RU2477243C2 - High-speed helicopter - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to production of helicopters. High-speed helicopter comprises airframe, rotor, additional engine, tail rotor, and wings. Extra blade is arranged under every rotor glade, in L-like manner, between rotor shaft and bottom of every blade. Reversible shaft of additional engine is connected with case engaged, in its turn, with helicopter tail frame by manipulator composed of pneumatic cylinder. Second suck pneumatic cylinder displaces tail rotor shaft in case cutout. Both said cylinders allow tail turn in horizontal and vertical planes through more than 180 degrees. Rotary wings prevent helicopter spin in landing with tail rotor failure.

EFFECT: higher speed, reliability and maneuverability.

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Description

The invention relates to aviation, to the structural elements of aircraft, helicopter technology and can be used as a vehicle and effective means for conducting military operations, for placing weapons in it, transporting people and goods.

The purpose of the invention is to increase the speed of horizontal flight, improving the reliability and maneuverability of the helicopter.

On the schematic illustration of the proposed technical solution - FIGS. 1 and 2 show a part of the helicopter, including the subject of the invention, comprising a main rotor 1 with main blades and additional 2 - mounted L-shaped under each main - between its shaft and the bottom of the blades, FIG. 1 - reverse shaft 3 of the additional engine, on which the crankcase 4 is fixed in the form of a round drum, FIG. 2 is a section view along AA, in which a tide for mounting bearings 5 of FIG. 1 is provided, shaft 3 passes through the tide 5 and ends with gear 6 to In addition, in the crankcase, on the stop ring 7 of Fig. 2, a holder ring with a tide 8 is movably mounted for mounting bearings and a tail rotor shaft with gear 10 in it, located in the longitudinal (along the wall) groove 11 of the crankcase 4, ending with a tail rotor 12 of Fig. .1 and 2, in addition, in the center of the crankcase there is an axis 13 on which the disk gears 14 and 15 are mounted together, the gear 14 is paired with gear 6, and 15 with gear 10. Under the crankcase cover 16 between it and the holder ring 8 installed an elastic ring - (figure 2) gasket 17. To the cover or to to the housing (options) of the crankcase 4 is attached (the casing) the pneumatic manipulator cylinder 18, and the rod to the shaft of the tail rotor 9 is another pneumatic cylinder 19, attached to the tail of the helicopter 20 by the rod through the rods, as in the 1st case is attached to the housing of the crankcase 4. K the helicopter body 20 in the direction of the axial part of the rotor shaft corresponding to the middle of the width of the base, independently rotated wings 21 each.

The proposed device operates as follows.

As shown in FIGS. 1 and 2, by imparting mechanical strength to the rotor 1 by mounting an additional additional blade 2 under each blade, in order to achieve the stated objective of the invention, a crankcase 4 is attached to the rotating reversing shaft 3 of the additional engine, which is held on the shaft from rotation and takes the desired position in flight with the help of a pneumatic manipulator with its rods 19 with a rotation of more than 180 °. The shaft 3 with its gear 6 generates a torque to the rigidly attached disk gears 14 and 15. Rotating on the axis 13, the gear 15 transmits torque through the gear 10, mounted on the shaft 9 of the tail rotor 12, in the direction that gives it the reverse of the additional engine, providing or slowing down the flight. The shaft 9 installed in the tide of the ring 8, with the help of a pneumatic cylinder with rods 18, rotates it with the stop ring 7 along the walls of the circumference of the crankcase, cuts in the wall of the crankcase 11, which determines the stroke of the shaft 9 of the screw 12 - 180 ° or more. The rotary wings 21 provide anti-rotation of the helicopter flight, in case of failure of the tail rotor 12, the possible position of the shaft and rotor movement is shown by the dashed lines in Figures 1 and 2. The elastic ring-gasket 17 selects the play between the crankcase cover 16 and ring 8; rotary wings also provide helicopter flight, its soft landing, in case of an emergency failure of the rotor 1, tail rotor 12 is braking flight. Position A of the rotary wings 21, shown by a dotted line in FIG. 1, provides additional forward lift; position B provides flight back.

The prior art of known analogues and prototype does not meet the requirements and tasks identified in the formula and description of the proposed technical solution. In the invention according to patent No. 2363618, application 2008103377/11; 01/29/08, a technical solution is proposed, according to which compensating counter-rotations are achieved due to the beveled aerodynamic surfaces of the fuselage, suggests a fixed anti-spin effect. The problem in the present invention is clearly predominantly solved, where the claimed effect is obtained variably due to the possibility of the tail rotor turning more than 180 ° both vertically and horizontally.

In the invention according to patent No. 2397919, application 2009114391/11; 04/15/09, a technical solution is proposed where operation is proposed, which in general differs from that stated by the absence of additional blades under the blades of the main blades, which does not meet the requirements of mechanical hardening of the rotors, which is due to breaking of the rotor blades, with the development of high horizontal flight speeds of helicopters .

In the invention according to patent No. 2356795, application No. 2006136970/11, 10.10.06 "Short helicopter" (options), (prototype), the proposed technical solution, like the prototype, is a shortened helicopter, with the difference that it is the same as that of analogues of the above, there are no L-shaped installed additional blades, in addition, compensating the reactive moment of the main rotors, the compensating rotors function much less efficiently, because in the proposed invention the amplitude of variability of the tail rotor - having a rotation of more than 180 ° offline feature soft landing in the event of failure of the rotor.

The objective of the invention is disclosed as follows: the objective of increasing the speed of horizontal flight is solved by the proposed hardening of the rotor in conjunction with the "pushing" tail rotor. The reliability of the helicopter is proposed to be ensured by replacing the operation of the rotor engine, in an emergency, with an additional engine with a tail rotor. Maneuverability is provided by a crankcase with a tail rotor - its rotational ability, both of the crankcase relative to the tail of the helicopter, and of the movement of the tail rotor shaft inside the crankcase, with the help of pneumatic manipulators.

Claims (1)

A high-speed helicopter comprising a housing, a rotor, an additional engine, a tail rotor, wings, characterized in that, in order to increase flight speed, reliability of the helicopter and its maneuverability, under each rotor blade, L-shaped, between the rotor shaft and the bottom of each blades for mechanical hardening of the structure, one more blade is installed, the reversible shaft of the additional engine contained in the tail section connected to the crankcase, which, in turn, is connected to the tail section of the helicopter in the middle Using the pneumatic manipulator cylinder that rotates the crankcase on the engine shaft by more than 180 °, together with the manipulator pneumatic cylinder attached to the crankcase, the tail rotor shaft moves along the crankcase, together both pneumatic rods rotate the screw horizontally and vertically more than 180 °, thereby changing and holding the direction of flight, the necessary braking of the flight, and the contained rotary wings prevents the helicopter from spinning during a smooth landing in case of failure in flight tails th screw.

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