Space Resources
roundtable vi
Colorado School of mines
November 1 -3, 2004
Program and Abstracts
LPI Contribution No. 1224
Space Resources Roundtable VI
November 1-3, 2004
Colorado School of Mines
Golden, Colorado
Sponsored by
Colorado School of Mines
Lunar and Planetary Institute
Space Resources Roundtable, Inc.
Steering Committee
Joe Burris, WorldTradeNetwork
R. Scott Baird, NASA Johnson Space Center
David Criswell, University of Houston
Michael B. Duke, Colorado School of Mines
Stephen Mackwell, Lunar and Planetary Institute
Clyde Parish, NASA Kennedy Space Center
Sanders Rosenberg, InSpace Propulsion, Inc.
Frank Schowengerdt, NASA Headquarters
G. Jeffrey Taylor, University ofHawai 'i
Lawrence Taylor, University of Tennessee
Lunar and Planetary Institute 3600 Bay Area Boulevard Houston TX 77058-1 1 13
LPI Contribution No. 1224
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Preface
This volume contains abstracts that have been accepted for presentation at the Space
Resources Roundtable VI, November 1-3, 2004, Colorado School of Mines, Golden,
Colorado.
Publications support for this meeting was provided by the staff of the Publications and
Program Services Department at the Lunar and Planetary Institute.
Space Resources Roundtable VI v
Contents
Program 1
Dielectric Constant Measurements on Lunar Soils and Terrestrial Minerals
R. C. Anderson, M. G. Buehler, S. Seshardri, andM. G. Schaap 7
Dust Mitigation of Astronaut Spacesuits
H. Angel, P. Thanh, and ML Nakagawa 8
Toward a Sustainable Mars Infrastructure
R.L.Ash 9
Granular Materials and Risks In ISRU
R. P. Behringer and R. A. Wilkinson 10
ISRU Technology Modeling and Analysis
B. R. Blair, J. Diaz, B. Ruiz, andM. B. Duke 11
Costs and Benefits of ISRU-Based Human Space Exploration
B. R. Blair, M. B. Duke, J. Diaz, andB. Ruiz 12
Report on the Construction and Testing of a Bucket Wheel Excavator
D. S. Boucher and J. Richard 13
The Lunar Polar Illumination Environment: What We Know & What We Don't
D. B. J. BusseyandP. D. Spudis 14
Lunar Simulants: JSC-1 is Gone; The Need for New Standardized Root Simulants
J. L. Carter, D. S. McKay, L. A. Taylor, and W. D. Carrier III 15
Space Transportation for a Lunar Resources Base (LRB)
H.P.Davis 16
Autonomous In-Situ Resources Prospector
R. W. Dissly, M.G. Buehler, M.G. Schaap, D. Nicks, G. J. Taylor,
R. Castano, and D. Suarez 17
Extraction of Oxygen from the Martian Atmosphere
C.England 18
Minimizing Launch Mass for ISRU Processes
C. England and K. P. Hallinan 19
Remote Sensing Assessment of Lunar Resources: We Know Where to Go to Find What We Need
J. J. Gillis, G. J. Taylor, and P. G. Lucey 20
Robotic Subsurface Analyzer and Sample Handler for Resource Reconnaissance and
Preliminary Site Assessment for ISRU Activities at the Lunar Cold Traps
S. P. Gorevan, J. Wilson, P. Bartlett, J. Powderly, D. Lawrence, R. Elphic,
G. Mungas, E. McCiillough, C. Stoker, H. Cannon, B. Glass, W. D. Carrier,
H. Schmitt, J. Johnson, D. Cole, C Dreyer, D. S. McKay, andR. V. Morris 21
vi LPI Contribution No. 1224
Economic Laws and the Lunar Imperative: Outline of Components for a Sustained
Development Strategy
K.P.Heiss 22
Granular Flow and In-Situ Resource Utilization
J. T. Jenkins, M. Y. Louge, andE. Rame 23
Power Lander for Support of Long-Term Lunar Presence
R. Joyner and G. Rodriguez 24
Near Earth Object Characterization, Exploration and Exploitation
