Solid Rocket Motors are extensively used in the aerospace and defence industry to deliver large thrust in a short duration. This study aims to analyze the methods & mechanisms for better control of solid rocket motor and the propellant extinction. Critical depressurization rates for extinction of non-Aluminized propellant is taken as the first point in the study.
Initially, the major advantages associated with the thrust termination of solid rocket motor are explored. Preliminary studies revealed an advantage in terms of overall weight saving and flexibility in the mission operation. A laboratory-scale experimental setup for determining the critical depressurization rates is developed. The experimental setup is designed with features to test propellants at different depressurisation rates and final conditions.Experimental results are compared to the results published in the past.
Control applications such as Divert and attitude control are presently limited to Liquid rocket system, use and applicability of solid rocket for such applications are attempted to be developed. Mini thrusters development and the problems associated with the design of such mini thrusters are deliberated.