for creating a closed volume with reduced pressure over the corresponding surface. Each body is made in the form of a chamber open from above and with a bottom forming a bearing surface, and each means for creating a closed volume is made in the form of a slit-like nozzle connected to the liquid supply means and placed in the upper part of the corresponding chamber with the possibility of creating a flat liquid jet, covering the upper open part of the chamber with the formation of a closed volume in its cavity (RU 2260545, IPC B64C 21/02, B64C29 / 00, 09/20/2005).

The disadvantage of this method and device is that the creation of vacuum in the chamber using a flat jet of liquid does not provide vacuum in the chamber and requires pumping pumps to achieve this application, which complicates the device and increases its weight, reducing its effectiveness. Since the liquid stream does not leave the chamber, but circulates in it, it does not create a lifting force. In order for the rarefaction of air in the chamber to raise the aircraft, the chamber must be several times larger than the aircraft itself.

The problem to which the invention is directed, is to create a design of the device to create a lifting force that would eliminate the above disadvantages.

The technical result achieved by the implementation of the invention is to increase the reliability and wear resistance, as well as to increase the efficiency.

The technical result is achieved in a device for creating a lifting force containing an even number of paired elements. Each element includes a rotor with blades and the axis of the rotor with a bevel gear of the rotor. In each pair of elements, an internal combustion engine with a shaft or an electric motor with a shaft is installed, bevel gears of the shaft are placed on the shaft, configured to transmit the rotation of the shaft of the internal combustion engine or electric motor to the vertically placed axis of the rotor through the bevel gears of the rotor.

The invention is illustrated by drawings. In FIG. 1 shows a device for generating lift; FIG. 2 shows a rotor with blades.

Device for creating a lifting force containing an even number of paired elements. Each element includes a rotor 1 with blades 2 and an axis 3 of a rotor 1 with a bevel gear 4 of a rotor 1. An internal combustion engine 5 with a shaft 6 or an electric motor 5 with a shaft 6 is installed in each pair of elements, bevel gears 7 of a shaft 6 are placed on shaft 6, made with the possibility of transmitting the rotation of the shaft 6 of the internal combustion engine 5 or electric motor 5 to a vertically placed axis 3 of the rotor 1 through bevel gears 4 of the rotor 1.

Execution example

The rotor 1 with blades 2 is mounted on top of the body of the aircraft 8 so that between the lower end of the rotor 1 and the surface of the body of the aircraft 8 there is a gap equal to about 2% of the diameter of the rotor 1.

The rotor 1 with the blades 2 can be recessed into the recesses 9 of the aircraft body 8 so that the recesses in the rotor 1 between the vanes 2 are less raised above the surface of the aircraft body 8.

If the number of blades 2 in the rotor 1 is six or more, then the blades 2 of the rotor 1 must be displaced in opposite directions so that the rotors 1 rotate in the opposite direction, while the vortex flows do not inhibit each other.

If four blades 2 are installed in the rotor 1, then the blades 2 must be placed strictly radially.

The claimed device for creating a lifting force can be used for drones, the weight of which is up to 30 kg. The axis 3 of the rotors 1 with blades 2 and the shafts 6 of internal combustion engines 5 or electric motors 5 can be made of steel, bevel gears 4 of the rotor 1 and bevel gears 7 of the shaft 6 are made of composites, the device for creating the lifting force and the body of the aircraft 8 are made of aluminum alloys or composites.

For manned vehicles, materials must be selected according to the load, as in the manufacture of aircraft and helicopters.

The device operates as follows. The blades 2 during rotation of the rotor 1 push air from the recesses between the blades 2 outward in the plane of rotation of the rotor 1, which provides a high degree of pumping of air, while the atmospheric pressure acts only on the inner part of the rotor 1 from the axis 3 of its rotation and on the surface of the upper edge of the blades 2 in the plane of the end face of the rotor 1. The lower part of the body of the aircraft 8 or the lifting device will be pushed up. Depending on the speed of rotation of the rotor 1, its blades 2 will expel air in the plane of rotation of the rotor 1 and beyond, reducing atmospheric air pressure on the upper surface of the aircraft or lifting device, increasing the lifting force. But moving away from the rotor 1, the vortex flow will weaken and be pressed more and more under the influence of atmospheric pressure to the surface of the aircraft body 8 or the lifting device, where the effect of the lifting force will decrease. The lower part of the body of the aircraft 8 or the lifting device will be pushed up in full without change.

Claims (1)

The aircraft, characterized in that it contains an even number of paired elements, each element includes a rotor with blades and a rotor axis with a bevel gear of the rotor, an internal combustion engine or an electric motor with a shaft is installed in each pair of elements, bevel gears of the shaft are made on the shaft, made with the possibility of transmitting the rotation of the shaft of the internal combustion engine or electric motor to the vertically placed axis of the rotor through the bevel gears of the rotor, while the rotors with blades installed over the body of the aircraft so that between the lower end of the rotor and the surface of the body of the aircraft was a gap equal to 2% of the diameter of the rotor.

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