Design of fast earth-return trajectories from a lunar base

Details Design of fast earth-return trajectories from a lunar base Design of fast earth-return trajectories from a lunar base

Sep 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991nps..reptt....a&link_type=abstract

M.S. Thesis Naval Postgraduate School, Monterey, CA.

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Applications

Energy Requirements, Flight Time, Hyperbolic Trajectories, Lunar Bases, Parking Orbits, Trajectories, Ascent Trajectories, Computer Programs, Nuclear Weapons, Space Weapons, Three Dimensional Models

Scientific paper

The Apollo Lunar Program utilized efficient transearth trajectories which employed parking orbits in order to minimize energy requirements. This thesis concentrates on a different type of transearth trajectory. These are direct-ascent, hyperbolic trajectories which omit the parking orbits in order to achieve short flight times to and from a future lunar base. The object of the thesis is the development of a three-dimensional transearth trajectory model and associated computer program for exploring trade-offs between flight-time and energy, given various mission constraints. The program also targets the Moon with a hyperbolic trajectory, which can be used for targeting Earth impact points. The first-order model is based on an Earth-centered conic and a massless spherical Moon, using MathCAD version 3.0. This model is intended as the basis for future patched-conic formulations for the design of fast Earth-return trajectories. Applications include placing nuclear deterrent arsenals on the Moon, various space support related activities, and finally protection against Earth-threatening asteroids and comets using lunar bases.

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