K. Klaus 25
Mission Design for Economically Self-Supporting Large Scale Lunar Telepresence
G. A. Konesky 26
Tumbleweed: A New Paradigm for Surveying the Surface of Mars for In-Situ Resources
K. R. Kuhlman, A. E. Behar, J. A. Jones, F. Carsey, G. A. Hajos,
J. J. Flick, and J. Antol 27
Simulation of Helium-3 Extraction from Lunar Ilmenite
K. R. Kuhlman, G. L. Kulcinski, andH. H. Schmitt 28
Mars Deep Drilling Remains a High Priority
H.C.Mandell 29
SELENE Scientific Data Products and their Application to Characterization of Lunar
Potential Resources
K Matsui, R. Nakamuara, M. Kato, and Y. Takizawa 30
The Identification of Gas Hydrate Resources on Mars: Implications for Human Exploration
and Long-term Habitation
M. D.MaxandS. Clifford 31
Micro-Structured Heat Exchangers and Reactors for ISRU and Energy Conversion
A. McCandless, S. Motakef D. Guidry, and M. Overholt 32
Rocks to Robots: A Biological Growth Approach to Rapid Lunar Industrialization or
How to Realize Von Neumann's Vision
L. M. E. Morin 33
Solar Energy Utilization for In-Situ Resource Utilization
T. Nakamura 34
Lessons from Earth: Experiences Which can Guide Lunar and Asteroidal Development
CD. O'Dale 35
SILVER: Surface Imaging for Lunar Volatiles, Resources, and Exploration
R. T. Pappalardo, E. Cobabe-Ammann, A. C Cook, R. Greeley, V. C. Gulick,
W. E. McClintock, J. M. Moore, S. A. Stern, A. R. Vasavada,
M. McClelland, and J. West/all 36
Exploration of the Impact of ISRU on Architectural System Mass and Cost
C. M. Reynerson 37
Space Resources Roundtable VI vii
Lunar and Martian Fiberglass as a Versatile Family of ISRU Value-Added Products
G. Rodriguez 38
Telepossession Transforms Asteroids into Resources
G. Rodriguez 39
Power Lander for Support of Long-Term Lunar Presence
G. Rodriguez andR. Joyner 40
Intelligent Excavation for the Moon
A. Schissler and V. Kecojevic 41
Solar Wind Helium Concentrations in Undisturbed Lunar Regolith
H.H.Schmitt 42
Synthesis of Sol-Gel Precursors for Ceramics from Lunar and Martian Soil Simulars
L. Sibille, J. A. Gavira-Gallardo, andD. Hourlier-Bahloul 43
Drilling to Extract Liquid Water on Mars: Feasible and Worth the Investment
C. Stoker 44
The Uncertain Nature of Polar Lunar Regolith
G. J. Taylor, J. Neubert, P. Lucey, and E. McCullough 45
The Nature of Lunar Soil: Considerations for Simulants
L. A. Taylor, D. S. McKay, W. D. Carrier III, J. L. Carter, and P. Weiblen 46
Steel Production Utilizing Iron Extracted from Lunar Ores and Soils
R. Westfalland W. C. Jenkin 47
Space Law Update: Real Property Rights and Resource Appropriation
W.N. White 48
Concept for Landed Measurements of Mars that will Help Identify and Characterize
Potential Surface Resources
C. M. T. Woodworth-Lynas, J. Y. Guigne, D. Hart, andR. Davidson 49
Using Spent Fuel Tanks as Habitats
T. Wray and G. Rodriguez 50
The Application of Self-Propagating High Temperature (Combustion) Synthesis (SHS)
for In-Space Fabrication and Repair
X. Zhang, H. C Yi, J. Y. Guigne, A. Mannerbino, and J. J. Moore 51
Space Resources Roundtable VI 1
Program
Monday, November 1, 2004
INTRODUCTION
8:00 a.m. Continental Breakfast and Registration
8:30 a.m. Duke M. Director, Center for Commercial Applications of Combustion in Space
Welcome
8:45 a.m. Taylor G. J. Roundtable Program Chair
Objectives and Organization of the Meeting
9:00 a.m. Wegeng R.
