WO2012026839A1

WO2012026839A1 - Helicopter

Info

Publication number: WO2012026839A1
Application number: PCT/RU2010/000467
Authority: WO
Inventors: Shulim Semenovich Shvidler
Original assignee: Shulim Semenovich Shvidler
Priority date: 2010-08-26
Filing date: 2010-08-26
Publication date: 2012-03-01

Abstract

The invention relates to helicopters. A helicopter comprises a carrying propeller with own drive, a movable tail propeller, which is rotated by the drive, or unmovable tail propeller, a device with a drive for turning the movable tail propeller, aerodynamic surfaces, which are movable with respect to the longitudinal axis of the helicopter fuselage and to its tail, or unmovable aerodynamic surfaces, levers and shafts for fastening aerodynamic surfaces to the helicopter and to the device for turning of the tail propeller, a variable speed drive or a reducer. The levers and shafts for fastening the movable aerodynamic surfaces with respect to the helicopter and to the device for turning the tail propeller are intended for turning of these surfaces at angle for the helicopter braking. The tail propeller is accomplished with adjustable or non-adjustable blade pitch. The invention is directed on the decrease of the aerodynamic drag and on a providing with exact compensation of reactive moment of the carrying propeller without of variation its parameters.

Description

HELICOPTER

Technical Field

This invention concerns helicopters especially the helicopters with one carrying propeller and one tail propeller with a its turning device, immovable or movable aerodynamic surfaces and variator of velocity of rotation or gear box, what provides possibility: to decrease power expenses of a helicopter within its flight, to decrease its aerodynamic resistance; to make precious compensation of reactive moment of the carrying propeller with no change of parameters of that carrying propeller; and also to make, when it is necessary, the sharp braking of the helicopter, and by this way to decrease the time of its braking.

Background Art

There is known a helicopter Patent RU ½ 2086476, B64C 27/04, 27/82, published 10.08.1997, in which for compensation of reactive moment the helicopter fuselage is subjected, the stationary (immovable) tail propeller which is placed with this perpendicularly to the longitudinal axis of the helicopter and set in rotation by the carrying propeller power plant.

This tail propeller by taking a part of the helicopter plant power does not lake part in creation of tractive force for longitudinal travel of the helicopter on its flight, but creates only a perpendicular tractive force, which compensates a reactive moment of the carrying propeller. This increases the aggregate power expenditures of the helicopter when its flight.

In accordance with the abovementioned patent the aerodynamic surfaces arc situated above and on one side of the tail propeller, outside of the zone of effect of air flows, created by this propeller and the carrying propeller. As the air flows created by tail propeller is directed perpendicularly to the long axis of the helicopter, that worsens aerodynamic characteristics of the helicopter when its flight, increases its aggregate power expenditure of the helicopter, worsens of its flight characteristics.

When the necessary braking of the helicopter, the tractive force created by the tail propeller does not take part in this braking and this worsens the flight characteristics of the helicopter.

Disclosure of Invention

The task of making of improved helicopter with decreased power expenses when its flight, with decreased aerodynamic resistance, with new method of precious compensation of reactive of the carrying propeller with no change of working parameters of this propeller and new method of braking is taken as a basis of the invention.

These engineering results are achieved on account of that the improved helicopter of this invention is supplied with:

- a carrying propeller with warp device;

- stationary or movable tail propeller with adjustable blade pitch or without adjustment of blade pitch, situated coaxially or almost coaxially to the longitudinal axis of the helicopter fuselage does, set in rotation by gear of the carrying propeller or by its own or by any other one;

- turning device of movable tail propeller;

- at least one aerodynamic surface either stationary (immovable) or movable as to longitudinal axis of the helicopter fuselage and situated next to the tail propeller, in the zone of acting of the air flows, made by the carrying propeller and the tail propeller;

- ties and shafts fastening the immovable aerodynamic surfaces to the helicopter and to the movable tail propeller rotation device, what provides possibility to make, when it is necessary, turning of the aerodynamic surfaces;

- velocity variator or gear box.

Brief Description of Drawings

The realization of the invention is described with reference to drawings wherein:

Fig. 1 shows as a scheme, the side-view of the helicopter in flight in accordance with the invention, this is one with an immovable tail propeller set on the longitudinal axis of fuselage of the helicopter, and the aerodynamic surfaces immovable as to fuselage of the helicopter. The helicopter is also equipped with the velocity variator.

Fig. 2 shows as a scheme the view from above of the same helicopter.

Fig. 3 shows as a scheme the side-view of the same helicopter when take-off or landing or being up in the air.

Fig. 4 shows as a scheme the view from above of the same helicopter.

Fig. 5 shows as a scheme the side-view of the helicopter in flight in accordance with the invention, this is one with a tail propeller movable as to longitudinal axis of the helicopter, and aerodynamic surfaces immovable as to fuselage of the helicopter, situated next to the tail propeller, in the zone of the air flows produced by the tail propeller and the carrying propeller effect.

Fig. 6 shows as a scheme the view from above of the same helicopter.

