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
8 pages
Report
No indication
English
Rocket Engines & Motors , Manned Spacecraft , Burning rate , Energy transfer , Erosive burning , Heat transfer , Ignition , Mass transfer , Mathematical models , Space shuttle main engine , Chemical reactions , Convergent-divergent nozzles , Kinetic energy , Nasa programs , Pressure gradients , Thrust chambers , University program
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