HYPERGOLIC IGNITION AT REDUCED PRESSURES. PART 2

A mathematical model of hypergolic ignition in reaction control systems was developed based on physical kinetics of droplet evaporation and chemical kinetics of ignition reactions. Reasonable agreement between theoretical and experimental ignition delays were obtained. The dominant ignition reaction...

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Bibliographische Detailangaben
Hauptverfasser:	Corbett, Albert D, Dawson, Bruce E, Seamans, Thomas F, Vanpee, Marcel M
Format:	Report
Sprache:	eng
Schlagworte:	ALCOHOLS CHLORINE COMPOUNDS CHLORINE PENTAFLUORIDE CHLORINE TRIFLUORIDE COMBUSTION CHAMBERS CONDENSATION FLUID FLOW FLUORIDES FUEL ADDITIVES FUEL INJECTION FUEL INJECTORS FURANS HYDRAZINE DERIVATIVES HYDRAZINES HYPERGOLIC IGNITION HYPERGOLIC ROCKET PROPELLANTS IGNITION LAG Liquid Propellant Rocket Engines LIQUID ROCKET FUELS LIQUID ROCKET OXIDIZERS Liquid Rocket Propellants MATHEMATICAL MODELS METHYL HYDRAZINES MHF-5 MMH NITROGEN COMPOUNDS NITROGEN OXIDE(N2O4) NITROGEN OXIDE(NO2) REACTION KINETICS ROCKET NOZZLES SPACE PROPULSION TETROXIDES VAPORS
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Zusammenfassung:	A mathematical model of hypergolic ignition in reaction control systems was developed based on physical kinetics of droplet evaporation and chemical kinetics of ignition reactions. Reasonable agreement between theoretical and experimental ignition delays were obtained. The dominant ignition reactions of N2O4 with the hydrazine fuels at reduced pressures were found to be thermal, gas phase reactions which are bimolecular with low activation energies and pre-exponential factors. A pre-ignition reaction product was found which is a clear, yellow, viscous liquid with a very low vapor pressure. The 'adduct' has the characteristics of a monopropellant. Of six additives tested, only furfuryl alcohol had a significant beneficial effect on the ignition characteristics of N2O4/MMH. The influence of thrust chamber design parameters on the ignition delay and pressure transients of Compound A with N2H4, UDMH and MHF-5 and also gaseous F2/H2 was investigated. See also Part 1, AD364162.