Effects of Additives on Ignition Delay and Chamber Pressurization of Space-Ambient Engines.
Technical summary rept. 15 Feb-15 Sep 68,
THIOKOL CHEMICAL CORP DENVILLE NJ REACTION MOTORS DIV
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The program objective is to evaluate the effects of the addition of NO, CH3CN and H2O on the ignition delay and pre-ignition chamber pressurization of space-ambient engines operating with N2O4MMH and N2O450-50 N2H4-UDMH. The evaluation is being made within the framework of a computer model of hypergolic ignition developed previously for the neat N2O4MMH propellant system. During the first seven months of the present program, the model has been reviewed in detail and refinements have been incorporated. Model inputs required for considerations of other propellant combinations have been identified and experimental work has been performed to determine the necessary inputs for the subject propellant combinations with additives. Kinetic factors for ignition have been determined for five propellant systems and several property determinations and chemical analyses have been performed on the condensed-phase reaction intermediates formed by ten propellant mixtures. No pronounced effect of any of the additives has been observed to date but differences between the MMH and 50-50 derived intermediates are marked. The latter are more nearly balanced stoichiometrically, appear to detonate rather than explode, and are more sensitive to impact than the MMH-derived intermediates. Further analyses and determinations are planned and engine testing with the various propellant systems will be performed at simulated altitudes. Author
- Liquid Propellant Rocket Engines