Abstract: A personal aircraft (PAC) capable of vertical take-off and landing (VTOL) comprises a fixed wing and a fuselage with a passenger compartment having a front, a rear and two sides, and a plurality of independently powered thrusters, preferably integrated into the wing, on each side of the fuselage. The aircraft has a lift to drag ratio equal to or greater than 2. The thrusters, which are ducted fan units capable of providing a vertically upward force to the aircraft, are provided with such redundancy that the aircraft can hover with at one thruster inoperative on each side of the fuselage. At least one thruster on each side of the fuselage preferably comprises a “levitator” which creates lift from the airfoil-like air inlet as well as from the acceleration of air from inlet to outlet.

Abstract: An end stop is disclosed for limiting the maximum displacement of a flexible member so as to minimize stress on this member and thus provide an extended surface life. The flexible member is rigidly supported at at least two spaced-apart points such that the flexible member can flex in the region between these points. The end stop includes a support member for clamping the flexible member at the two supporting points and a wall surface arranged in opposed, facing relationship to the flexible member in the region between the two points. The curvature of the wall surface is defined by first and second curves that form a continuous curvature and have first and second derivatives of the local angle .phi. of the tangent to the curve with respect to the distances along the curve which are zero.

Abstract: A ground-air-water craft comprises a fuselage body with a passenger compartment mounted thereon, a box-type main wing connected to the fuselage and extending outwardly on both sides thereof, the main wing comprising an upper wing and a lower wing which are substantially horizontal and which have a total wing span in the range of 5 to 10 feet, as well as a right side member and a left side member, each side member extending substantially vertically and connected between the lateral ends of the upper and lower wings on the respective right and left sides of the craft. The craft also comprises a control or canard wing connected to the fuselage and extending outwardly on both sides of the fuselage with a wing span no greater than 10 feet.