Vertical takeoff and landing aircraft专利检索-起落架飞行器飞机类型专利检索查询-专利查询网

Vertical takeoff and landing aircraft

阅读：834发布：2024-02-19

专利汇可以提供Vertical takeoff and landing aircraft专利检索，专利查询，专利分析的服务。并且A vertical takeoff and landing (VTOL) aircraft has a discusshaped fuselage with a plurality of angularly equispaced liftgenerating assemblies. Each assembly comprises a rotor above or flush with the fuselage, a compressor in the fuselage drawing air in from above, and a nozzle below the fuselage for expelling the air from the compressor in a jet. The nozzles can be rotated to point in any direction. Thus, according to the settings of the nozzles, the aircraft can rise or sink vertically and move in any horizontal direction.，下面是Vertical takeoff and landing aircraft专利的具体信息内容。

权利要求

1. An aircraft comprising: a closed-skin discus-shaped fuselage of circular outline having conical upper and lower halves centered on an axis and defining all of the airfoil surface of the aircraft within said outline, the center of gravity of the aircraft being located along said axis in said lower half; a plurality of lift-generating assemblies spaced around said fuselage, each of said assemblies including a respective rotor rotatable along the top of said fuselage, means for rotationally driving said rotor, a respective compressor in said fuselage below said rotor drawing in and compressing air froM below said rotor, and a respective nozzle connected to said compressor to expel from below said fuselage the air compressed thereby, said nozzles projecting downwardly below said fuselage and exclusively forming rudder controls for said aircraft; and control means for selectively directionally orienting each of said nozzles, each of said control means including a rotatable disk mounted on and substantially flush with the lower surface of said fuselage, said nozzle being formed at the lower end of a fixed-elbow tube rising through the disk to the compressor, and drive means connected to said disk for rotating same and thereby rotating said nozzle.

2. The aircraft defined in claim 1 wherein each of said control means further includes means for orienting the respective tube and nozzle in a vertical plane.

3. The aircraft defined in claim 1 wherein said rotor is an airscrew spaced above said fuselage.

4. The aircraft defined in claim 1 wherein said rotor is a fan substantially flush with the upper surface of the fuselage.

5. The aircraft defined in claim 1 wherein said nozzles are formed with longitudinal fins below said fuselage.

6. The aircraft defined in claim 1 further comprising a shaft, said rotor and said compressor being mounted on said common shaft and said means for rotationally driving said rotor thereby also driving said compressor.

7. The aircraft defined in claim 1 wherein said assemblies are angularly equispaced around said fuselage.

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