Tilt-rotor vertical takeoff and landing aircraft

摘要

The present disclosure provides an aircraft system in the tilt-rotor category with four propulsion units where the tilt angle and thrust of each unit is controlled independently of the other units. The tilt angle for each unit can be adjusted anywhere from below horizontal, to fully forward, and to greater than 180 degrees (i.e. tilted backwards). As a result, the system enables greater control during all phases of flight. Due to continuous, independent tilt control of the angle and thrust of each rotor, the present aircraft can avoid stalls much easier than traditional fixed-wing aircraft and other VTOL designs, as thrust vectors can at any moment be adjusted to compensate for loss of wing lift, making the aircraft safer to use.