RU2617014C1 - Aircraft - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: aircraft includes a housing formed as a disc-shaped rotation body, wherein the propulsion device is an annular fan wheel which creates a main lift, and an air-jet engine (AJE) of opposite rotation. The annular fan wheel has controlled blades. The aircraft comprises of the first blade apparatus, which guides the air flow, and the second blade apparatus that provides straightening the air flow ejected by the fan wheel. The housing is designed to accommodate control cabins, control systems, landing systems and fan wheel drives. The air-jet engine is configured to provide two functions including generating electric power for the drive of the fan wheel, control systems and electric power consumers installed on board the aircraft, and is also configured to provide an additional lift in start-up or hover mode using a swiveling nozzle.

EFFECT: increased security, flexibility and reliability in the operation of the aircraft.

4 cl, 1 dwg

Description

Technical field

The present invention relates to the field of aircraft (LA) and can serve as an alternative to a helicopter fleet.

State of the art

Aircraft are known, disclosed, for example, in patents RU 2495795, published April 10, 2005 and RU 2348567, published March 10, 2009, the hull of which is made in the form of bodies of revolution. Moreover, the cockpit, control systems, landing systems are located inside the hull.

Known aircraft have a number of significant drawbacks, namely, they have an unreliable and complex design.

Disclosure of invention

The aim of the present invention is to provide an aircraft in which a sparing mode of operation of the blades of the fan wheel (VK) is provided, unlike the blades of a helicopter, since a swash plate is not used and a larger number of blades of the fan wheel (VK) reduce the voltage in the blades.

The technical result consists in increasing the reliability of the operation of the aircraft, as well as its safety and maneuverability.

The specified technical result is achieved in that the aircraft contains a casing made in the form of a disk-shaped body of revolution, in which ring fans are used as the propulsors connected to the casing, creating the main lifting force, and an air-jet engine (WFD) of opposite rotation, and the ring the fan wheel (VK) has controllable blade vanes, while the aircraft also comprises a first blade apparatus directing air flow to the blade vanes of the VK, and a second vane apparatus for rectifying the air flow discharged by the VC, the lenticular housing being able to accommodate the cockpit, control system, landing system and drive the fan wheel, the jet engine is configured to provide two functions, including generating electricity for driving the fan wheel , control systems and electricity consumers installed on board the aircraft, and is also configured to provide For further lifting thrust on the starting mode or hover mode by means of rotary nozzle thereby providing a further mode of propulsion thrust.

In the claimed invention, to ensure exchange rate stability, the principle of equal momentum of the moment of force of the fan wheel and the jet engine is used, controlled by the on-board computer with a coaxial arrangement of propulsion devices (for example, as in a helicopter). Flight control is additionally carried out by pitch and roll control windows, by passing air from the dorsal region to the dorsal region.

In one embodiment of the claimed invention, the fan wheel is driven by three drives, each mounted on a three-pointed star-shaped power beam in the body of the aircraft.

In another of the options, if you need to place more drives, they are installed either on the power ring, or, for example, 4 drives on an X-shaped beam.

Brief Description of the Drawings

In FIG. 1 shows a general view of an aircraft.

The implementation of the invention

The proposed aircraft has the appearance of a "flying saucer." The apparatus has a circular disk-shaped body, in which an annular fan wheel 2 with controlled vanes-blades located between the inner and outer rims of the VK, creating the main lifting force, and an air-jet engine (WFD) of the opposite rotation are used as a propeller 4 - coaxial circuit, a guide vane apparatus 1, which improves the parameters of the air flow entering the VK, a second straightening vane apparatus 3, which organizes the air flow after the VK, a round cranial fuselage (in figure edstavlen as a flat), in which are arranged cockpit 7 (shown in Figure 2 pilots), control systems, landing systems 8 (telescopic strut) fan wheel drive (PVK) 6.

