A homeostatic flying hovercraft preferably utilizes at least two pairs of counter-rotating ducted fans to generate lift like a hovercraft and utilizes a homeostatic hover control system to create a flying craft that is easily controlled. The homeostatic hover control system provides true homeostasis of the craft with a true fly-by-wire flight control and control-by-wire system control.

A homeostatic flying hovercraft preferably utilizes at least two pairs of counter-rotating ducted fans to generate lift like a hovercraft and utilizes a homeostatic hover control system to create a flying craft that is easily controlled. The homeostatic hover control system provides true homeostasis of the craft with a true fly-by-wire flight control and control-by-wire system control.

The invention relates to an engine (2) for a flying body (1), with an annular vortex guide element (3) which, seen in section, has an air inlet opening (6) arranged centrally with respect to a longitudinal central axis (4) of the engine (2) and, at a distance from the air inlet opening (6), an air outlet opening (7) arranged centrally with respect to the longitudinal central axis (4), which are connected to one another in terms of flow via an intake duct (5) bounded by the vortex guide element (3) and accommodating an air conveying device (8), wherein the air outlet opening (7) is overlapped by an air deflecting element (9) which is arranged geodetically above the vortex guide element (3) during intended operation of the engine (2) and which extends radially outwards from the air outlet opening (7) so that it delimits with the vortex guide element (3) an air exit gap (11) which is in flow connection with the air outlet opening (7). It is provided that the vortex guide element (3) is in the form of a body of rotation which is formed by rotation about an axis of rotation of a closed curve having a continuous course at least on its radially outer side, and in that the air inlet opening (6) opens directly into an outer environment (19) of the engine (2), so that during intended operation of the engine (2) air is conveyed from the side of the engine (2) facing away from the air deflecting element (9) through the air inlet opening (6) into the intake duct (5). The invention further relates to a method for operating an engine (2) for a flying body (1) as well as a flying body (1) with at least one engine (2).

The invention relates to an engine (2) for a flying body (1), with an annular vortex guide element (3) which, seen in section, has an air inlet opening (6) arranged centrally with respect to a longitudinal central axis (4) of the engine (2) and, at a distance from the air inlet opening (6), an air outlet opening (7) arranged centrally with respect to the longitudinal central axis (4), which are connected to one another in terms of flow via an intake duct (5) bounded by the vortex guide element (3) and accommodating an air conveying device (8), wherein the air outlet opening (7) is overlapped by an air deflecting element (9) which is arranged geodetically above the vortex guide element (3) during intended operation of the engine (2) and which extends radially outwards from the air outlet opening (7) so that it delimits with the vortex guide element (3) an air exit gap (11) which is in flow connection with the air outlet opening (7). It is provided that the vortex guide element (3) is in the form of a body of rotation which is formed by rotation about an axis of rotation of a closed curve having a continuous course at least on its radially outer side, and in that the air inlet opening (6) opens directly into an outer environment (19) of the engine (2), so that during intended operation of the engine (2) air is conveyed from the side of the engine (2) facing away from the air deflecting element (9) through the air inlet opening (6) into the intake duct (5). The invention further relates to a method for operating an engine (2) for a flying body (1) as well as a flying body (1) with at least one engine (2).