Coaxial rotor/wing aircraft

摘要

A system and method which enable efficient, rapid and safe transition between rotary-wing and fixed-wing flight mode in rotor/wings aircrafts is disclosed. The aircraft comprises of two rotor/wings on the same axis of rotation, one above the fuselage and the other one under the fuselage. During rotary-wing mode, the rotor/wings rotate coaxially and provide vertical lift. During transition between rotary-wing and fixed-wing modes, the synchronised operation of the two rotor/wings maintains lateral symmetry of lift on the aircraft. The reaction of the rotor/wings on the fuselage is also canceled. During fixed-wing flight mode, the two rotor/wings are stopped and locked in a biplane configuration, both providing lift as fixed wings. The rotor/wings may be further reconfigured for higher subsonic or supersonic speed. Tandem and multiple rotor/wings aircrafts with increased cargo capacity, speed and range, comprise of multiple of these coaxial rotor/wings.

主权项

1. An aircraft having a first flight mode, a transition flight mode and a second flight mode comprising:
a fuselage; a first group of rotor/wings comprising at least one rotor/wing; a second group of rotor/wings comprising at least one rotor/wing; at least one propulsion unit to provide forward thrust; at least one engine to power said propulsion unit and said rotor/wings; wherein said rotor/wings comprising of a plurality of wings rotatably mounted to said fuselage; wherein during said first flight mode, said first group and said second group of rotor/wings rotate in counter-rotation to produce vertical lift; wherein during said second flight mode, said rotor/wings are not rotating and at least one said rotor/wing is positioned to produce aerodynamic lift as fixed wings; wherein during said transition flight mode when said aircraft is transiting between said first flight mode and said second flight mode, said first group of rotor/wings is operated in coordination with said second group of rotor/wings, in order to reduce the destabilizing forces on said fuselage, resulting due to said transition mode.