The Moon, Mars, and Beyond: View from Headquarters
9:30 a.m. Sanders G. B.
Overview of ISRU Activities and Goals
10:00 a.m. BREAK
LUNAR POLAR DEPOSITS
Moderator: J. J. Gillis
10:15 a.m. Bussey D. B. J. Spudis P. D.
The Lunar Polar Illumination Environment: What We Know & What We Don 't [#6022]
10:45 a.m. Pappalardo R. T. Cobabe-Ammann E. Cook A. C. Greeley R.
GulickV. C. McClintock W.E. Moore J. M. Stern S. A. VasavadaA. R.
McClelland M. Westfall J.
SILVER: Surface Imaging for Lunar Volatiles, Resources, and Exploration [#6028]
11:00 a.m. Taylor G.J. NeubertJ. Lucey P. McCullough E.
The Uncertain Nature of Polar Lunar Regolith [#6040]
11:15 a.m. Gorevan S. P. Wilson J. BartlettP. PowderlyJ. Lawrence D. Elphic R.
MungasG. McCullough E. Stoker C. Cannon H. Glass B. Carrier W. D.
SchmittH. H. McKay D. S. Morris R. V. Johnson J. Cole D. DreyerC.
Robotic Subsurface Analyzer and Sample Handler for Resource Reconnaissance and
Preliminary Site Assessment for ISRU Activities at the Lunar Cold Traps [#6043]
LPI Contribution No. 1224
Monday, November 1, 2004 (continued)
11:30 a.m. Discussion: Exploration Strategy for Lunar Polar Deposits
12:00- 1:30 p.m. LUNCH in Green Center
Welcome by Dr. John Trefny, President of Colorado School of Mines
ISRU SIMULANTS FOR THE MOON AND MARS
Moderator: G. J. Taylor
1:30 p.m. Taylor L. A. McKay D. S. Carrier W. D. 111 Carter J. L. Weiblen P.
The Nature of Lunar Soil: Considerations for Simulants [#6024]
1 :45 p.m. Carter J. L. McKay D. S. Taylor L. A. Carrier W. D. Ill
Lunar Simulants: JSC-1 is Gone; The Need for New Standardized
Root Simulants [#6023]
2:00 p.m. Discussion: Simulants
EXPLORATION TECHNIQUES
Moderators: B. Bussey and L. A. Taylor
2:30 p.m. Matsui K. Nakamuara R. Kato M. Takizawa Y.
SELENE Scientific Data Products and their Application to Characterization of
Lunar Potential Resources [#6005]
2:45 p.m. Gillis J. J. Taylor G. J. Lucey P. G.
Remote Sensing Assessment of Lunar Resources: We Know Where to Go to
Find What We Need [#6029]
3:00 p.m. Dissly R. W. Buehler M. G. Schaap M G. Nicks D. Taylor G. J.
Castano R. Suarez D.
Autonomous In-Situ Resources Prospector [#6017]
3:15 p.m. Anderson R. C. Buehler M. G. Seshardri S. Schaap M. G.
Dielectric Constant Measurements on Lunar Soils and Terrestrial Minerals [#6035]
3:30 p.m. Klaus K.
Near Earth Object Characterization, Exploration and Exploitation [#6025]
3:45 p.m. Woodworth-Lynas C. M. T. GuigneJ. Y. HartD. Davidson R.
