Gas generator for guided missiles

Claim 1

A COMPACT GAS GENERATOR COMPRISING A GENERALLY SIMILAR FIRST AND SECOND DISCONTINUOUS AND SEPARATE SOLID PROPELLANT FOR POWERING A TURBINE AND THE LIKE IN A MISSILE SYSTEM WHEREIN THE PROPELLANTS ARE INCLOSED IN A CASING HAVING AN UPPER END AND A LOWER END, A FIRST IGNITER AT SAID UPPER END FOR INITIAL IGNITION OF THE FIRST PROPELLANT, SAID PROPELLANTS BEING IN ADJACENT PARALLEL RELATION TO EACH OTHER AND HAVING COPLANAR ENDS, THERMAL INSULATION BETWEEN SAID PROPELLANTS, A SECOND IGNITER ADJACENT A LOWERMOST PORTION OF SAID INSULATION AND CONTACTING EACH OF SAID PROPELLANTS, A CROSSOVER MEMBER AT THE LOWER END OF SAID CASING IN CONTACT WITH SAID SECOND IGNITER AND PROPELLANTS, SAID SECOND PROPELLANT HAVING A PLURALITY OF SPACED BORES IN ITS END ADJACENT THE CROSSOVER MEMBER, SAID CROSSOVER MEMBER BEING DEVOID OF ANY PROPELLANT THEREIN AND CONTAINING A SERIES OF PASSAGEWAYS SOLELY FOR PASSAGE OF HOT GASES THERETHROUGH, SAID PASSAGEWAYS COMMUNICATING BETWEEN SAID SECOND IGNITER AND PROPELLANTS AND MEANS ADJACENT SAID FIRST IGNITER FOR EXITING A CONSTANT FLOW OF GASES UPON THE SEPARATE AND SEQUENTIAL BURNING OF THE PROPELLANTS.