PASSIVE VARIABLE THERMAL RESISTANCE TECHNIQUES

SOME MISSILE INERTIAL GUIDANCE SYSTEMS USE THE MISSILE STRUCTURE AS A HEAT SINK. THE HEAT SINK TEMPERATURE CHANGES DURING THE ELAPSED TIME BETWEEN LAUNCH AND WHEN THE MISSILE BECOMES BALLISTIC. THIS CHANGE IN TEMPERATURE RESULTS IN A CHANGE IN GUIDANCE SYSTEM TEMPERATURE WHICH IN TURN CAUSES TEMPERATURE INDUCED MISALIGNMENTS AND RESULTING NAVIGATION SYSTEM ERRORS. THIS PROPOSAL DESCRIBES A PROGRAM TO DEVELOP A PASSIVE VARIABLE THERMAL RESISTANCE SUITABLE FOR MISSILE INERTIAL GUIDANCE SYSTEMS. THE INTENT IS TO DECREASE THERMAL RESISTANCE AS THE HEAT SINK TEMPERATURE INCREASES THERBY MAINTAINING NEARLY CONSTANT GUIDANCE SYSTEM TEMPERATURES. THE PROPOSED WORK PROGRAM IS BASED ON USING GAS CONTROLLED HEAT PIPE TECHNOLOGY. IT COVERS DEFINITION OF REQUIREMENTS THRU ANALYSES, FABRICATION AND TEST OF PROOF-OF-PRINCIPLE HARDWARE.