Concept for Landed Measurements of Mars that will Help Identify and Characterize
Potential Surface Resources [#6042]
4:00 pm. KuhlmanK. R., BeharA. E. Jones J. A. Carsey F. Hajos G. A.
Flick J. J. AntolJ.
Tumbleweed: A New Paradigm for Surveying the Surface of Mars for
In-Situ Resources [#6041]
4:15 p.m. Mandell H. C.
Mars Deep Drilling Remains a High Priority [#6001]
Space Resources Roundtable VI
4:30 p.m. Stoker C.
Drilling to Extract Liquid Water on Mars: Feasible and Worth the Investment [#6002]
5:00 p.m. SPACE RESOURCES ROUNDTABLE BOARD MEETING
(OPEN TO ALL)
Tuesday, November 2, 2004
8:00 a.m. Continental Breakfast and Registration
MATERIALS HANDLING AND PROCESSING TECHNIQUES
Moderators: L. Gertsch and A. Ignatiev
8:30 a.m. Schmitt H. H.
Solar Wind Helium Concentrations in Undisturbed Lunar Regolith [#6039]
8:45 a.m. Jenkins J. T. Louge M. Y. Rame E.
Granular Flow and In-Situ Resource Utilization [#6019]
9:00 a.m. Behringer R. P. Wilkinson R. A.
Granular Materials and Risks In-Situ [#6021]
9:15 a.m. SchisslerA. Kecojevic V.
Intelligent Excavation for the Moon [#6016]
9:45 a.m. Boucher D. S. Richard J.
Report on the Construction and Testing of a Bucket Wheel Excavator [#6004]
10:00 a.m. BREAK
10:15 a.m. McCandless A. MotakefS. GuidryD. OverholtM.
Micro-Structured Heat Exchangers and Reactors for ISRU
and Energy Conversion [#6038]
10:30 a.m. Rodriguez G.
Lunar and Martian Fiberglass as a Versatile Family of ISRU
Value-Added Products [#6034]
10:45 a.m. Westfall R. Jenkin W. C.
Steel Production Utilizing Iron Extracted from Lunar Ores and Soils [#6020]
1 1 :00 a.m. Sibille L. Gavira-Gallardo J. A. Hourlier-Bahloul D.
Synthesis of Sol-Gel Precursors for Ceramics from Lunar and
Martian Soil Simulants [#6015]
11:15 a.m. Zhang X. Yi H. C. Guigne J. Y. Mannerbino A. Moore J. J.
The Application of Self-Propagating High Temperature (Combustion)
Synthesis (SHS) for In-Space Fabrication and Repair [#6011]
11:30 England C.
Extraction of Oxygen from the Martian Atmosphere [#6036]
LPJ Contribution No. 1224
Tuesday, November 2, 2004 (continued)
12:00 -1:30 p.m. LUNCH in Green Center
1:30 - 2:30 p.m. PANEL DISCUSSION
Mars Human Missions: Propellant from Atmosphere, Regolith, or Ice?
Panelists: Sanders J. Taylor G. J. England C. Ash R.
MINING CLAIMS AND SPACE LAW
Moderator: M. Duke
2:30 p.m. White W. N.
Space Law Update: Real Property Rights and Resource Appropriation [#6009]
2:45 p.m. Rodriguez G.
Telepossession Transforms Asteroids into Resources [#6033]
3:00 p.m. Discussion: Legal Issues
IMPROVING OPERATIONS ON PLANETARY SURFACES
Moderator: S. Mackwell
3:15 p.m. JoynerR. Rodriguez G.
Power Lander for Support of Long-Term Lunar Presence [#6032]
3:30 p.m. Wray T. RodruguezG.
Using Spent Fuel Tanks as Habitats [#6031]
3:45 p.m. Angel H. Thanh P. NakagawaM.
