Aircraft

Abstract

An aircraft that has a set of wings which spin about respective axes that are laterally spaced apart in a horizontal plane of the aircraft, parallel to each other, and positioned adjacent respective frame portions, each of said frame portions defining a continuous surface, having a semi-circular cross-section means being provided to drive the sets of wings so that, as they spin, each wing of said sets of wings moves sequentially upwards inside its respective frame portion, and downwards outside its respective frame portion so as to provide lift to the aircraft.

Description

According to the present invention there is provided an aircraft that comprises sets of wings which spin about respective axis that are laterally spaced apart in a horizontal plane of the aircraft, parallel to each other, and positioned adjacent respective frame portions, each of said frame portion defining a continuous surface, having a semi-circular cross-section, means being provided to drive the set of wings so that, as they spin, each wing of said set of wings moves sequentially upwards inside its respective frame portion, and downwards outside respective frame portion so as to provide lift to the aircraft.

FIGS. 1-8 all relate to a single embodiment of the invention; some features essential to the invention have been omitted from some of the figures so as to allow a clearer understanding of the features shown.

FIG. 1 shows a side view of the top half of the aircraft. An engine (E) is connected to two shafts (S). Each shaft is connected to a pair of wings (W). The end of each shaft which is furthest from its engine is held by a shaft-holder (SH). The engine and each shaft-holder are supported by a platform (P).

Each shaft and its wings are rotated by the engine. The size, shape, number, mountings and positions of every engine on the aircraft are optional, as are the size, shape, number, mountings and positions of every wing.

FIG. 2 shows a head on view of a pair of wings which are rotating. The wings here are flat, but they could also be bent or curved to gain better purchase on air.

FIG. 3. Another engine and another two pairs of wings are added on the other side of the aircraft.

FIG. 4. The rotating wings, when in the outside positions, are unimpeded and provide lift.

The wings in the inside positions are enclosed inside semi-circular frames (F) which may, as here, be linked to each other by horizontal frames (F). The upper horizontal frame may be used as a wing. The platform (P) may be used as wings.

FIG. 5. A means of propulsion (MOP)—maybe a jet or propeller engine—is added. As a means of steering a pair of rudders (R) may be added or the means of propulsion may be rotated. If propellers are the MOP, they may be rotated by the engines which rotate the wings.

FIG. 6 shows how braking may be achieved. The rudders (R) can be rotated inwards into the blast of air or gases from the means of propulsion (MOP). Braking may also be achieved by reversing the thrust of the MOP. FIG. 6 shows braking system from side.

FIG. 7 shows the braking system as seen from above. The rudders (R) may be heat resistant.

FIG. 8 shows the aircraft as seen from the front. The number of passengers and/or crew carried in the cabin (C) is optional. In FIG. 8 the aircraft has two rear wheels (RW) and one nose wheel (NW). This arrangement can be varied.

In another embodiment of the aircraft, the shafts (S) are extended through the shaft holders, and an additional pair of wings added to each extension so that each engine is rotating eight wings instead of four.

In a further embodiment, the upper horizontal frame is extended on both sides of the aircraft to provide additional wing surface area.

In a still further embodiment, retractable wings are installed within the platform (P) such that they can be extended to provide increased wing surface area during flight. It should be noted that these wings must be retracted within the platform during use of the rotating wings (W), in order that the rotating wings are able to generate lift.

For smaller versions of the aircraft, a parachute can be added at the top of the aircraft as a safety measure, to be deployable in the event of engine failure.

In a yet further embodiment, two engines are used on each side of the aircraft, rather than a single engine on each side of the aircraft as shown in FIG. 1. In this manner, if one engine fails on one side of the aircraft, the second engine can still provide power to the rotating wings. In this embodiment, the engines could be positioned at each end of the shafts (S) on each side of the aircraft rather than at the centre of each side as shown in FIG. 1.

On larger versions of the aircraft, further engines can be added to each side of the aircraft as appropriate.

Claims

1. An aircraft comprising: sets of wings which spin about respective axes that are laterally spaced apart in a horizontal plane of the aircraft, parallel to each other, and positioned adjacent respective frame portions; each of said frame portions defining a continuous surface, having a semi-circular cross-section, the cross-section extending from a point directly above the axis of its respective wing, and to a position directly below the same axis; the cross-section extending from a point directly above the axis of its respective wing, and to a position directly below the same axis; and means being provided to drive the sets of wings so that, as they spin, each wing of said sets of wings moves sequentially upwards inside its respective frame portion, and downwards outside its respective frame portion so as to provide lift to the aircraft.

2. An aircraft as claimed in claim 1, further comprising: at least one wing which does not spin.