
Mitigation of irregular burning in a small solid propellant rocket motor
Author(s) -
M. Elkshen,
Hatem M. Belal,
M. A. Al-Sanabawy
Publication year - 2020
Publication title -
iop conference series. materials science and engineering
Language(s) - English
Resource type - Journals
eISSN - 1757-899X
pISSN - 1757-8981
DOI - 10.1088/1757-899x/973/1/012002
Subject(s) - propellant , baffle , signal (programming language) , materials science , combustion , solid fuel , acoustics , rocket (weapon) , thrust , solid fuel rocket , mechanics , deflagration , aerospace engineering , detonation , physics , mechanical engineering , chemistry , engineering , computer science , explosive material , organic chemistry , programming language
An irregular burning phenomenon arises in some solid propellant motors(SRM), where the time-averaged pressure differs largely from that dedicated by instantaneous area burning. This phenomenon is generally considered the result of the interaction of pressure disturbances within the motor cavity with solid propellant deflagration. Hence, it is a combustion-dependent acoustic phenomenon. Historically, different suppression devices included the classical resonance rods and paddles, and arrays of acoustic resonators and various baffle arrangements were applied. In this paper, irregular burning which arises in a modification of a shoulder-launched rocket is investigated. Several techniques dealing with the irregular burning problem were attempted. In each case, the signal of pressure was analysed in the time domain through time average and AC pressure signal, and in the frequency domain through Fourier transform and power spectral density. The most successful technique was the drilling of holes through the grain, connecting the perforation to the external burning region of the cylinder. Next was the increasing of blocking factor, both methods lead to stabilizing the modified motor.