Dust Mitigation of Astronaut Spacesuits [#6030]
4:00 - 4:45 p.m. Discussion: ISRU Demonstration Experiments and Flights
Moderator: Jeff Taylor
6:00 p.m. RECEPTION AND DINNER in Green Center
Speaker: Robert Ash
"Why Don 't You See if You Can Make Rocket Fuel at Mars? " — 27 Years Later
Wednesday, November 3, 2004
8:00 a.m. Continental Breakfast and Registration
ECONOMICS AND EXPLORATION ARCHITECTURES
Moderators: H. H. Schmitt and B. Blair
8:30 a.m. Blair B. B. Diaz J. RuizB. Duke M. B.
ISRU Technology Modeling and Analysis [#6026]
8:45 a.m. Blair B. B. Duke M. B. Diaz J. RuizB.
Costs and Benefits of ISRU-Based Human Space Exploration [#6027]
Space Resources Roundtable VI 5
Wednesday, November 3, 2004 (continued)
9:00 a.m. England C. Hallinan K. P.
Minimizing Launch Mass for ISRU Processes [#6037]
9:30 a.m. Reynerson C. M.
Exploration of the Impact of ISRU on Architectural System Mass and Cost [#6008]
9:45 a.m. Davis H. P.
Space Transportation for a Lunar Resources Base [#6013]
10:00 a.m. O'DaleC. D.
Lessons from Earth: Experiences Which can Guide Lunar and
Asteroidal Development [#6006]
10:15 a.m. BREAK
10:30 a.m. Heiss K. P.
Economic Laws and the Lunar Imperative: Outline of Components for a Sustained
Development Strategy [#6007]
10:45 a.m. Konesky G. A.
Mission Design for Economically Self-Supporting Large Scale
Lunar Telepresence [#6010]
11:00 a.m. MorinL.M.E.
Rocks to Robots: A Biological Growth, Approach to Rapid Lunar Industrialization
or How to Realize Von Neumann's Vision [#6018]
11:15 a.m. Nakamura T.
Solar Energy Utilization for In-Situ Resource Utilization [#6014]
11:30 a.m. AshR. L.
Toward a Sustainable Mars Infrastructure [#6012]
1 1 :45 a.m. Final Remarks
12:00 p.m. Meeting Adjourns
1:30 p.m. ISRU CAPABILITY WORKSHOP
PRINT-ONLY PRESENTATIONS
Kuhlman K. R., Kulcinski G. L., and H. H. Schmitt
Simulation ofHelium-3 Extraction from Lunar Ilmenite [#6044]
Space Resources Roundtable VI 7
DIELECTRIC CONSTANT MEASUREMENTS ON LUNAR SOILS AND
TERRESTRIAL MINERALS
R. C. Anderson 1 , M. G. Buehler 1 , S. Seshardri 1 , and M.G. Schaap 2
'jet Propulsion Laboratory, Pasadena, CA 91 1 09, 2 University of California, Riverside,
Martin.G.Buehler@jpl.nasa.gov
Introduction: The return to the Moon has ignited the need to characterize the lunar regolith using in situ
methods. An examination of the lunar regolith samples collected by the Apollo astronauts indicates that only a
few minerals (silicates and oxides) need be considered for in situ resource utilization (ISRU). This simplifies
the measurement requirements and allows a detailed analysis using simple methods. Characterizing the
physical properties of the rocks and soils is difficult because of many complex parameters such as soil
temperature, mineral type, grain size, porosity, and soil conductivity. In this presentation, we will show that the
dielectric constant measurement can provide simple detection for oxides such as Ti02, FeO, and water. Their
presence is manifest by an unusually large imaginary permittivity.
