Design issues for lunar ascent and lunar descent rocket engines fueled by aluminum/oxygen propellant produced in situ at the lunar surface were evaluated. Key issues are discussed which impact the design of these rockets: aluminum combustion, throat erosion, and thrust chamber cooling. Four engine concepts are presented, and the impact of combustion performance, throat erosion and thrust chamber cooling on overall engine design are discussed. The advantages and disadvantages of each engine concept are presented.
Design issues for lunar in situ aluminum/oxygen propellant rocket engines
1992-02-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Design of a LOX/Aluminum Lunar Propellant Rocket Engine
British Library Conference Proceedings | 1994
|Solid-Propellant Rocket Engines
NTIS | 1974
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