Patent ID: 8998131
Filing Date: 2015-04-07
Classification: B64C,B64D,B64G,G05D

Abstract:
1. A system for providing enhanced control of a flight vehicle about either the pitch or yaw axes during flight, comprising: a first plurality of engines of the flight vehicle having a positive tangential cant such that a thrust line from each of the first plurality of engines is misaligned with a centerline of the flight vehicle in a tangential direction with respect to a circumference of the flight vehicle; and a second plurality of engines of the flight vehicle having a negative tangential cant such that a thrust line from each of the second plurality of engines is misaligned with the centerline of the flight vehicle in a tangential direction with respect to a circumference of the flight vehicle and opposite to the first plurality of engines, wherein the first and second plurality of engines are spaced equidistant from one another and from the centerline of the flight vehicle, each of the first plurality of engines alternately positioned relative to each of the second plurality of engines, and the first and second plurality of engines configured for differential throttling to control attitude of the flight vehicle about pitch, yaw and roll axes wherein the positive and negative tangential cants of the first and second plurality of engines enhance movement of the flight vehicle about one of the pitch and yaw axes.