Supersonic inlet

Claim 1

A SUPERSONIC, TWO-DIMENSIONAL, COMBINATION EXTERNAL-INTERNAL COMPRESSION AIR INLET SYSTEM HAVNG A LONGITUDINAL AXIS AND COMPRISING: A FIRST SURFACE ANGLED WITH RESPECT TO SAID AXIS AND GENERATING AN INITIAL OBLIQUE SHOCK WAVE EXTERNALLY OF THE INLET, SAID FIRST SURFACE BEING SELECTIVELY TRANSLATABLE FORE AND AFT LONGITUDINALLY OF SAID INLET SYSTEM; A FORWARD FLOATING SURFACE GENERATING AT LEAST ONE SECONDARY OBLIQUE SHOCK WAVE EXTERNALLY OF THE INLET, THE ANGLE OF SAID FORWARD FLOATING SURFACE WITH RESPECT TO SAID AXIS BEING DETERMINED AS A FUNCTION OF THE LONGITUDINAL POSITION OF SAID FIRST ANGLED SURFACE; A SEGMENTED, VARIABLE ANGLE RAMP PROVIDING INTERNAL COMPRESSION IN SAID INLET, SAID RAMP INCLUDING A FORWARD PORTION PIVOTALLY CONNECTED TO SAID FLOATING SURFACE AND VARIABLE IN ANGLE WITH RESPECT TO SAID AXIS AND SAID FLOATING SURFACE, SAID RAMP PORTION ADJUSTING TO ANGLE CHANGES OF SAID FLOATING SURFACE WHEREBY SAID CONTRACTION RATIO IS SUBSTANTIALLY UNAFFECTED DURING TRANSLATION OF SAID FIRST ANGLED SURFACE TO VARY THE OBLIQUE SHOCK MASS FLOW SPILLAGE RATE SO AS TO DECREASE AERODYNAMIC DRAG, THE ANGLE OF SAID FORWARD FLOATING SURFACE AUTOMATICALLY DECREASING AT HIGH MASS FLOW SPILLAGE RATES AND AUTOMATICALLY INCREASING AT LOW MASS FLOW SPILLAGE RATES SO AS TO IMPROVE OVERALL INLET PRESSURE RECOVERY.