Abstract: An aircraft (10) including a stowable, wingtip mounted, vortex turbine (30) for dissipating or extracting energy from a lift induced vortex (28) emanating from the aircraft (10) is provided. The vortex turbine (30) includes a first and a second array (38, (40) of blades (32a,b) (34a,b) extending respectively from a first and a second hub section (32), (34). Hub sections (32), (34) may be independently pivoted about a common axis of rotation (36) to a stowed position for landing, take-off, or ground operation, whereat none of the blades (32a,b) (34a,b) extend below a minimum ground clearance of the aircraft, or beyond a maximum horizontal extension of the wing (16). In flight, the hub sections (32), (34) may be deployed and the pitch of the blades adjusted to maximize dissipation of the lift induced vortex (28), thereby minimizing drag and providing improved safety for other aircraft flying through the wake of the aircraft (10) producing the vortex (28).

Abstract: A system and method of separating the gaseous components of air to provide an oxygen-enriched gas stream and a nitrogen-enriched gas stream are disclosed. The on-board gas generation system and method generate an oxygen-enriched stream including substantially pure oxygen, such as about 99% or greater oxygen, and, if desired, having a pressure of up to about 10,000 pounds per square inch, thereby eliminating the need for a separate compressor to compress the oxygen-enriched gas stream. The on-board oxygen generation system and method are used in enclosed vehicles, like aircraft and military tanks, to supply substantially pure oxygen for breathing, especially at high altitudes and in contaminated atmospheres.