Impedance Spectrometer: The dielectric constant, s, is expresses as the product of the permittivity of free
space, eo, times the relative permittivity, e r . The permittivity is further described as E r = e' - ie" where e' is the
real permittivity and s" is the imaginary permittivity [1], Fig. 1 shows that the real permittivity, e' can be used
to determine the density of lunar soils [2] and terrestrial minerals [3]. The simple relationship shown in the
figure holds for silicates and oxides with a few exceptions such as titanates which have high permittivities. The
graph in Fig. 2 demonstrates a direct correlation between the amount of %Ti0 2 + %FeO in the lunar soil. At a
measured e', the amount of %Ti0 2 + %FeO is determined from e". Other minerals or water can also cause e"
to be abnormally large. The deviation of the e" versus e' above the %Ti0 2 + %FeO = line signals the
detection of a mineral in the regolith that needs further identification by, for example, Raman or XRD. The
data [2] in Fig. 2 was fitted using a multivariate least squares method; the equation is at the top of the graph.
1000'
H Terrestrial Titanates
♦ Terrestrial Minerals
♦ Lunar Soils
— Fit to all non tltanate data
E' = 1.555p
log(t") » -3.02 + 0.0293"C(y.) ♦ 0.288*?
C = %TI02+%FeO
♦ Lunar Soils
.%Ti02+»XFeO
-%T!02+%FeO
-%Ti02+%FeO = 16
-%TI02+%FeO « 24
-%Ti02+WeO » 32
-%Tl02+WeO ■ 40
0.001
10
Dielec4904.xls
DENSITY, p (g/cm J )
Dielec4904.xls
REAL PERMITTIVITY, t'
Figure 1. Relationship between real permittivity and
density of lunar soils [2] and terrestrial minerals [3].
Figure 2. e" versus e' for various percentages of Ti0 2
and FeO for lunar soils obtained from Apollo
missions [2].
Conclusion: Prospecting for minerals on the surface of the Moon calls for developing rapid survey techniques.
We propose using impedance spectroscopy that provides dielectric constant measurements, electrostatic
measurements that provide data for signature analysis techniques, and magnetic properties measurements. All
of these measurements are rapid and the sensors are small and so can be incorporated into the wheel of a
roving vehicle allowing real-time in situ measurements while the vehicle is in motion.
Acknowledgements: The authors are grateful to Walter Russel, USDA-ARS George E. Brown, Jr. Salinity
Laboratory, for extracting the lunar soil data from [2]. File: Dielec4A08Pub.doc
References: [1] Anderson, J. C. Anderson, Dielectrics, Reinhold Publishing Corp. (New York, 1964).
[2] Heiken, G, D. Vaniman, and B. M. French, Lunar Sourcebook, Cambridge University Press (New York, 1991).
[3] R. S. Carmichael, Practical Handbook of Physical Properties of Rocks and Minerals, CRC Press (Boca Raton,
Florida, 1990).
8 LP1 Contribution No. 1224
DUST MITIGATION ON ASTRONAUT SPACESUITS
H. Angel, P. Thanh, M. Nakagawa
Colorado School of Mines
1500 Illinois St.
Golden, CO 80401
hangel@mines.edu, pthanh@mines.edu, mnakagaw@mines.edu,
The particles that make up moon dust and Mars soil can be hazardous to an astronaut's
health if not handled properly. Exploration missions require astronauts to establish base habitat on
the surface of the Moon and Mars. During these explorations, dust and soil will cling to their
space suits and become imbedded in the fabric. The astronauts will track moon dust and mars
soil back into their living quarters. This not only will pollute cabin air with millions of tiny air-
born particles floating around, but will also be dangerous in the case that the fine particles are
breathed in and become trapped in an astronaut's lungs.
In order to mitigate this problem, engineers and scientists at the NASA-Glenn research
center and at the Colorado School of Mines are investigating ways to remove these particles from
space suits. This problem is very difficult due to the nature of the Lunar regolith: They are
extremely small and have jagged edges which can easily latch onto the fibers of the fabric.
Important factors in determining a technique include low power and material usage do to the
limited supplies in space, making the equipment durable so that it will require little work from
astronauts, and the effectiveness, or amount of dust the technique can remove.
