Patent ID: 7178757

Claim:
An aircraft comprising: a. a propeller arranged to rotate and provide forward propulsion of the aircraft; b. a rotating wing arranged to freely rotate with forward motion of the aircraft and a rotor head adjustably connecting the rotating wing to the aircraft such that the rotating wing axis of rotation in the aircraft front-to-rear and side-to-side directions may be adjusted; c. a rudder and horizontal stabilizer assembly, the rudder adjustably arranged to provide airborne aircraft yaw control and the horizontal stabilizer arranged to provide airborne aircraft pitch stability; d. an engine and a propeller drive assembly arranged such that the engine rotation is reduced in rotational speed and transmitted to rotate the propeller; e. one or more front wheels and one or more rear wheels arranged on a front-to-rear axis of the aircraft such that the aircraft is movably supported on a surface wherein the aircraft on the ground may accelerate along the ground surface with forward motion from the propeller rotation until the aircraft forward speed is sufficient that the rotating wing provides sufficient lift force such that the aircraft becomes airborne; f. a control column with a gimbal mount arranged such that the control column rotates on a rotational axis and tilts on front-to-rear and side-to-side transverse axes, the control column movably connected to one or more wheels, wherein rotating the control column turns the one or more wheels to an angle to the aircraft front-to-rear axis, and the control column movably connected to the rotor head wherein moving the control column in the front-to-rear transverse axis adjusts the rotating wing axis of rotation in the front-to-rear transverse axis, and moving the control column in the side-to-side transverse axis adjusts the rotating wing axis of rotation in the side-to-side transverse axis.