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NASA NTRS · 20170001563

Propulsion Estimates for High Energy Lunar Missions Using Future Propellants

Palaszewski, Bryan A.·Bennett, Gary L.
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Abstract

High energy propellants for human lunar missions are analyzed, focusing on very advanced ozone and atomic hydrogen. One of the most advanced launch vehicle propulsion systems, such as the Space Shuttle Main Engine (SSME), used hydrogen and oxygen and had a delivered specific impulse of 453 seconds. In the early days of the space program, other propellants (or so called metapropellants) were suggested, including atomic hydrogen and liquid ozone. Theoretical and experimental studies of atomic hydrogen and ozone were conducted beginning in the late 1940s. This propellant research may have provided screenwriters with the idea of an atomic hydrogen-ozone rocket engine in the 1950 movie, Rocketship X-M. This paper presents analyses showing that an atomic hydrogen-ozone rocket engine could produce a specific impulse over a wide range of specific impulse values reaching as high as 1,600 s. A series of single stage and multistage rocket vehicle analyses were conducted to find the minimum specific impulse needed to conduct high energy round trip lunar missions.

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BibTeXRIS

Palaszewski, Bryan A., Bennett, Gary L.. 2016-07-25. Propulsion Estimates for High Energy Lunar Missions Using Future Propellants. https://ntrs.nasa.gov/citations/20170001563

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