Patent ID: 6543720
Filing Date: 2003-04-08
Classification: B64C,Y02T

Abstract:
An aircraft, comprising:a canard control surface and an aft control surface; the canard control surface comprising an integral aerofoil which in its entirety pivots about a first axis of rotation, the canard control surface having a centre of lift which is rearward of the first axis; the aft control surface being rearward of the canard control surface and comprising an integral aerofoil which in its entirety pivots about a second axis of rotation, the aft control surface having a center of lift which is rearward of the first axis; the canard control surface and the aft control surface acting in unison to produce a directional change in the aircraft; the canard control surface and the aft control surface being both generally horizontally oriented and acting in unison by rotating in different directions; the aft control surface comprising the primary lifting wings of the aircraft, the wings each being independently rotatable about the second axis.