Ablatively cooled rocket with non-eroding throat

Claim 1

AN ABLATIVELY COOLED ROCKET MOTOR COMPRISING AN OPEN ENDED ABLATIVE BODY CONVERGING TOWARD ONE END AND DEFINING A COMBUSTION CHAMBER, A HEAD SPANNING AND CLOSING THE CONVERGENT END OF THE BODY, MEANS CARRIED BY SAID HEAD FOR INJECTING FUEL AND OXIDIZER THROUGH THE HEAD FOR BURNING IN THE COMBUSTION CHAMBER, A TUBULAR NOZZLE AT THE OPPOSITE OPEN END OF THE BODY CONVERGING TO A REDUCED DIAMETER THROAT BEYOND THE BODY AND THEN DIVERGING FROM THE THROAT TO DEFINE AN OUTWARDLY FLARING EXIT PORTION, SAID TUBULAR NOZZLE HAVING A UNIFORM THICKNESS THROUGHOUT ITS LENGTH TO MINIMIZE THERMAL SHOCK AND BEING COMPOSED OF A HIGH TEMPERATURE SUBSTANTIALLY EROSION RESISTANT METAL ALLOY, AN INSULATING COVER SURROUNDING SAID TUBULAR NOZZLE MINIMIZING HEAT CONDUCTION THERETHROUGH, AND A MULTI-PIECE HOUSING INCLUDING A FIRST PORTION ENVELOPING SAID COVER AND A SECOND PORTION ENVELOPING A PART OF THE FIRST PORTION AND SURROUNDING SAID BODY AND HEAD.