RU2506203C1 - Method of landing rotorcraft without alighting run with autorotating rotor and wing - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to landing of rotorcraft. Proposed method consists in that, first, preset speed is selected at glide path slope. Then, total pitch of the rotor is selected. Then, reverse is actuated of engine reversing devices are activated depending upon engine type at preset altitude above landing ground to brake the rotorcraft and to reduce landing speed. Now, total pitch and rotor thrust are increased to reduce landing speed to zero unless touchdown.

EFFECT: landing without alighting run.

Description

The claimed invention relates to the field of aviation.

A rotary-wing aircraft with an autorotating rotor and a wing, according to the principle of creating lift at low flight speeds, refers to a gyroplane, which is an intermediate type of aircraft between a helicopter and an airplane. In this regard, it is advisable to consider the existing landing methods used in helicopters, aircraft and gyroplane.

A known method of vertical landing of a helicopter. On the glide path of planning, the pilot sets the set speed. At a given height relative to the landing pad, the pilot, acting on the common and cyclic pitch of the rotor, controls the helicopter to brake and hangs over the landing pad. After that, by smoothly reducing the total pitch of the main rotor, the pilot lowers and lands the helicopter [1].

For a helicopter, unlike an airplane, there are no such concepts as evolutive speed and critical stall mode. At the same time, the necessary stability of the device at a low flight speed, including at its zero value, is ensured by a rotating rotor, and its controllability is due to the pilot's actions with the control levers on the general and cyclic pitch of the rotor.

There is also a known method of landing an airplane. On the glide path of planning, the pilot sets the set speed. The landing method includes the stage of flight on the glide path of planning from a given height above the level of the end of the runway before landing and the run through the airfield to a complete stop. The specified phase of the flight includes several stages: leveling, holding, parachuting and landing [2, p.441]. The lower the evolutionary speed of the aircraft, the lower its landing speed and path length.

For the purpose of braking the aircraft after landing and reducing mileage, use the brakes of the landing gear wheels. In addition, to reduce the mileage can also be used depending on the type of power plant of the aircraft reversible devices of jet engines or reverse propellers. The use of the brakes of the wheels of the chassis and the reverse of propellers after landing on the runway made it possible to obtain a mileage of 280 m [3] on an S-80GP airplane.

The landing method of the gyroplane does not have fundamental differences from the landing method of the aircraft. On the glide path, the pilot also sets the target speed. The landing method includes the stage of flight on the glide path of planning from a given height above the level of the landing site before landing and a short run to a complete stop. The main advantage of a gyroplane: minimum (evolving) speed and a smaller landing distance compared to an airplane [2, p. 34]. The difference between the gyroplane is significantly lower landing speed and path length. In addition, in a gyroplane, like in a helicopter, a rotating rotor provides the necessary stability and controllability at significantly lower speeds of the landing stages compared to an airplane.

The technical task of the claimed invention is a method of landing without a run of a rotary-wing aircraft with an autorotating rotor and a wing, in which to reverse the rotor-wing aircraft on the glide path and reduce its landing speed to zero by the time of landing, reversible propellers are used depending on the type of power plant or reversible devices of engines and the general pitch of the rotor to increase its thrust due to the available kinetic energy reserve ui.

The technical result of the method of landing without a run of a rotary-wing aircraft with an autorotating rotor and a wing is achieved by setting a predetermined speed on the glide path, then setting a predetermined common pitch of the rotor, and then turning on the rotors or reversing engines of the engines, depending on the type of power plant at a given height relative to the surface of the landing pad to brake the apparatus and reduce the landing speed, then before the end of the brakes Zheniya increase the overall pitch and thrust of the rotor to reduce the speed of landing of the apparatus up to zero by the time the wheels of the chassis touch the surface of the site.

An example of the implementation of the landing method without mileage of a rotorcraft with an autorotating rotor and wing is as follows:

- set the desired speed on the glide path;

- then set the specified total pitch of the rotor to ensure the maximum possible frequency of rotation and the required supply of kinetic energy;

- after this, depending on the type of power plant, reverse propellers or reversing devices of the engines are turned on at a predetermined height relative to the surface of the landing pad to brake the apparatus and reduce the landing speed. At the same time, the necessary stability of the apparatus at low speeds is provided by a rotating rotor, and its controllability is due to the pilot's leverage on the common and cyclic pitch of the rotor;

- then, before the end of braking, the overall pitch and thrust of the rotor are increased to reduce the landing speed of the apparatus up to zero by the moment the wheels of the chassis touch the surface of the platform.

In this case, the necessary increase in thrust of the autorotating rotor is achieved through the use of stored kinetic energy.

The analysis of the prior art by the applicant showed that the set of essential features of the claimed technical solution is new and meets the condition of patentability of the invention.

Information sources

1. Instructions to the crew of the Mi-4A helicopter with the ASh-82V engine, military publishing house of the USSR Ministry of Defense, Moscow, 1972 (p. 60, 61).

2. Svishchev G.P. Aviation, encyclopedia. Scientific publishing house "Big Russian Encyclopedia", TsAGI, Moscow, 1994

3. Simonov M.P., Litvinov G.A. Multifunctional aircraft for local and regional air lines S-80GP. Magazine "Flights N91, Publishing House" Engineering ", Moscow, 1999 (p. 14).

Claims (1)

A method of landing without a run of a rotary-wing aircraft with an autorotating rotor and a wing, which consists in setting a predetermined speed on the glide path, characterized in that a predetermined common pitch of the rotor is set, then, depending on the type of power plant, reverse propellers or engine reversing devices are turned on a predetermined height relative to the surface of the landing pad for braking the apparatus and reducing the landing speed, after which I increase before braking general step and the thrust of the rotor to reduce the landing speed of the machine until a zero value at time of gear wheels touch pad surface.