Propellent charge for solid fuel rockets

Claim 1

A SOLID FUEL ROCKET COMPRISING AN ELONGATED CONTAINER ENCLOSED AT ONE END, A COMBUSTION CHAMBER, A NOZZLE CONNECTED TO THE OPEN END OF SAID CONTAINER AND COMMUNICATING WITH SAID COMBUSTION CHAMBER, A MAIN SOLID FUEL CHARGE DISPOSED WITHIN SAID COMBUSTION CHAMBER AND HAVING A BURNING RATE DEPENDENT UPON VARIATIONS IN EXTERNAL AMBIENT TEMPERATURE ASSUMED BY THE UNBURNT FUEL AND UPON VARIATIONS IN COMBUSTION CHAMBER PRESSURE, SAID MAIN FUEL CHARGE PRODUCING AN PREDETERMINED PROPULSION MOMENTUM AT A REFERENCE AMBIENT TEMPERATURE AND A REFERENCE COMBUSTION CHAMBER PRESSURE AND LOWER PROPULSION MOMENTUM AT LOWER AMBIENT TEMPERATURES AND COMBUSTION CHAMBER PRESSURES, MEANS FOR IGNITING SAID MAIN FUEL CHARGE, AT LEAST ONE AUXILIARY SOLID FUEL CHARGE DISPOSED WITHIN SAID COMBUSTION CHAMBER AND ISOLATED FROM SAID MAIN FUEL CHARGE, MEANS FOR IGNITING SAID AUXILIARY FUEL CHARGE INDEPENDENTLY OF SAID FIRST MENTIONED IGNITING MEANS, AND SWITCHING MEANS FOR SAID SECOND MENTIONED IGNITING MEANS RESPONSIVE TO AT LEAST ONE OF SAID VARIATIONS WHEN THE VARIATION WOULD CAUSE THE PROPULSION MOMENTUM GENERATED BY SAID MAIN FUEL CHARGE TO BE LOWER THAN SAID PREDETERMINED PROPULSION MOMENTUM, SAID SWITCHING MEANS INCLUDING A BIMETALLIC ELEMENT CONTROLLED BY SAID EXTERNAL AMBIENT TEMPERATURE, UPON IGNITION SAID AUXILIARY FUEL CHARGE BEING CAPABLE OF GENERATING AT LEAST DURING A SUBSTANTIAL PART OF THE BURNING TIME OF SAID MAIN FUEL CHARGE AN AUXILIARY PROPULSION MOMENTUM WHEREBY THE COMBINED AUXILIARY PROPULSION MOMENTUM AND LOWER MAIN PROPULSION MOMEMTUM ARE SUBSTANTIALLY EQUAL TO SAID PREDETERMINED PROPULSION MOMENTUM.