WFD 4 has two functions: generating electric power for PVC and for control systems, as well as other consumers of electric power, and creating additional lifting thrust at the starting or hovering mode and with the help of a rotary nozzle creating a marching thrust. To ensure the exchange rate stability mode, the principle of equality of the momentum of the torque of the VC and the WFD, controlled by the onboard computer, is used. Controlled mismatch of rotation allows you to choose the course of flight. Other flight control functions are carried out by control windows 6 pitch and roll bypass air from the dorsal region to the dorsal or other special control methods.

The proposed flight of the aircraft is as follows: 1) initially the aircraft is on the ground with the help of retractable landing gears 8, 2) the WFD 4 is launched with a rotary nozzle 5 with the thrust vector set vertically, 3) upon receipt of the necessary electric power of the PVC, which can be either gear type and hydraulic type (in the figure their number is 3 pcs.), spin the fan wheel 2, while the WFD 4 and VK 2 rotations, carried out in opposite directions, are controlled by the control system, ensuring equal in the moments of rotation. The air flow passing through the guide vanes 1 is sucked in by a fan wheel 2 with installed adjustable vanes, similar to the shortened rotor blades of the helicopter (the number of vanes is determined experimentally) in the “lift” mode and, passing through the straightening air flow vanes of the second vanes 3 , creates the aircraft lift force together with the WFD 4, 4) when climbing, the landing gear 8 is removed and a negative aircraft pitch is set to start the marching movement, 5) to select of the required marching mode, the nozzle is rotated 5 to 90 ° to the axis of the aircraft; 6) aircraft maneuvering is carried out: along the course - by mismatching the torque of the WFD, by pitch - by opening-closing the front control windows 9 and by turning the nozzle 5, by roll - by opening-closing left or right pair of windows 9 of the aircraft.

Moreover, according to FIG. 1, the rotation of the fan wheel occurs around the cockpit structure, i.e. the cockpit is located in the central part of the aircraft.

The use of this invention provides a more sparing mode of operation of VK blades, in contrast to helicopter blades, since a swash plate is not used and a larger number of VK blades reduce stress in the blades. In this case, the blades are located inside the rim of the fan wheel and the body of the aircraft and cannot be destroyed when the aircraft comes into contact with trees, houses, power lines, etc. In addition, in case of an emergency in flight, it is easier to organize the evacuation of the flight crew (there are no chopping blades of the helicopter ), and the device itself is capable of parachuting, providing a non-rigid landing, while the controlled blades VK 2 can be installed in a transverse air flow position. The device of the proposed device allows you to install standard rescue parachutes. The streamlined shape of the "flying saucer" and the rotary nozzle make it possible to obtain speeds more substantial than those of helicopters.

Claims (4)

1. Aircraft comprising a housing made in the form of a disk-shaped body of revolution, and propulsors connected to the housing, characterized in that the propellers use an annular fan wheel that creates the main lifting force, and an air-jet engine (WFD) of opposite rotation, moreover, the annular fan wheel (VK) has controllable blade vanes, while the aircraft also contains a first blade apparatus directing air flow to the blade vanes of the VK and a second blade app the ratchet, which ensures the rectification of the air flow discharged by the VK, the hull being able to accommodate the cockpit, control system, landing system and fan wheel drive, the jet engine is configured to provide two functions, including generating electricity for driving the fan wheel, control systems and electricity consumers installed on board the aircraft, and is also configured to provide additional lifting thrust to the launch pad mode or hover mode by means of rotary nozzles providing traction on marching mode. 2. Aircraft according to claim 1, characterized in that a coaxial arrangement of the propulsors is applied, in which the propulsors differ in thrust and are spaced from each other. 3. Aircraft according to claim 1, characterized in that to ensure the course stability mode, the principle of equal momentum of the moment of force of the fan wheel and the jet engine controlled by the on-board computer is used. 4. The aircraft according to claim 1, characterized in that the flight control is also carried out by control windows that are installed on the aircraft body in its dorsal and ventral regions, moreover, the air is transferred from the dorsal region to the ventral region.

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