posted on Dec, 14 2007 @ 01:40 AM
Here are some Highlights:
MODEL USERS, FEATURES, DESCRIPTIONS, COMPUTER IMPLEMENTATION AND MANAGEMENT
The following section describes
( A ) the potential user community of the proposed modeling system,
(B) the user interface and model features as seen by the various sections of that community, (C) model descriptions,
(D)system implementation, and (E) model management.
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Inputs. System objectives must ultimately be expressed in specific numerical terms, e.g., as tons of Lunar LOX to be delivered to LEO per year. These
may be input directly by the user, or may be derived from various "markets" which the system is serving, e.g., LEO servicing, LEO space station,
SDI, Mars Missions, etc. System configuration or structure is a complete specification of what system elements are included in a particular study and
the type of each element. System elements include the surface infrastructure, Earth launch systems, lunar launch systems, and OTV systems.
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Outputs. System operation variables include power consumption,
LLOX production, person and cargo trips/year of various vehicle types, etc. System performance variables are either a subset of system operation
variables or are easily derived from them. An example is metric tons of lunar oxygen delivered to LEO, mass payback ratios, etc. Costs include
transport costs, system lifetime cost, emplacement costs, etc.
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SECTION IV: PLAN FOR FUTURE ACTION
A. Implementing the Modeling Process Building on the results of the Workshop on Lunar Base Methodology Development, a Lunar Base Modeling Working
Group is to be formed to focus technical and strategic or programmatic models toward an overall planning model for Lunar Base development. This
working group will assess the feasibility of modeling that will allow integrated lunar base planning and strategic analyses. Models should incorporate
technical and programmatic (cost and schedule) modules that describe the parameters and interrelationships among transportation, base habitat,
science, manufacturing, power, etc. Sensitivities to technology levels and definition uncertainties can be determined and the results can provide a
focus for future studies planning and technology investment strategies.
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The purpose of this section of the report is to identify, within
the limitations of the talent and time available:
( 1 ) The elements and sub-elements of a lunar base program;
most frequently an identifiable, discrete hardware end-item.
( 2 ) The quantifiable requirements for each sub-element which
must be specified to the designer of each sub-element before beginning the concept selection and design process. Examples of such requirements are
payload , range, reliability and life.
( 3 ) The attributes of the element or sub-element which
provide both a physical description of the end-item and the needs
which must be supplied from outside the element in order for it to fulfill its function and meet its requirements. Examples would be the mass, volume,
unit cost, and fuel consumption rate of an internal combustion engine. The fuel consumption attribute of the engine, once defined, would become a part
of the requirements for the fuel supply and distribution element.
( 4 ) The transform relationships which may be used in the
modeling process for deriving first order estimates of new attribute values in response to new requirement values. An example of an attribute is the
specific mass of a storage battery, expressed in the units of Kg/Watt Hour.
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The essence of the completed lunar base model will be the
mathematical relationships linking the "requirements" to the
"attributes" of the lunar base "elements" which are required to
achieve a specified set of goals. Eleven candidate lunar base
elements were defined early in the workshop to provide a starting
point for development of such relationships. Regrouping and
redefinition of these elements will be a natural outcome of further effort on the lunar base model development project.
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Initially, a normalization of the level-of-detail of the sub-element descriptions, requirements and attributes will be necessary.
Completion of the definition of the transform algorithms will also be necessary. Much of the data on nominal estimated transform algorithms will be
missing and little or no data on the necessary minimum and maximum expected values will be present.
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MODEL GROWTH AND EXPANSION
Initial models will attempt only to provide a "snapshot" of the
lunar base at it will exist at a single moment of its life cycle.
The real lunar base will, of course, require multi-year activities to establish first a transient fasthold, then a facility which can support life
over an extended interval and, eventually a human community which approaches self-sufficiency and produces goods and services for export.
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POWER SYSTEM ALTERNATIVES MODELING
LUNAR BASE SUPPORTING ELEMENTS
The power system alternatives considered for application to these
1. Solar Photovoltaic Power Systems with Regenerative Fuel Cells
2. Solar Thermal Dynamic Power Systems (cycle unspecified).
3. Nuclear Reactor Power (Energy Conversion System TBD).
4. Isotope Power Systems - Dynamic and Passive.
5 . Regenerative fuel cells for Lunar Surface Transportation.
6 . Batteries Fuel Cells for Launch Vehicle and Lunar Transit
7 . Isotope Power for Recoverable Earth-to-LEO Launch Vehicles.
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EXAMPLE ESTIMATE OF LUNAR OXYGEN PRODUCTION PLANT MASS
ELECTROLYSIS OF MOLTEN SLAG: A crude mass estimate for a plant to
electrolyze molten slags derived from lunar minerals can be made as follows :
Oxygen production via slag electrolysis proceeds as follows.
Regolith is mined, and a specific feedstock (e.g., ilmenite) is
concentrated by beneficiation. The feed material (minus tailings) is slowly introduced into the electrolysis cell where it dissolves in the liquid
slag. The slag flows through the electrolysis cell and is discharged after sufficient amount of electrolysis. The Ferrotitanium product is also
discharged periodically. Hot oxygen is cooled and sent to a liquefier for condensation and storage.