Propulsion system for high speed vtol aircraft

Claim 1

A COMBUSTION EXHAUST NOZZLE-DIVERTER VALVE ASSEMBLY FOR USE IN HIGH SPEED VTOL AIRCRAFT, SAID ASSEMBLY COMPRISING: (A) A HOUSING HAVING AT LEAST ONE PORT THEREIN, (B) A FIRST WALL DOWNSTREAM OF SAID PORT WITH RESPECT TO THE DIRECTION OF FLUID FLOW THROUGH SAID ASSEMBLY, SAID FIRST WALL DIVERGING OUTWARDLY IN THE DOWNSTREAM DIRECTION AND DEFINING A DIVERGENT PASSAGEWAY, (C) A PLURALITY OF MOVABLE VALVE SEGMENTS UPSTREAM OF SAID FIRST WALL, (D) AND MEANS TO MOVE SAID VALVE SEGMENTS BETWEEN FIRST AND SECOND OPERATIVE POSITIONS, (E) SAID VALVE SEGMENTS IN SAID FIRST POSITION DEFINING A SECOND WALL CONVERGING IN THE DOWNSTREAM DIRECTION TO FORM WITH SAID FIRST WALL A CONVERGING-DIVERGING NOZZLE, SAID PORT BEING FORMED IN THE CONVERGENT PORTION OF SAID NOZZLE, SAID SECOND WALL BLOCKING SAID PORT TO PREVENT FLUID FLOW THERETHROUGH, (F) AND SAID VALVE SEGMENTS IN SAID SECOND POSITION DEFINING A THIRD WALL BLOCKING THE DIVERGENT PASSAGEWAY DEFINED BY SAID FIRST WALL TO PREVENT FLOW THERETHROUGH AND PERMITTING FLUID FLOW THROUGH SAID PORT.