Investigation of LF combustion instability is conducted where mechanism of instability is lag of burning-rate response to pressure disturbances near propellant surface due to temperature gradient just below surface and its interaction with lag in exhausting chamber due to nozzle flow; burning-rate and pressure perturbations are related through closed-loop feedback system analysis; expressions are derived for 2 transfer functions, and instability criterion is developed by application of Cauchy's theorem, resulting in correlation of critical pressure for given propellant and chamber characteristic length.
Theory of low-frequency combustion instability in solid rocket motors
AIAA J
AIAA Journal ; 2 , n 4
1964
7 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Combustion Instability in Solid Rocket Motors
NTIS | 1989
|High-Frequency Instability of Combustion in Solid Rocket Motors
Online Contents | 1995
|Combustion instability in solid propellant rocket motors
Engineering Index Backfile | 1958
|