Variable sweep aircraft wing

Claim 1

AN AIRCRAFT HAVING SUPERSONIC FLIGHT CAPABILITIES COMPRISING A FUSELAGE HAVING A FINENESS RATIO SUITABLE FOR SUPERSONIC FLIGHT, PROPULSION MEANS CARRIED BY SAID FUSELAGE, AN EMPENNAGE ASSEMBLY CARRIED BY SAID FUSELAGE ADJACENT THE AFTER END THEREOF, AND A WING CONNECTED TO EACH SIDE OF SAID FUSELAGE AND PROJECTING SUBSTANTIALLY HORIZONTALLY AND OUTWARDLY THEREFROM, EACH OF SAID WINGS INCLUDING: A MAIN WING PANEL HAVING A STRAIGHT LEADING EDGE PIVOTALLY CONNECTED TO SAID FUSELAGE NEAR THE OUTBOARD EDGE THEREOF FOR ROTATION IN A SUBSTANTIALLY HORIZONTAL PLANE BETWEEN A LOW SWEEP POSITION IN WHICH THE INBOARD END OF SAID LEADING EDGE IS CONTIGUOUS TO THE SIDE OF SAID FUSELAGE AND A HIGH SWEEP POSITION IN WHICH THE INBOARD END OF SAID LEADING EDGE IS SPACED FROM SIDE TO SIDE OF SAID FUSELAGE, A FORWARD WING PANEL HAVING A LEADING EDGE PIVOTALLY CONNECTED ABOUT A SINGLE PIVOT POINT ADJACENT A FORWARD EXTREMITY THEREOF TO SAID FUSELAGE NEAR THE OUTBOARD EDGE THEREOF FOR ROTATIONAL MOVEMENT ONLY ABOUT SAID SINGLE PIVOT POINT AND IN SAID SUBSTANTIALLY HORIZONTAL PLANE BETWEEN A HIGH SWEEP POSITION IN WHICH SAID FORWARD WING PANEL LEADING EDGE IS COLLINEAR WITH SAID MAIN WING PANEL LEADING EDGE WHEN SAID MAIN WING PANEL IS DISPOSED IN SAID MAIN WING PANEL HIGH SWEEP POSITION AND A RETRACTED POSITION IN WHICH SAID FORWARD WING PANEL IS POSITIONED WITHIN SAID FUSLAGE AND IN WHICH SAID FORWARD WING PANEL LEADING EDGE IS CONTIGUOUS TO THE SIDE OF SAID FUSELAGE, SAID FORWARD WING PANEL HAVING A REARWARD PORTION OVERLAPPING A PORTION OF SAID MAIN WING PANEL, AND MEANS LINKING SAID OVERLAPPING PORTIONS OF SAID FORWARD AND MAIN WING PANELS FOR EFFECTING RETRACTION OF SAID FORWARD WING PANEL INTO SAID FUSELAGE WHEN SAID MAIN WING PANEL IS ROTATED FROM SAID MAIN WING PANEL HIGH SWEEP POSITION TO SAID MAIN WING PANEL LOW SWEEP POSITION.