Fig. 7 and 8 show on a large scale a section of Fig. 6 and 7 by E-E and T-T lines. Fig 9 shows as a scheme the side-view of the helicopter in flight in accordance with the invention, this is one with a tail propeller movable to the fuselage of the helicopter and its longitudinal axis, and aerodynamic surfaces movable as to fuselage of the helicopter.

Fig. 10 shows as a scheme the view from above of the same helicopter.

Fig. 11 shows as a scheme the side-view of the same helicopter when taking-off or landing or being up in the air.

Fig. 12 shows the view from above of the same helicopter.

Fig. 13 shows on a large scale a section of Fig. 9 by K-K line.

Fig. 14 shows on a large scale a section of Fig. 13 by S-S line.

Best Mode for Carrying out the invention

Referring to Fig. 1, 2, 3 and 4 we see a helicopter 1 which consists of a fuselage 2, in the front part of which a cockpit 3 is situated. A power plant 4 provides rotation of a carrying propeller 5 with a warp device (swach plate) 6. A fuselage 2 in its back part turns into tail 7.

In the free end part of the tail, coaxial to the longitudinal central axis M-M of the helicopter, a immovable tail propeller 8 with a changeable pitch, which is set in rotation by a power plant 4 by means of a shaft 9, is set. If it is necessary the power plant 4 may be provided with velocity variator 10, which changes when it is necessary the velocity of rotation of the shaft 9.

Besides that, the tail 7 in its end part is equipped by aerodynamic surfaces 11. They are situated next to the tail propeller 8, in the zone of the air flows, produced by this tail propeller and carrying propeller, effect. The aerodynamic surfaces may not change their position as to the helicopter within all periods of flight.

Number, construction and dimensions of the immovable aerodynamic surfaces, their form and position are stated by the created type of helicopter and its required working characteristics. The stipulation above concerns the movable aerodynamic surfaces too.

During the flight of the helicopter the carrying propeller 5 on its rotation in direction of pointer Fl produces a reactive force F2_; which tries to turn the helicopter to the same direction. But an air flow 12, produced by the tail propeller 8, flowing round the aerodynamic surfaces 11, together with an air flow 13, arising as a result of displacement of the helicopter in space, produces side tractive forces £2, which compensates the reactive force F2.

The tractive force f3, produced by tail propeller 8, when the flight, composes with the tractive force F3, produced by the carrying propeller. As a result this reduces power expenditures of the helicopter, when its flight. A control of forces f2 when changing of flight conditions may be made by velocity variator 10, which changes the turning velocity of the shaft 9, and by changing pitch of blades of the tail propeller 8 or by any other method.

When taking-off or landing or being up in the air the warp device creates a tractive force F4 of the carrying propeller (see Fig. 4), which is directed towards the tail propeller 8 and is equal to the tractive force of the tail propeller.

As a result the tractive force of the tail propeller is neutralized by tractive force of the carrying propeller 5.

Because the air flow 12 of the propeller 8 is on the same axis the M-M axis does, but not perpendicularly to it, the aerodynamic resistance of the helicopter reduces and this causes reduction of flight power expenditures.

Analogously, within flight of the helicopter by the second or the third version, the reduction of power expenditures and reduction of aerodynamic resistance of the helicopter take place.

By the second version the helicopter 1 (see Fig. 5; 6) according to the invention, with the carrying propeller 5, is equipped with the movable tail propeller 8 end immovable aerodynamic surfaces 11, set in the area of the tail propeller 8, in the zone of air flows 12, produced by this tail propeller and carrying propeller, effect.

The flight of the helicopter according to the second version is analogous to the flight of the helicopter according to the first version (see Fig. 5; 6 continuous lines), and forces and air flows produced by this are analogous to the forces and air flows of the helicopter according to the first version. By this the tail propeller of the helicopter is set on the same axis or almost on the same axis, the longitudinal axis of the helicopter fuselage does. One of the possible constructions of the tail propeller 8 turning device (see Fig. 7, made according to section of Fig. 6 by E-E, and section of Fig. 8, made according to section of Fig. 7 by T-T) includes shaft 9, coming from the helicopter power plant 4. This shaft carries a pinion 15 as to wheel 17 and tail 7. The wheel 17 through the vertical shaft 18 and bearing units 19 and 20 is fixed in the helicopter tail 7 covers 21 and 22. The bearing unit 20 is equipped with horizontal bearing unit 23, on which the movable tail propeller 8, pinion 24 and eye 25 are set (see Fig. 8). The unit 23 is tied strictly with the unit 20.

In the tail 7 the power cylinder 26, a rod 27 of which is tied with the eye 25, is also set, but the cylinder 26 support 28 is bind by hinge with the helicopter 1 tail 7.

When the flight of the helicopter 1. the shaft 9 rotates the pinion 15 and through the wheel 17 sets in rotation the pinion 24 and accordingly the tail propeller 8. By this the cylinder 26 rod 27 keeps the tail propeller on the axis M-M of the helicopter or almost on it, or in any other necessary position. In other respect the flight of the helicopter happens by analogy with the flight of the helicopter according to version 1.

