Investigation of the feasibility of FLOX for performance improvement on the S-IC
Feasibility of using liquid fluorine and oxygen /FLOX/ as oxidizer to improve performance of Saturn S-IC stage
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Feasibility of using liquid fluorine and oxygen /FLOX/ as oxidizer to improve performance of Saturn S-IC stage
Bibliography of fluorine and flox oxidizers for spacecraft propulsion systems
An analysis was completed for determination of the most promising hydrocarbon fuels for use with flox in upper stage rocket engines. Experimental rocket firings in uncooled, transpiration cooled, and regeneratively cooled thrust chambers were conducted using flox with methane, propane, butene-1, and a eutectic blend of pentane and isopentane. Experimental heated tube heat transfer and hypergolicity tests were conducted, and laboratory determinations of physical properties of various blends of hydrocarbon compounds were made.
Flox-light hydrocarbon combinations desirable as liquid rocket propellants due to high specific impulse, hypergolicity and cooling properties
Fluorine propulsion technology discussed with regard to performance, system design criteria, handling and launch procedures
Reaction characteristics of fluorine and fluorine- oxygen mixture spills on rocket test or launch facility materials
Oxidizer tank helium pressure regulator compatible with fluorine-liquid oxygen
Fluorine-liquid oxygen disconnect for Atlas launch vehicle oxidizer system
Protecting fluorine-liquid oxygen Atlas launch vehicle oxidizer tank against overpressurization
Atmospheric diffusion of fluorine from spills of fluorine-oxygen mixtures
Static and dynamic reactivity of fluorine and fluorine-oxygen mixtures with polymer materials
Fluorine-liquid oxygen mixture and injector design effects on JP-4 jet fuel performance in rocket engines
Meteorological considerations in handling liquid fluorine and liquid oxygen mixture
Increased performance of rocket engine using fluorine-oxygen mixture with RP-1 fuel
Flox-light hydrocarbon combinations desirable as liquid rocket propellants due to high specific impulse, hypergolicity and cooling properties
Exposure and tolerance limits for fluorine rocket propellants
Ignition of hydrogen fluorinated oxidizers