Lunar Module Descent Mission Design
Author(s)
Wilhite, Alan W.
Tolson, Robert
Moen, Marina M.
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Abstract
Various lunar descent trajectories were analyzed that include the optimization of the
Apollo constrained mission trajectory, a fully optimized minimum energy trajectory, and a
optimal, constrained trajectory using current instrumentation technology. Trade studies
were conducted to determine the impacts of mission assumptions, pilot in the
loop/automated flight demands, and additional constraints for the present recurring
missions to the same outpost landing site. For mission design at this conceptual phase of the
program, the Apollo pre-mission planning was applied to account for known contingencies
(hardware, instrumentation known uncertainties) and unknown unknowns. The mission
Delta-V's are presented in a risk form of conservative, nominal, and optimistic range where
90 percent of Delta-V is derived by trajectory analysis and the other 10 percent was derived
from a qualitative analysis from Apollo 11 pre-mission planning. The recommendations for
the Delta Vs are the following: conservative (Apollo derived) (2262 m/s), nominal (2053
m/s), and optimistic (1799 m/s). Because of the qualitative nature of the results, the degree of
autonomy assumed, additional safety considerations for a lunar outpost, and the impact of
advanced instrumentation, more in-depth analyses are required to refine the present
recommendations.
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Date
2008-08
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Text
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Paper
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