초록 ▼

An aircraft adapted for flight in helicopter mode with its longitudinal axis oriented generally vertically and in airplane mode with its longitudinal axis oriented generally horizontally is provided with the capability of launching and landing with the tail end directed skyward. The invention also i

An aircraft adapted for flight in helicopter mode with its longitudinal axis oriented generally vertically and in airplane mode with its longitudinal axis oriented generally horizontally is provided with the capability of launching and landing with the tail end directed skyward. The invention also includes improvements to the controllability and efficiency of aircraft in helicopter mode provided by the stabilizer wings and relative rotation of the fuselage section about the aircraft's longitudinal axis. The aircraft has an elongate boom positioned between the rear fuselage and the stabilizer wings for engagement with a base structure. The base structure may be attached to a building, a trailer transporter, a ship or some other structure. The base may be a beam having latching arms that swing inward when pressure from the boom is applied, then trap the boom in a recess between the latching arm and beam, thereby suspending the aircraft. An actuator for releasing the latching arms is provided to allow the aircraft to launch.

대표청구항 ▼

[ I claim as my invention:] [20.] An aircraft having a fuselage with an aft portion and a fore portion, said fuselage having a longitudinal axis, the aircraft being adapted for flight in a helicopter mode with the longitudinal axis oriented generally vertically and in an airplane mode with the longi

[ I claim as my invention:] [20.] An aircraft having a fuselage with an aft portion and a fore portion, said fuselage having a longitudinal axis, the aircraft being adapted for flight in a helicopter mode with the longitudinal axis oriented generally vertically and in an airplane mode with the longitudinal axis oriented generally horizontally, the aircraft comprising:(a) at least a pair of rotor blades, each blade having a lateral axis and each blade being connected to the fuselage for rotation about its lateral axis relative to the fuselage; and(b) a plurality of stabilizing wings connected to said fuselage;(c) at least one of said stabilizing wings is rotatable in plane with the airflow in translational helicopter mode flight.