To predict pressure-time and thrust-time behavior of solid rocket motors, a one-dimensional numerical model is developed. The ignition phase of solid rocket motors (time less than 0.4 sec) depends critically on complex interactions among many elements, such as rocket geometry, heat and mass transfer, flow development, and chemical reactions. The present model solves the mass, momentum, and energy equations governing the transfer processes in the rocket chamber as well as the attached converging-diverging nozzle. A qualitative agreement with the SRM test data in terms of head-end pressure gradient and the total thrust build-up is obtained. Numerical results show that the burning rate in the star-segmented head-end section and the erosive burning are two important parameters in the ignition transient of the solid rocket motor (SRM).
Ignition transient analysis of solid rocket motor
1990-10-01
Conference paper
No indication
English
Ignition Transient Analysis of Solid Rocket Motor
NTIS | 1990
|Ignition transient analysis of solid rocket motor
NTRS | 1991
|Modeling of Solid Rocket Motor Ignition Transient Revisited
British Library Conference Proceedings | 2002
|Solid Rocket Motor Ignition Transient Phenomenon and Pressure Buildup Simulation
British Library Conference Proceedings | 2007
|Fluid–solid coupled simulation of the ignition transient of solid rocket motor
Online Contents | 2015
|