Integrated aircraft engines

Claim 1

A CRUISING-LANDING ENGINE SYSTEM FOR A HYPERSONIC AIRCRAFT, COMPRISING: (A) A DETONATION COMBUSTION CRUISING ENGINE INCLUDING AN AEROTHERMODYNAMIC DUCT HAVING AN AIR INLET AT ONE END, AN EXHAUST NOZZLE AT THE OTHER END, A COMBUSTION ZONE INTERMEDIATE SAID INLET AND NOZZLE, A FUEL INJECTION NOZZLE IN THE DUCT UPSTREAM OF SAID COMBUSTION ZONE, AND A COMBUSTION CONTROL RAMP IN SAID COMBUSTION ZONE, SAID RAMP BEING MOVABLE BETWEEN OPEN AND CLOSED POSITIONS; (B) LANDING ENGINE MEANS ARRANGED IN PARALLEL WITH SAID COMBUSTION ZONE OF SAID CRUISING ENGINE INCLUDING AN AIR INLET DUCT BRANCHING OFF FROM SAID AETOTHERMODYNAMIC DUCT IMMEDIATELY UPSTREAM OF SAID COMBUSTION ZONE BETWEEN THE ZONE AND SAID FUEL INJECTION NOZZLE AND HAVING AN AIR INLET PASSAGE COMMUNICATING WITH SAID AEROTHERMODYNAMIC DUCT THROUGH A FIRST WALL OPENING THEREIN, AN EXHAUST DUCT BRANCHING OFF FROM SAID EXHAUST NOZZLE IMMEDIATELY DOWNSTREAM OF SAID COMBUSTION ZONE BETWEEN THE ZONE AND THE REAR OPEN END OF THE EXHAUST NOZZLE AND HAVING AN EXHAUST PASSAGE COMMUNIATING TO THE INTERIOR OF SAID EXHAUST NOZLE THROUGH A SECOND WALL OPENING IN SAID AEROTHERMODYNAMIC DUCT, AND A JET THRUST LANDING ENGINE MOUNTED BETWEEN SAID INLET AND EXHAUST DUCTS WITH ITS INLET IN COMMUNICATION WITH THE INLET PASSAGE IN SAID INLET DUCT AND ITS EXHAUST IN COMMUNICATION WITH THE EXHAUST PASSAGE IN SAID EXHAUST DUCT; (C) MEANS FOR SELECTIVELY ADMITTING THE AIR FLOWING THROUGH SAID AEROTHERMODYNAMIC DUCT TOWARD SAID COMBUSTION ZONE THEREOF INTO SAID INLET DUCT; AND (D) MEANS FOR SELECTIVELY OPENING AND CLOSING SAID EXHAUST DUCT.