Near-optimal operation of dual-fuel launch vehicles
- Santa Clara Univ., CA (United States)
- NASA Ames Research Center, Moffett Field, CA (United States)
Current studies of single-stage-to-orbit (SSTO) launch vehicles are focused on all-rocket propulsion systems. One option for such vehicles is the use of dual-fuel (liquid hydrocarbon and liquid hydrogen (LH{sub 2})), for a portion of the mission. As compared with LH{sub 2}, hydrocarbon fuel has higher density and produces higher thrust-to-weight, but has lower specific impulse. The advantages of hydrocarbon fuel are important early in the ascent trajectory, and its use may be expected to lead to reduced vehicle size and weight. Because LH{sub 2} is also needed for cooling purposes, in the early portion of the trajectory both fuels must be burned simultaneously. Later in the ascent, when vehicle weight is lower, specific impulse is the key parameter, indicating single-fuel LH{sub 2} use.
- OSTI ID:
- 481973
- Report Number(s):
- CONF-960503--; CNN: Grant NCC 2-5069
- Country of Publication:
- United States
- Language:
- English
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