When taking-off or landing or being up in the air, the power cylinder 26, overcoming the resistance of the rotating wheel 17, turns the unit 23 together with the pinion 24 and tail propeller 8 to position A (see Fig. 6). Accordingly the propeller 8 comes into position 8A, but the air flow 12 comes into position 12 A. As a result the tractive force of the tail propeller in position 8 A compensates the reactive moment of the carrying propeller 5.

When changing the flight conditions the tractive force, necessary for carrying propeller reactive moment compensation, must be changed too.

Such change according to the invention is made by power cylinder, which overcoming the resistance of the rotating wheel 17, deflects the unit 23 together with the pinion 24 and the tail propeller 8 to the necessary angle a to the right or to the left as to the axis M-M, and this changes tractive force f2 by the necessary value (Fig. 6 shows only the angle a, the tail propeller 8 in position 8a is not conditionally shown. Fig. 8 shows both the angle a and the tail propeller 8 in position 8a). The described construction according to this invention improves the flight characteristics of the helicopter, such as easiness of helicopter control when a change of flight conditions.

By the third version of the helicopter by this invention the aerodynamic surfaces 11 are fastened both to the vertical shaft 28 (Fig. 14), which passes through the shaft 18, and to the tie 29, which by its lower end is fastened to the unit 23 (see Fig. 9; 10; 11; 12; 13 and 14).

The aerodynamic surfaces 11 are set in the area of the tail propeller in the zone of the air flows, produced by this tail propeller and carrying propeller, effect.

By this the flight is analogous to the flight of helicopter by the second version (Fig. 5; 6; 7 and 8, continuous lines).

When an urgent braking is necessary the power cylinder 25 turns the body 23 together with the tail propeller 8 to position 8A (Fig. 11; 12). By this the tie 23 turns the aerodynamic surfaces 11 to position 11 A, As the air flow 12A of the tail propeller 8 A continues to flow round the surfaces 11A the power Fl lA, which is directed against longitudinal move of the helicopter, arises and this causes according to the invention to its urgent braking.

As a result such flight characteristic, as the braking time is, reduces sharply.

I wish it to be understood that we do not desire to be limited to the exact details of construction shown and described in this patent, the modifications, admissible in the framework of this patent, may be made to them by a person skilled in the appropriate field.

Claims

Claim 1. Helicopter provided with a carrying propeller with its own drive, movable tail propeller, rotated by any drive, movable tail propeller turning device with its own drive, at least one aerodynamic surface movable as to longitudinal axis of the fuselage of the helicopter and its tail, links and shafts, fastening the movable aerodynamic surfaces to the helicopter and to the tail propeller turning device, velocity variator or gear box; and this helicopter is made in such way, that for the purpose to decrease its power expenses, decrease of its aerodynamic resistance, providing of exact compensation of reactive moment of the carrying propeller without change of parameters of that carrying propeller, and also sharp braking of the helicopter when it is necessary, when its flight, it includes:

- a movable tail propeller which can turn at a needed angle around the longitudinal axis of the helicopter when it is necessary, and connected with its power plant through a velocity variator or gear box;

- a movable tail propeller turning device, situated next to this propeller and providing a turning of the tail propeller at a needed angle when it is necessary, when the flight;

- at least one aerodynamic surface, movable as to the longitudinal axis of the helicopter and situated next to the tail propeller, in the zone of air flows, produced by tail propeller and carrying propeller;

- links and shafts fastening movable aerodynamic surfaces to the helicopter and to the tail propeller turning device and which provide the turning of that surfaces at a needed angle when it is necessary, and by this way the braking of the helicopter is made;

- the velocity variator (or gear box), which outlet shaft is situated on the needed height as to the carrying propeller, what provides possibility to set the aerodynamic surfaces in the zone of air flows, produced by carrying propeller and tail propeller.

Claim 2. The helicopter according to Claim 1, provided with a carrying propeller, movable tail propeller, movable tail propeller turning device, at least one aerodynamic surface, immovable as to the longitudinal axis of the fuselage of the helicopter and its tail, velocity variator or gear box; and this helicopter is made in such way, that for the purpose to decrease its power expenses, decrease of its aerodynamic resistance, providing of exact compensation of reactive moment of the carrying propeller without change of parameters of that carrying propeller, this helicopter has: - aerodynamic surfaces made immovable as to the fuselage of the helicopter and its longitudinal axis, and this surfaces are situated next to the tail propeller in the zone of air flows produced by tail propeller and carrying propeller, effect.

Claim 3. The helicopter according to Claim 2, provided with a carrying propeller, immovable propeller, at least one aerodynamic surface, immovable as to the longitudinal axis of the helicopter and its tail, velocity variator or gear box, and this helicopter is made in such way, that for the purpose to decrease its power expenses, decrease of its aerodynamic resistance, this helicopter includes:

- immovable tail propeller with adjustable blade pitch;

- aerodynamic surfaces, immovable as to the fuselage of the helicopter and its tail, and these surfaces are situated next to the tail propeller, in the zone of air flows produced by tail propeller and carrying propeller.