RU2014107956A

RU2014107956A - VERTICAL RETAINING VEHICLE WITH VERTICAL TAKEOFF

Info

Publication number: RU2014107956A
Application number: RU2014107956/11A
Authority: RU
Inventors: Андрей Зелимханович Парастаев
Original assignee: Андрей Зелимханович Парастаев
Priority date: 2014-03-03
Filing date: 2014-03-03
Publication date: 2015-09-10
Also published as: WO2015133932A2; WO2015133932A3; RU2563921C1

Abstract

1. Высокоскоростной винтокрылый летательный аппарат с вертикальными взлетом и посадкой, содержащий, по крайней мере, один движитель, фюзеляж, хвостовое оперение с установленным на нем под углом к набегающему воздушному потоку вертикальным килем, создающим компенсирующий крутящий момент по отношению к закрепленному на валу несущему винту, с прикрепленным к вертикальному килю рулем направления, горизонтальный стабилизатор с прикрепленным к нему рулем высоты, рулевой винт в кольцевом обтекателе в хвосте летательного аппарата для обеспечения тяги в необходимую сторону для компенсации крутящего момента несущего винта, гондолу и механизм отклонения несущего винта, обеспечивающий достаточный зазор несущего винта в его отклоненном положении и отклоняемых вместе с несущим винтом устройств, на которых закреплен несущий винт, с верхней частью фюзеляжа, отличающийся тем, что гондола выполнена отклоняемой совместно с вращающимся валом несущего винта, по крайней мере, часть которого установлена в отклоняемой гондоле, в летательный аппарат дополнительно введен установленный в отклоняемой гондоле автомат перекоса с системой его управления, механизм отклонения несущего винта выполнен в виде механического привода, обеспечивающего возможность увеличения вектора тяги несущего винта в горизонтальном направлении посредством наклона вала несущего винта на заданный угол и обеспечивающего достаточный зазор между гондолой и плоскостью вращения лопастей несущего винта в отклоненном положении несущего винта и верхней частью фюзеляжа, рулевой винт выполнен, по крайней мере, с двумя лопастями и с возможностью поворота 1. A high-speed rotorcraft with vertical take-off and landing, comprising at least one propulsion device, fuselage, tail unit with a vertical keel mounted on it at an angle to the incoming air flow, creating a compensating torque with respect to the rotor fixed to the shaft , with a rudder attached to a vertical keel, a horizontal stabilizer with a height rudder attached to it, a tail rotor in an annular cowl at the tail of the aircraft to ensure thrust in the necessary direction to compensate for the rotor torque, the nacelle and the rotor deflection mechanism, providing a sufficient clearance of the rotor in its deflected position and deflected together with the rotor of the device on which the rotor is mounted, with the top of the fuselage, characterized in that the nacelle is made deflectable together with the rotor shaft of the rotor, at least part of which is installed in the deflected nacelle, an additional a swivel nacelle with a swash plate with its control system, the rotor deflection mechanism made in the form of a mechanical drive, which provides the possibility of increasing the thrust vector of the rotor in the horizontal direction by tilting the rotor shaft by a predetermined angle and providing sufficient clearance between the nacelle and the plane of rotation of the rotor blades in deflected rotor position and the upper part of the fuselage, the tail rotor is made with at least two blades and can be rotated

Claims

1. A high-speed rotorcraft with vertical take-off and landing, comprising at least one propulsion device, fuselage, tail unit with a vertical keel mounted on it at an angle to the incoming air flow, creating a compensating torque with respect to the rotor fixed to the shaft , with a rudder attached to a vertical keel, a horizontal stabilizer with a height rudder attached to it, a tail rotor in an annular cowl at the tail of the aircraft to ensure thrust in the necessary direction to compensate for the rotor torque, the nacelle and the rotor deflection mechanism, providing a sufficient clearance of the rotor in its deflected position and deflected together with the rotor of the device on which the rotor is mounted, with the top of the fuselage, characterized in that the nacelle is made deflectable together with the rotor shaft of the rotor, at least part of which is installed in the deflected nacelle, an additional a swivel nacelle with a swash plate with its control system, the rotor deflection mechanism made in the form of a mechanical drive, which provides the possibility of increasing the thrust vector of the rotor in the horizontal direction by tilting the rotor shaft by a predetermined angle and providing sufficient clearance between the nacelle and the plane of rotation of the rotor blades in deflected rotor position and the upper part of the fuselage, the tail rotor is made with at least two blades and can be rotated the aircraft in the helicopter mode of its flight by increasing or decreasing the tail rotor thrust and is located in the duct channel, the wing is made of a small area with ailerons designed to change the position of the aircraft along the roll.

2. The aircraft according to claim 1, characterized in that the rotor deflection mechanism is configured to tilt the rotor by a predetermined angle (+ 70 °> α> -45 °) when it transitions from vertical to inclined position.

3. The aircraft according to claim 1, characterized in that at least one mover is made in the form of an electric motor.

4. The aircraft according to claim 1, characterized in that the tail rotor is configured to shut off in horizontal flight mode.