The current technique under investigation uses vibrating motors imbedded in the fabric
that vibrate and shake the particles free. The particles will be left on the planet's surface or
collected in a vacuum to be disposed of later. The motors have an unevenly weighted shaft that,
when connected to a power supply, spins unevenly and creates a motion on the fabric similar to
what people use at the beach to shake sand off of a beach towel. Because the particles are so
small, similar to volcanic ash, caution must be taken to make sure that this technique does not
further imbed them into the fabric and make removal more difficult. Only a very precise range of
frequency and amplitude of the fabric will produce a suitable vibration. Analysis was done to
determine what input factors, such as power, tension in the fabric, and size of motor would
produce the desired output.
Space Resources Roundtable VI 9
TOWARD A SUSTAINABLE MARS INFRASTRUCTURE
Robert L. Ash
Aerospace Engineering Department, Old Dominion University, Norfolk, VA 23529
RAsh@odu.edu
Currently, there are four nuclear electric power-generating units operating on Mars (pairs of
radioisotope thermal generators, now generating a little of 70 W each, located at the VL-1 and
VL-2 landing sites), one small dusty solar array {Sojourner) and two somewhat larger solar
arrays — one each for the Mars Rovers Spirit and Opportunity— -in use currently. In addition,
there are two Viking Landers, three robotic rovers with landers and scientific instruments,
numerous aeroshells with associated entry gear, and a variety of crashed landers (Mars 2, Mars 3,
Mars 6, Mars Polar Lander, and Beagle) strewn about the Mars landscape. Electric power on the
Mars surface is in short supply, but electric power will be the key for developing a robust
infrastrucure capable of supporting human explorers.
This talk will utilize the author's more than 25-year involvement with engineering system designs
focused on the utilization of extraterrestrial resources, in order to frame the issues related to
evolving a sustainable infrastructure on a planetary body that is too far from Earth for
teleoperation and too far from the Sun to rely completely on Solar power. The talk will discuss
some early work and its legacy, in the context of major increases in distributed computational
power, component miniaturization and other advances. In order to build up a capability to return
humans from the Martian surface, an unmanned landing and return site with significant levels of
on-demand electric power is needed critically, but budgetary constraints and relatively short
mission-planning horizons, along with the severe constraints that result from "locking-in" a
landing site, will make such a determination and selection extremely difficult to justify. The
author is beginning to collaborate with Old Dominion University's National Center for System of
Systems Engineering, examining in situ resource utilization in the context of Moon, Mars and
Beyond planning and those implications will be discussed.
10 LPI Contribution No. 1224
GRANULAR MATERIALS AND RISKS IN ISRU
Robert P. Behringer' and R. Allen Wilkinson 2
'Department of Physics, Duke University, Durham, N.C. 27708-0305
bob@phy.duke.edu
2 NASA Glenn Research Center, MS 1 10-3, 21000 Brookpark Rd., Cleveland, OH 44135
aw@grc.nasa.gov
Working with soil, sand, powders, ores, cement and sintered bricks, excavating, grading
construction sites, driving off-road, transporting granules in chutes and pipes, sifting gravel,
separating solids from gases, and using hoppers are so routine that it seems straightforward to
execute these operations on the Moon and Mars as we do on Earth. We discuss how little these
processes are understood and point out the nature of trial-and-error practices that are used in
today's massive over-design. Nevertheless, such designs have a high failure rate. Implementation
and extensive incremental scaling up of industrial processes are routine because of the inadequate
predictive tools for design. We present a number of pragmatic scenarios where granular materials
play a role, the risks involved, what some of the basic issues are, and what understanding is
needed to greatly reduce the risks. This talk will focus on a particular class of granular flow
issues, those that pertain to dense materials, their physics, and the failure problems associated
with them. In particular, key issues where basic predictability is lacking include stability of soils
for the support of vehicles and facilities, ability to control the flow of dense materials (jamming
and flooding/unjamming at the wrong time), the ability to predict stress profiles (hence create
reliable designs) for containers such as bunkers or silos. In particular, stress fluctuations, which
are not accounted for in standard granular design models, can be very large as granular materials
flows, and one result is frequent catastrophic failure of granular devices.
