Transverse wing actuation system

What is claimed is an aircraft sustentation system comprised of a fuselage, and two sets of swept and tapered wings;

• the primary wings being fixed to the fuselage of the aircraft above and in front of the second set of wings, this second set being capable of remaining in a position parallel to the primary wings with the leading and trailing edges of both sets of swept, tapered wings also remaining parallel for high speed flight, the second set of wings capable of being tilted in a manner where the leading edge of the secondary wings approach the trailing edges of the primary wings in a manner to create one high lift producing airfoil from the two individual sets of wings, wherein the improvements comprise:
• a means of tilting the secondary wing from the parallel high speed position to the tilted high lift position utilizing a wing tilt lever arm with a fixed and attached transverse wing support arm, a transverse wing tilt lever mounting bearing and a universal transverse wing actuation arm bearing, both bearings cooperating with each other to support the wing tilt lever and wing actuation arm as a unit during actuation of this system, and both bearings being located a distance from the junction where the wing tilt lever and the transverse wing actuation arm meet to form one unit which rotates upon a motive force from the power source, thus canting, laterally tilting, and forward sweeping the rearward swept, tapered transverse wing in a manner where the leading edge of the transverse wing approaches the trailing edge of the swept primary wing with a parallel relationship between the edges, thus forming one high lift producing airfoil.