发明名称 High speed vertical take-off and land aircraft
摘要 A high-speed vertical take-off and land (HSVTOL) aircraft includes a disk-shaped fuselage wit a rotatable fan having a nozzle ring driven by hot jet gasses and fan air from jet engines. Feed ducts and an annular plenum, have a composite duct-in-duct configuration to separate the hot gases from the relatively cool fan air. High efficiency air bearings serve to support the rotatable fan assembly on the fuselage in the vertical direction, and rollers around the perimeter provide horizontal support and stability. A bearing and seal interface hub and other components, are isolated from the hot gases. The combined exhaust is ejected downwardly at approximately 15° for maximum fan spin and provide direct reaction lift. The fan blades are angled at approximately 57° with moveable airfoil portions and stationary trailing flap portions to provide maximum lift and down wash. Various diverter valves and bypass doors are provided for hot gas/air control. Decoupler valves can interrupt all flow for engine out operation. Control of the pitch, roll and yaw is provided by aero flaps providing control surfaces in the path of the down wash. When twisted about a substantially horizontal control axis, the flaps generate lift, as well as being modulated for attitude control. Aerodynamic disk-shape of the fuselage provides high lift, low drag necessary to support the efficient high speed performance. A control circuit includes an on board CPU controller that operates and coordinates all functions through the various actuators, valves, transducers and other control components.
申请公布号 US6382560(B1) 申请公布日期 2002.05.07
申请号 US20000655966 申请日期 2000.09.06
申请人 GO AIRCRAFT LTD. 发明人 OW GORDON Y. W.
分类号 B64C27/20;B64C29/00;B64C39/00;B64D27/20;(IPC1-7):B64C29/00 主分类号 B64C27/20
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