초록 ▼

An aircraft capable of vertical short takeoff and landing is shown according to the teachings of the present invention as including four separate engine locations. In its most preferred form, the first and second engines are located on opposite sides of the fuselage of the aircraft and are pivotal a

An aircraft capable of vertical short takeoff and landing is shown according to the teachings of the present invention as including four separate engine locations. In its most preferred form, the first and second engines are located on opposite sides of the fuselage of the aircraft and are pivotal about first and second axes which are in a plane perpendicular to the longitudinal axis of the aircraft and which are in front of the center of gravity of the aircraft. The third and fourth engines are located on opposite sides of the fuselage of the aircraft and are pivotal about third and fourth pivot axes which are parallel to the first and second axes of the first and second engines, respectively, but which are behind the center of gravity of the aircraft. The engines are mounted and rotated about their respective pivot axes by a system including a shaft having a first end operatively attached to the engine. The shaft is pivotally mounted to the fuselage of the aircraft by a bearing system including first and second tapered roller bearing members wedged between frusto-conical surfaces formed in a bearing mount, on the shaft, and on a collar removably attached to the shaft. A drive gear is attached to the shaft for rotation by a worm gear driven in turn by actuators such as hydraulic or electric motors. Thus, the engines at all four locations can be simultaneously pivoted about their respective axes.

대표청구항 ▼

Engine mounting and rotating system for use in an aircraft capable of vertical and/or horizontal flight including a fuselage comprising, in combination: a mount formed in the fuselage; a shaft having a first end and a second end, with the first end of the shaft being operatively attached to the engi

Engine mounting and rotating system for use in an aircraft capable of vertical and/or horizontal flight including a fuselage comprising, in combination: a mount formed in the fuselage; a shaft having a first end and a second end, with the first end of the shaft being operatively attached to the engine; bearing means located between the shaft and the mount for allowing the rotation of the shaft but preventing the shaft from moving in any other direction; and means for rotating the shaft in the mount such that the thrust of the engine can be directed at the desired angle by rotating the shaft within the mount, with the bearing means comprising, in combination: first frusto-conical surface formed on the shaft; second, frusto-conical surface formed in the mount complementary to the first frusto-conical surface; first tapered roller bearing members rotatably received by and between the first and second frusto-conical surfaces; a collar removably attached to the shaft, with the collar including a third frusto-conical surface; fourth frusto-conical surface formed on the mount complementary to the third frusto-conical surface; and second tapered roller bearing members rotatably received by and between the third and fourth frusto-conical surfaces.