RU2698141C1 - Helicopter - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to aircraft engineering, particularly, to helicopters. Helicopter comprises emergency landing system, fuselage, bearing screw on shaft connected via reduction gear with gas turbine engine. Emergency landing system includes cylindrical casing located in lower part of fuselage, inside of which there is a fan, which contains working blades on hub, connected by second shaft with reduction gear. Outlet guide vanes are fixed on the casing under the fan. On side wall of casing there are inlet openings for air intake. Fan in flight creates up to 10 % of lifting force, and at break of rotor 90–99 %. Working blades of the fan and the guide vanes are made rotary. Damping gasket is installed between cylindrical casing and fuselage.

EFFECT: enabling safe landing at screw destruction.

4 cl, 4 dwg

Description

The invention relates to aviation, more specifically to helicopters and is aimed at improving the safety of their flight.

Known safe helicopter according to the patent of the Russian Federation No. 2203837, PMK, publ. 07/27/2002. This helicopter contains a rotor. A bearing is mounted on the rotor shaft above the blades, and the parachute system is mounted on the rotor shaft above the rotor blades in a streamlined casing above the bearing, parachute slings are attached to the outer bearing race made stationary, the parachute is equipped with a rocket for accelerated output of the canopy of the parachute. When saving the helicopter, the rotor shaft is locked, the parachute is pulled out and the helicopter is landing.

Disadvantages: large dimensions and weight of the parachute and obfuscation of its slings during rotation of the falling fuselage.

Known safe helicopter according to the patent of the Russian Federation for the invention No. 2333135, IPC ВСС 27/04, publ. September 10, 2008

This helicopter contains a traction engine and a rotor with a vertical axis, on top of which there is an even number, but not less than four blades. The helicopter also contains a connecting device that plays the role of a transmission in the operating mode of the traction engine, and in the operating mode of the starting engines - the role of a freewheel mechanism. Each second rotor blade has a calculated shortened dimension of overall length and includes in its device one or more elementary starting engines, for example, operating on solid fuel. The invention improves safety during emergency landing of a helicopter.

Disadvantage: low reliability.

Known helicopter according to the patent of the Russian Federation for the invention No. 2335432, IPC ВСС 27/04, publ. 10/10/2008

This helicopter includes a fuselage and coaxial screws, and the screws can be two or more and they can be of different diameters. At least one of the screws is controlled with a variable pitch, and the rest with a fixed pitch. In the second embodiment, the helicopter has a tail boom with an elastic pneumatic chamber at the end, and when the beam is raised, thrust reduction is blocked. In the third embodiment, the engine and gearbox are located in a separate engine nacelle) located above the fuselage on the pylons and / or elastic inserts. The invention improves the efficiency of the rotor.

Disadvantage: low reliability of the helicopter due to the fact that when one propeller breaks, the thrust of the other is not enough for it to land and, in addition, the occurrence of an imbalance disrupts the operation of the second propeller.

Known helicopter according to the patent of the Russian Federation for the invention No. 2148537, IPC ВСС 7/20, publ. 05/10/2002, the prototype.

This helicopter contains a housing, an air-jet engine for generating thrust for horizontal flight, rotors that are located inside the housing and serve as a compressor for an air-jet engine, an engine that is designed to rotate these rotors, and the cockpit. A protective net is provided under which the rotors are located. Sashes are located below the net and are designed for take-off and landing.

Disadvantage: poor flight safety due to the fact that when the propeller is destroyed, helicopter landing will almost always lead to catastrophic consequences.

The task of creating the invention: improving the reliability and safety of flight.

Effect: ensuring a safe landing when the screw is destroyed.

The solution to this problem was achieved in a helicopter containing an emergency landing system, a fuselage bearing a rotor on a shaft connected through a gearbox to a gas turbine engine, in that the emergency landing system includes a cylindrical casing located at the bottom of the fuselage, inside of which a fan containing working blades is mounted on a hub connected by a second shaft to the gearbox and under them the output guide vanes mounted on the casing, inlet openings for air intake are made on the side wall of the casing, The fan creates a flight to 10% of lift, and in case of breakage of the rotor 90-99%.

The working blades can be made rotary.

Guide vanes can be made rotary.

Between the cylindrical casing and the fuselage can be installed damping pad.

The invention is illustrated in the drawings (Fig. 1 and 4), where:

- in FIG. 1 shows a diagram of a helicopter,

- in FIG. 2 shows the design of the casing and the fan installed in it,

- in FIG. 3 shows a detailed design of the casing and the fan installed therein,

- in FIG. 4 shows view AA.

A safe helicopter (Fig. 1) contains a fuselage 1, a rotor 2, a tail 3, a control screw 4, a shaft 5 connecting a screw 2 through a gearbox 6 to a gas turbine engine 7.

A cylindrical casing 8 is fixed under the fuselage, in which a fan 9 is installed. The fan 9 is connected by a shaft 10 to a reducer 6.

In FIG. 2 shows in more detail the design of the fan 9. It contains a hub 11 with rotor blades 12, under the rotor blades 12 on the casing 8, output guide vanes 13 are fixed. The cylindrical casing 8 has a side wall 14. Entrance openings 15 for air intake are made on the side wall 14.

The working blades 12 can be made rotary, for this they must be mounted with the possibility of rotation on the pins 16. The drive of the working blades 12 is not shown.

The output guide vanes 13 can be made rotatable and for this they must be installed between the outer bandage 17 and the inner cylinder 18 on the pins 19 and 20 and connected to the drive 21 (Fig. 2). The cavity 22 of the inner cylinder is filled with a honeycomb structure 23 (Figs. 3 and 4). Cells are placed in a plane perpendicular to the shaft 5.

Between the fuselage and the casing 8 can be installed damping pad 24 (Fig. 2). The damping pad 24 can be made of metal rubber and tightened with bolts 25 with nuts 26 (Fig. 2).

In FIG. 3 shows a detailed design of the casing and the fan installed therein, and FIG. 4 shows view AA.

HELICOPTER WORK

During operation of the helicopter (Fig. 1) the rotor 1 creates about 90% of the lifting force and up to 10% creates a fan 9, expelling air through the guide vanes 13 down.

If the rotor 2 breaks down, the fan 8 creates a lifting force of up to 90% to 99% of the lifting force of the rotor 2 and the helicopter will be able to land on the ground without damage or with slight damage to the casing 8 and fan 9, which are compensated by the honeycomb structure 23 and damping gasket 24.

The application of the invention allowed:

- ensure a safe landing when the screw is destroyed,

- save the life of the crew and passengers.

Claims (4)

1. A helicopter containing an emergency landing system, a fuselage, a rotor on a shaft connected through a gearbox to a gas turbine engine, characterized in that the emergency landing system includes a cylindrical casing located at the bottom of the fuselage, inside which a fan is installed, containing working blades on the hub, connected by a second shaft to the gearbox, and under them the output guide vanes mounted on the casing, inlet openings for air intake are made on the side wall of the casing, the fan in flight creates up to 10 % of lifting force, and when the rotor breaks, 90-99%. 2. The helicopter under item 1, characterized in that the working blades are made rotary. 3. The helicopter under item 1, characterized in that the guide vanes are made rotary. 4. The helicopter according to claim 1, characterized in that a damping pad is installed between the cylindrical casing and the fuselage.

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