RU2674731C1 - High speed helicopter - Google Patents

Abstract

FIELD: aviation.SUBSTANCE: invention relates to the field of aviation, in particular, to designs of single-screw high-speed helicopters. Helicopter contains a lifting screw, engines, tail boom, rudder. Tail boom has a wing profile located in the air flow from the lifting screw, and is provided with a rotatable aerodynamic surface. Engines have rotary exhaust devices with the ability to change the thrust from the side opposite to the direction opposite to the direction of flight, while changing the direction of thrust is performed synchronously.EFFECT: provided increase in the speed of the helicopter.1 cl, 2 dwg

Description

The technical field to which the invention relates.

The invention relates to the field of aircraft construction, in particular to single-rotor helicopters, and can be used for a helicopter of increased flight speed.

The prior art and the background of the invention.

At present, in the aircraft industry, a helicopter arrangement is widely used, comprising a fuselage, a lifting screw, a tail boom with a variable pitch steering rotor, engines and a power transmission with shafts and intermediate gears [1].

Well-known analogues of helicopters of this type are the helicopters described in the book [2] or in the RF patent for the invention [3]. Such, for example, are commercially available Mi-24, Mi-35, Mi-28, AL-64 Apache helicopters (and their modifications).

Currently, work is underway in Russia and abroad to create helicopters of increased flight speed. These machines include helicopters that support cruising speeds of 350 km / h and higher.

It is known from open sources [4] that the Flight Laboratory of a promising high-speed helicopter (LL PSV), which is an experimental aircraft based on the Mi-24 helicopter and having improved aerodynamic characteristics, is being tested in Russia. The power plant of the helicopter consists of two turboshaft engines. Chassis retracts in flight.

Some elements of the fuselage of the flying laboratory have been finalized, which "significantly reduces air resistance and improves the aerodynamics of the helicopter at high flight speeds" [4].

One of the main tasks in the implementation of LL PSV is to obtain experimental data on the use on helicopters of new whole composite rotor blades created at the plant named after M.L. Mile [4]. These blades have improved aerodynamic characteristics and are created using the latest developments in the field of aerodynamics, strength, composite materials science.

The above-described domestic apparatus LL LL PSV can be considered as an analogue of the invention.

The disadvantages of such a scheme include the complexity of the device and the need for power take-off to drive the tail rotor.

In addition, the flight speed of such a helicopter is limited by the permissible speed of flow around the blades.

One of the problems that prevent the achievement of increased flight speed is the presence of a tail rotor, which creates additional vibrations, requires a complex transmission, takes part of the power and creates a number of other problems. For helicopters of increased flight speed, the use of a tail rotor is highly desirable.

The general technical problem solved by the patented invention is to provide increased helicopter flight speed

Disclosure of the invention.

The proposed helicopter contains a lifting screw, engines, a tail boom, a rudder and is characterized in that the tail boom has a wing profile located in the air stream from the rotor and is equipped with a rotatable aileron, the engines have rotary exhaust devices with the ability to change the thrust from the side opposite to the direction is opposite to the direction of flight, and the change in thrust direction is performed synchronously.

The proposed helicopter allows you to perform horizontal flight at a speed exceeding the flight speed of serial helicopters, while takeoff and landing can be performed vertically. In addition, the presence of a tail boom in the form of a wing located in the air stream from the lift screw allows you to compensate for the reaction from the rotation of the screw and dispense with the tail rotor (and the problems it creates with increased flight speed), as well as save the power of the power plant.

The proposed helicopter has two modes of operation, which will be discussed in detail below:

- horizontal flight mode with increased speed;

- vertical take-off or landing mode.

A brief description of the drawings.

In FIG. 1 shows the proposed helicopter in horizontal flight at high speed.

In FIG. 2 helicopter shown in vertical take-off or landing mode.

The implementation of the invention.

The helicopter of increased flight speed consists of a lifting screw 1, jet engines 2, a tail boom 3, a rudder 4, wings 5, rotary nozzles 6, and aileron 7.

Consider the horizontal flight mode with increased speed on the proposed helicopter, while the rotational speed of the lifting screw 1 is reduced to an acceptable speed around the blades, and the directional control and compensation of the reaction from the rotation of the rotor are provided by the aircraft type 4 rudder. The acceleration is supported by the jet engines 2, directed opposite the direction of flight with the help of rotary nozzles 6. In this case, the loss of lift is compensated by the lift of the wings s 5.

Consider the vertical take-off and landing mode. In this case, the rotational speed of the lifting screw 1 is increased, and the directional control and compensation of the reaction from the rotation of the screw are provided due to the tail beam 3 in the form of a wing located in the air stream from the lifting screw 1, with aileron controlled 7. The aerodynamic force of the tail beam 3 in the form of a wing compensates for the reaction from the lifting screw 1. At the same time, the control is carried out by turning the aileron 7. The jet of engines 1 due to the rotary nozzles 6 are directed sideways opposite, as in a conventional helicopter, and compensate for yn friend.

The transition from one mode to another is carried out smoothly by synchronously turning the nozzles of the jet engines 6 and changing the rotational speed of the lifting screw 1.

Additional advantages of the proposed helicopter include the safety of the control system.

Bibliographic data of information sources.

1. Helicopter diagrams [Electronic resource]. URL: https://ru.wikipedia.org/wiki/ Helicopter diagrams (accessed: 03/01/2017);

2. Modern combat helicopters: Ref. allowance / Autostat. IN AND. Korolev. - Mn .: Elayda, 1998 .-- 208 p.: Ill. - (In the world of technology). ISBN 985-6163-19-6.

3. Pchentleshev V.T. Rotary-wing aircraft // RF Patent, RU 2600966 C1, published October 27, 2016.

4. The Russian high-speed laboratory helicopter took off for the first time [Electronic resource]. URL: https://ria.ru/defense_safety/20160119/1361791736.html (published date: 01/19/2016).

Claims (1)

A helicopter containing a lifting screw, engines, a tail boom, a rudder, characterized in that the tail boom has a wing profile located in the air flow from the lifting rotor, and is equipped with a rotatable aileron, the engines have rotary exhaust devices with the ability to change the thrust from the side opposite direction in the direction opposite to the direction of flight, and the change in thrust direction is performed synchronously.

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