Leroy stram

Claim 1

A HIGH ALTITUDE STARTING SYSTEM FOR A TURBOJET ENGINE AND COMPRISING (A) A HOUSING STRUCTURE, (B) A COMBUSTOR STRUCTURE DISPOSED WITHIN SAID HOUSING STRUCTURE AND DEFINING A COMBUSTION CHAMBER, (C) A FUEL SUPPLY MEANS DELIVERING A PRIMARY FUEL STREAM TO SAID COMBUSTION CHAMBER, (D) AIR INDUCTION MEANS DELIVERING AIR TO SAID COMBUSTION CHAMBER TO PROVIDE HIGH ENERGY FUEL, AND (E) A FLAME PRODUCER OPERABLE TO PROVIDE A HIGH ENERGY FLAME WITHIN SAID COMBUSTION CHAMBER FOR INITIATING COMBUSTION OF SAID PRIMARY FUEL, (F) SAID FLAME PRODUCER COMPRISING A PYROTECHNIC FLARE SUPPORTED WITHIN SAID COMBUSTION CHAMBER AND HAVING A CHARGE OF HIGH ENERGY SOLID ROCKET FUEL INCLUDING AN OXIDIZER AND MEANS IGNITING SAID ROCKET FUEL, (G) SAID FLARE COMPRISING A METAL SLEEVE SECURED TO SAID HOUSING STRUCTURE AND HAVING AN OPEN END DISPOSED ADJACENT SAID COMBUSTOR STRUCTURE AND EXTERIORLY OF SAID COMBUSTION CHAMBER, (H) SAID FLARE FURTHER COMPRISING A COMBUSTIBLE TUBE CARRYING SAID CHARGE OF ROCKET FUEL AND CARRIED WITHIN SAID SLEEVE AND EXTENDING FROM SAID OPEN END THROUGH SAID COMBUSTOR STRUCTURE AND INTO SAID COMBUSTION CHAMBER, WHEREBY SAID SLEEVE IS DISPOSED SUBSTANTIALLY ENTIRELY EXTERIORLY OF SAID COMBUSTION CHAMBER AND SAID COMBUSTIBLE TUBE IS DISPOSED SUBSTANTIALLY ENTIRELY INSIDE SAID COMBUSTION CHAMBER.