Solid propellant rocket thrust vectoring system

Claim 1

A CONVERGENT, DIVERGENT ROCKET NOZZLE COMPRISING A FIXED SECTION HAVING A FLOW PASSAGE INCLUDING THE NOZZLE THROAT OPEN AT ITS DIVERGENT OUTER END, A SKIRT MEMBER HAVING A FLOW PASSAGE OPEN TO THE OUTER END OF THE FIXED SECTION FLOW PASSAGE AND CLOSELY OVERLAPPING SAID OUTER END TO FORM A SUBSTANTIALLY TIGHT JOINT, MEANS MOUNTING SAID SKIRT FOR SLIDING PIVOTAL MOVEMENT RELATIVE TO SAID FIXED SECTION BETWEEN A FIRST POSITION WHEREIN SAID FLOW PASSAGES ARE ALIGNED AND DEFLECTED POSITIONS WHEREIN SAID FLOW PASSAGES ARE INCLINED RELATIVE TO EACH OTHER, GASES FLOWING THROUGH SAID PASSAGES WITH A VELOCITY GREATER THAN MACH ONE, SAID FIXED SECTION AND SKIRT MEMBER COOPERATING WHEN IN SAID DEFLECTED POSITIONS TO ESTABLISH A COMPRESSION WAVE AND AN EXPANSION WAVE EACH EMANATING FROM THE JOINT BETWEEN SAID FIXED SECTION AND SKIRT MEMBER AND CROSSING WITHIN SAID SKIRT MEMBER FLOW PASSAGE WHEREBY SAID GASES FLOWING THROUGH SAID PASSAGES ARE DEFLECTED BY PASSAGE THROUGH SAID WAVES TO A DEFLECTABLE ANGLE GREATER THAN THE ANGLE OF DEFLECTION OF SAID SKIRT MEMBER.