RU2456209C1 - Converter plane - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to VTOL aircraft. Converter plane comprises fuselage, wing, engines, empennage and undercarriage. Pylons are made on wing tips to rotate thereon. Two front engines are mounted on pylons. Rear engine is mounted on keel-pylon. Gears are aligned with wing pylons and keel.

EFFECT: well-balanced flight.

4 dwg

Description

The present invention relates to the field of aviation technology and can be used for the design and production of unmanned and transport aircraft.

Turntop planes have undeniable advantages in transportation, which are not fully implemented in technical solutions at the present time.

A variety of tiltrotor schemes are known in the art, for example. Bell V-22 Osprey, Bell / Aguste BA609, Hiller XC-142A (tiltrotor Bell-Boeing V22-Osprey - URL http://atikot.my1.ru/news/2009-07-03-487. Bell / Agusta BA609 - URL http://en.wikipedia.org/wiki/Bell/Agusta_BA609. Beating Gravity - Vought-Hiller-Ryan XC-142A - URL http://www.unrealaircraft.com/gravity/vhr_XC-142A.php), which are dual-mode devices capable of flying like an airplane, i.e. engines create traction necessary for moving forward at a given height at a given speed; during movement, the wing creates a lifting force, due to the prevalence over the weight of which the device makes a lift, and like a helicopter, in which the engine thrust, overcoming the weight, provides the lift of the device, and forward movement is provided either by the inclination of the rotor, or by an additionally blown tail unit, which are inherent transition from helicopter to airplane mode through the rotation of engines or wings, with engines placed on it.

Known disadvantages of these devices is that structurally the centers of mass of the engines are not installed on the same axis as the center of mass of the tiltrotor, which leads to extreme longitudinal instability and poor controllability of the device. In addition, in the case of a rotary wing, rotation of the wing during flight by an angle of 90 ° leads to a disruption of the flow on the wing and a catastrophic decrease in lift. It should be noted that only one Bell V-22 Osprey is in serial production, which indicates the imperfection of previously proposed design schemes.

The closest to the claimed technical solution is the tiltrotor (patent US 6607161 B1, publ. 08/19/2003, US C1. 244/7, IPC B64C 37/00, Convertible aircraft with tilting rotors), including the fuselage, wing, tail, engines installed at the ends of the wing, landing gear. The patent also provides a control circuit. The transition from helicopter to airplane mode is possible by turning the engines.

The disadvantages of this technical solution is that helicopter propellers of large diameter are installed, which have great restrictions on flight speed in comparison with aircraft of small diameters, and helicopter hubs with swash plates that are necessary for pitch control during hovering, take-off and landing, which greatly complicates and makes the design heavier, since in the main phase of the flight - cruising mode - these bushings with swashplate are dead weight and in themselves are extremely complex technical items. When the engine nacelle is rotated, with the engine placed in it, the wing enters the propeller airflow zone, which reduces its efficiency and is another drawback.

The problem to be solved is the creation of a promising aircraft for transportation, a simple design, balanced in all flight modes, capable of performing horizontal flight, vertical take-off and landing and hovering in one place. The usefulness of a tiltrotor lies in the possibility of take-off / landing at almost any suitable site in terms of size and in reducing transportation time due to the ability to deliver the target load to the destination as close as possible.

The technical result is aimed at increasing the efficiency of the convertiplane. The technical result is achieved by the fact that in the tiltrotor containing the fuselage, wing, engines, plumage, landing gear, pylons are introduced, made with the possibility of rotation and located on the wing, while they have a pair of front engines, and the rear engine is mounted on the keel pylon, moreover, the landing gear combined with the pylons of the wing and keel, respectively.

The advantage provided by the given set of features is the removal of the engines on the pylons forward from the center of mass and the introduction of the third engine in the tail section, which allows you to effectively control the device by the angle of heel and pitch at zero speeds of take-off and landing.

The invention is illustrated by drawings, which depict:

figure 1 - presents a view of the tiltrotor on takeoff / landing mode,

figure 2 - presents a view of the convertiplane at cruising mode,

figure 3 is a top view of a tiltrotor,

figure 4 - presents a view of the convertiplane from the nose,

where 1 is the fuselage;

2 - wing;

3 - front engines in nacelles;

4 - tail engine in a nacelle, rigidly fixed to the keel;

5 - rotary keel;

6 - stabilizer;

7 - front wheels of the chassis;

8 - rear wheel of the chassis;

9 - rotary pylons;

10 - ailerons;

11 - elevators;

12 - rudder.

The present invention contains a fuselage 1, which serves to accommodate the target load, elements of the control system and other systems; wing 2 with pylons, with engines placed on it, serves to create lift in cruising mode; engines 3 located on the wing and engine 4 located on the rotary keel 5, which serve to create lift in take-off / landing modes and to create traction in cruise mode.

This invention has several features. The plumage feature is a rotary keel 5 and a fixed stabilizer 6. The chassis is made according to the scheme of a three-leg chassis with a rear support. The front wheels of the chassis 7 are mounted on the pylons 9 of the front engines 3, and the rear wheel of the chassis 8 is mounted on the rotary keel 5.

The device operates as follows: on takeoff / landing, engines 3, 4 occupy the position shown in FIG. 1. Moreover, the location of the engines provides longitudinal, track and lateral balancing due to the location of the front 3 and tail 4 engines relative to the center of mass of the apparatus (CM). Upon reaching the cruise flight altitude, the apparatus freezes and the engines 3, 4 by turning the pylons 9 and the rotary keel 5 respectively occupy the position shown in FIG. 2.

In the process of turning engines 3, 4, an increase in the horizontal component of speed occurs. The wing 2 thus creates a lifting force that compensates for the decrease in the vertical component of the thrust of the screws.

As the horizontal component of the flight speed increases and the vertical component of the thrust of the propellers decreases, aircraft control is transferred to the aircraft controls: elevators 11 and ailerons 10. Rotary keel 5 and rudder 12 in all modes control the apparatus along the yaw line.

Further, after turning the engines, the flight of the device does not differ from the flight of the aircraft.

To ensure stability in transition from hovering to horizontal flight, propulsion is controlled using self-propelled guns (automatic control systems).

Compared with the known analogues, the claimed technical solution has a number of technical and economic advantages, namely, by changing the distance from the engines to the wing equal to the length of the pylons, the efficiency has decreased by a smaller amount. propellers of the front engines in transition due to the wing entering the propeller airflow zone, and the apparatus weight is reduced by 7-12% due to the exclusion of helicopter hubs with swashplate. For example, the weight of the swashplate of an ultralight helicopter with a total mass of 450 kg is 34 kg or 7.6%.

Claims (1)

A tiltrotor comprising a fuselage, wing, engines, plumage, landing gear, characterized in that pylons are introduced, rotatably mounted and located on the wing, while a pair of front engines are mounted on them, and the rear engine is mounted on a keel pylon, landing gear combined with wing pylons and keel, respectively.

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