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Scientific paper
Sep 1992
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992lbsa.conf..119s&link_type=abstract
In its The Second Conference on Lunar Bases and Space Activities of the 21st Century, Volume 1 p 119-131 (SEE N93-17414 05-91)
Other
Lunar Landing Modules, Space Transportation, Spacecraft Design, Spacecraft Propulsion, Hydrogen Oxygen Engines, Maintenance, Orbit Insertion, Orbit Transfer Vehicles, Parking Orbits, Payload Mass Ratio, Propellants, Spacecraft Control, Translunar Injection
Scientific paper
This paper is a first look at the problems of building a lunar lander to support a small lunar surface base. A series of trade studies was performed to define the lander. The initial trades concerned choosing number of stages, payload mass, parking orbit altitude, and propellant type. Other important trades and issues included plane change capability, propellant loading and maintenance location, and reusability considerations. Given a rough baseline, the systems were then reviewed. A conceptual design was then produced. The process was carried through only one iteration. Many more iterations are needed. A transportation system using reusable, aerobraked orbital transfer vehicles (OTV's) is assumed. These OTV's are assumed to be based and maintained at a low Earth orbit (LEO) space station, optimized for transportation functions. Single- and two-stage OTV stacks are considered. The OTV's make the translunar injection (TLI), lunar orbit insertion (LOI), and trans-Earth injection (TEI) burns, as well as midcourse and perigee raise maneuvers.
Adorjan A. S.
Chambers T. V.
DOnofrio M.
Hirasaki J. K.
Morris O. G.
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