Solid Propellant Rocket Motor Thermal Analysis

This paper discusses how analog and digital computers are used to finalize solid propellant rocket motor thermal design calculations, with emphasis on the effect of propellant-liner incremental thickness lumped with the motor case, and how it is selected. The effect of neglecting the motor case heat storage on final temperature distribution is indicated for both ground and flight analyses. The negligible effect of heating from propellant burning as opposed to aerodynamic heating is also shown. Finally, the results of comparative checks between analog, digital, and exact solutions are discussed. Present exact solutions are limited and can only be considered as rough approximations during long ground standby times.