Temperature responsive rocket nozzle cooling system

Claim 1

A TEMPERATURE-RESPONSIVE COOLING SYSTEM FOR A ROCKET ENGINE NOZZLE COMPRISING: A POROUS LINER FOR SAID NOZZLE; A COOLANT CHAMBER SURROUNDING SAID BOZZLE LINER; A VALVE BODY PROVIDING A COOLANT PASSAGE INTO SAID COOLANT CHAMBER INCLUDING A COOLANT INLET, A COOLANT OUTLET, AND A VALVE SEAT THEREBETWEEN, SAID COOLANT OUTLET OPENING INTO SAID COOLANT CHAMBER; A VALVE BODY CAP THREADINGLY ATTACHED TO SAID VALVE BODY AND POSITIONED ADJACENT TO SAID NOZZLE LINER; A PIN MEANS HAVING ONE END THEREOF SEATED IN SAID VALVE SEAT TO RESTRICT THE FLOW OF COOLANT THROUGH SAID VALVE BODY; A BLOCK OF MELTABLE MATERIAL DISPOSED WITHIN SAID VALVE BODY CAP, SAID MELTABLE MATERIAL HOLDING SAID PIN MEANS IN ITS SEATED POSITION TO RESTRICT THE FLOW OF SAID COOLANT THROUGH SAID VALVE BODY, AND SAID MELTABLE MATERIAL MELTING WHEN THE VALVE BODY CAP REACHES A PREDETERMINED TEMPERATURE TO RELEASE SAID PIN MEANS FROM ITS SEATED POSITION THEREBY FACILITATING THE FLOW OF COOLANT THROUGH SAID VALVE BODY INTO SAID COOLING CHAMBER.