| 摘要 |
An aircraft having a substantially circular body having a profile in the direction of flight as a profile of an airplane wing, at least two concentric counter-rotating turbo-blade assemblies (15) within said body for effecting a vertical lifting air stream through said assemblies (15). Power generating devices (6, 13, 21, 23) and devices (122, 123, 124, 126) for coupling the power generating devices to the turbo-blade assemblies (15) for maintaining them in rotary motion. It also includes thrusting devices (6, 18, 157) coupled to the power generating devices for applying horizontal thrust to the aircraft, retro-boosting devices (21, 169) including a plurality of combustion chambers (104) located below the turbo-blade assemblies for boosting said vertical lifting airstream. Also included is a compressed air plenum (106) disposed below said turbo-blade assemblies (15) in fluid communication with the combustion chambers (104) and to the intake portion of the power generating means for supplying oxygen for sustaining combustion in said combustion chambers (104) and for sustaining power in said power generating means (6, 13, 21, 23), including upper vanes (7, 101) disposed above said turbo-blade assemblies (15) for ingesting air, and lower vanes (24) disposed below said compressed air plenum (106) for exhausting air, and respective upper and lower vane control means (110). |
