Abstract: A rocket assisted projectile is equipped with a bi-metallic disk which ches shape to compensate for propellant grain growth or shrinkage with change in ambient temperature for maintaining the propellant in a predetermined position within the combustion chamber of the rocket. The disk is located in the combustion chamber forward of the propellant grain and bears against the chamber forward wall and the forward end of the grain. The effective thickness of the disk increases with reduced temperature so that the grain is maintained in solid contact with the base of the projectile to prevent excessive energy absorption upon firing of the projectile.

Abstract: Slurried rocket propellants and a spinning rocket motor wherein the propents have viscosities which enable them to form central cores when spun in spinning rocket motors, the motor having a diaphragm-like base plate which assists in transferring forward momentum through the propellant.