A Recommended Lunar Exploration Architecture

Paper number

IAC-06-D3.3.02

Author

Mr. William Kosmann, Orbital Sciences Corporation, United States

Year

2006

Abstract

From 2004 September 1 until 2005 August 31, Orbital Sciences conducted a NASA-funded Concept Exploration and Refinement (CER) study, designed to make recommendations to NASA on how to return men (and women) to the Moon, then onto Mars.  This paper presents the major results of that study.

The first major decision made was to base the launch vehicle on the current Space Transportation System (STS) Solid Rocket Booster (SRB), Space Shuttle Main Engine (SSME) and External Tank (ET).  The payload, cargo or human, was located on the top of the booster.  The heaviest payload (a fully loaded Cargo Lunar Lander) to be delivered to the Lunar vicinity drives the design of the entire transportation system.  This case drove the design of the Shuttle Derived Heavy Lift Launch Vehicle (SDHLLV), the Space Exploration Module (SEM) In-Space propulsion system, and the Lunar Lander.  An all chemical Lunar Transportation system was designed. The SD HLLV used 2 five segment SRBs, and 4 SSMEs using Hydrogen and Oxygen as propellents.  The SEM used three MB60 LOX/Hydrogen rocket engines.  The Lunar Landers used four new RD160 LOX/Methane rocket engines.  This optimized transportation system could deliver 140 MT to Low Earth Orbit (100 n.mi. altitude, 28.5 degree inclination), 85,000 lbm. of payload to Low Lunar Orbit, and 35,000 lbm. of payload to the Lunar Surface.

The above Lunar Transportation architecture requires 2 launches: the first launch places the HLL in Low Lunar Orbit (LLO), and the second launch places the CEV in LLO.  The architecture can be used either to assemble the pieces in Low Earth Orbit (LEO), or in LLO.  A mild preference was expressed for an LLO based architecture.

Use of such a Lunar Transportation system can only be determined once the fundamental objective of the Lunar Surface Activity is determined.  It was recommended to NASA that the fundamental objective of the Lunar Surface Activity should be to construct and operate a Lunar Base with Permanently Manned Capability (PMC).  A time ordered functionality analysis was completed, to determine what functionality was needed, and in what order, to construct and operate the Lunar Base.  Each functionality was translated into design requirements.  For each functionality, a design was created, complete with mass and volume estimates.  The collection of such designs, along with needed propellents, human consumables and base spares for base operation were manifested onto a series of SDHLLV launches, starting in 2015 continuing through 2025.

Abstract document

IAC-06-D3.3.02.pdf

Manuscript document

IAC-06-D3.3.02.pdf (🔒 authorized access only).

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