Unmanned aerial aircraft having a single engine with dual jet exhausts

Claim 2

In an aircraft, an improved thrust system comprising: a single engine located forwardly of the aircraft's center of gravity, at a forwardly, upwardly acute angle to a longitudinal axis of the aircraft, and enclosed within a fuselage and having bifurcated exhausts; first conduit means for directing respective exhaust flows in a first direction transverse of the engine, the flows equaling an entire exhaust output of the engine; first and second nozzles rotatably mounted to ends of corresponding first conduit means for movement in mutually parallel planes separated by a center line of the aircraft, and which redirect exhaust flows in directions perpendicular to the first conduit means, at individually adjusted angles; wherein thrust from the engine can be individually vectored by the nozzles to achieve several degrees of freedom primarily during take off and landing.

Claim 3

In an unmanned aircraft, an improved thrust system comprising: a single engine located forwardly of the aircraft's center of gravity, at a forwardly, upwardly acute angle to a longitudinal axis of the aircraft, and enclosed within a fuselage and having bifurcated exhausts; first conduit means for directing respective exhaust flows in a first direction transverse of the engine, the flows equaling an entire exhaust output of the engine; first and second nozzles rotatably mounted to ends of corresponding first conduit means for movement in mutually parallel planes separated by a center line of the aircraft, and which redirect exhaust flows in directions perpendicular to the first conduit means, at individually adjusted angles; and means connected to the ends of the first and second nozzles for deflecting exhaust flowing therethrough and individually vectoring engine thrust to achieve several degrees of freedom primarily during take off and landing.

Claim 4

In an unmanned aircraft, an improved thrust system comprising: a single engine located forwardly of the aircraft's center of gravity, at a forwardly, upwardly acute angle to a longitudinal axis of the aircraft, and enclosed within a fuselage and having bifurcated exhausts; first conduit means for directing respective exhaust flows in a first direction transverse of the engine, the flows equaling an entire exhaust output of the engine; first and second nozzles rotatably mounted to ends of corresponding first conduit means for movement in mutually parallel planes separated by a center line of the aircraft, and which redirect exhaust flows in directions perpendicular to the first conduit means, at individually adjusted angles; and means connected to the ends of the first and second nozzles for deflecting exhaust flowing therethrough and individually vectoring engine thrust to achieve several degrees of freedom primarily during take off and landing.

Claim 5

The unmanned aircraft set forth in claim 2 wherein the means connected at each nozzle end comprises an assembly of orthogonal pitch and roll vanes having a central axis angularly rotatable with respect to the central axis of a respective nozzle for achieving pitch and roll control; differential deflection from the pitch vanes resulting in yaw control.

Claim 6

The unmanned aircraft set forth in claim 2 wherein the means connected at each nozzle end comprises a roll vane which pivots generally laterally with respect to a center line of the nozzle to control roll.

Claim 7

The unmanned aircraft set forth in claim 2 wherein the means connected at each nozzle end comprises a gimballed nozzle which laterally deflects exhaust flow therethrough to achieve roll control.

Claim 8

The unmanned aircraft set forth in claim 2 together with an inlet formed in a forward section of the fuselage for admitting air to an engine intake.