When pulsing rocket engines are tested under altitude conditions, data show that probability of large ignition overpressures generally decreases as temperature of rocket engine increases; this trend suggests that large ignition overpressures are related to accumulations of energy-rich substances on internal surfaces of engine; analytical and experimental investigation of this hypothesis and of means for insuring smooth ignition of pulsing rocket engines are presented; results show that large ignition overpressures can be avoided if engine walls are kept warm enough to prevent residual materials from accumulating in combustion chamber during duty cycles being fired.
Ignition transients in small hypergolic rockets
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 5 , n 3
1968
5 pages
Article (Journal)
English
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Ignition transients in small hypergolic rockets.
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