Analytical predictions are presented for effect of mass discharge rate from single- or multiple-pellet-mode pyrotechnic igniter elements, operating individually, or in Pyrogen igniters, on chamber pressure transients in inert chambers and during ignition phase of rocket motors; predictions show good agreement with experimental data; it is found that motor ignition spikes are primarily produced by erosive burning and igniter mass discharge rate, neglecting effect of variations in flame temperature during ignition; size and type of igniter necessary to avoid excessive ignition spikes in motor can be determined.
Igniter performance in solid-propellant rocket motors
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 4 , n 8
1967
6 pages
Article (Journal)
English
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Igniter performance in solid-propellant rocket motors.
AIAA | 1967
|Igniter performance in solid propellant rocket motors
AIAA | 1966
|Solid-Propellant Rocket Motors
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