Space Resources Roundtable VI 1 1
ISRU TECHNOLOGY MODELING AND ANALYSIS
Blair, B. R., Diaz, J., Ruiz, B. and Duke, M. B.
Center for Commercial Applications of Combustion in Space, RL 232,
Colorado School of Mines, 1500 Illinois Street, Golden, CO 80401
bblair@mines.edu
A preliminary In Situ Resource Utilization (ISRU) technology matrix has been developed that
identifies the type of technology, its applications, the rationale for wanting to improve
performance, its current status and expected (or desired) future performance. This database can
be utilized to determine where the most effective investments can be made in ISRU technologies
(as opposed to ISRU systems). Technologies are sorted into demonstration of feasibility vs.
performance improvement (optimality) categories through membership in a metric called critical
path. Improvements and updates to the technology database will be solicited during SRR6
through a formal survey process.
An approach to modeling the investment value for developing ISRU technology will also be
presented, along with quantitative results for specific ISRU subsystems. The basis for the
valuation of technology is performance per unit mass (also known as specific mass). The method
used to derive value is sensitivity analysis of technical performance parameters within an
integrated architectural and economic modeling for ISRU-based human lunar exploration.
Changes in technical parameters are mapped directly into economic costs for the exploration
scenario. Improvements in overall cost related to enhancing specific technical performance
parameters are interpreted as total value of the new technology.
12 LPI Contribution No. 1224
COSTS AND BENEFITS OF ISRU-BASED HUMAN SPACE
EXPLORATION
Blair, B. R, Duke, M. B., Diaz, J. and Ruiz, B.
Center for Commercial Applications of Combustion in Space, RL 232,
Colorado School of Mines, 1500 Illinois Street, Golden, CO 80401
bblair@mines . edu
A three phase 10-year scenario for In Situ Resource Utilization (ISRU)-based human exploration
architecture will be introduced as a foundation for an economic cost/benefit model of the value of
the use of space resources, including infrastructure and capability growth through time. This
architecture is generally consistent with the development of a self-sufficient outpost on the Moon
during the period 2020-2030, Cycle 2 of the current NASA exploration vision. A preparatory set
of robotic missions has also been assumed to emplace ISRU capabilities as well as infrastructure
in preparation for the first human missions. Models for both performance benefits (e.g. the
amount of mass that has to be transported from Earth to achieve the desired lunar capability) and
relative costs, compared to alternative scenarios that do not utilize ISRU have been developed.
Economic differences between the ISRU architecture and the all-expendable baseline will be
presented, which provide the basis for quantifying the benefits of ISRU development. Sensitivity
analysis of the integrated architectural/economic model will be used to recommend priorities for
future research and modeling. Economic conclusions that will be presented include expected
product unit costs and rate of return analysis.
Space Resources Roundtable VI 13
REPORT ON THE CONSTRUCTION AND TESTING OF A
BUCKET WHEEL EXCAVATOR
Dale S. Boucher', Jim Richard 2
'Northern Centre for Advanced Technology Inc. 1400 Barrydowne Road, Sudbury,
Ontario, Canada, P3A 3V8
2 Electric Vehicle Controllers Ltd, 2200 Valleyview Road, Val Caron, Ontario, Canada,
P3N 1L1
Phone: (705) 521-8324 x202, email: dboucher@norcat.org
The Northern Centre for Advanced Technologies Inc. (NORCAT), in partnership with Electric
Vehicle Controllers Ltd. (EVC), is presently engaged in the development and adaptation of
existing mining technologies and methodologies for use extra-terrestrially as precursor and
enabling technologies for ISRU and for use as ISSE in support of longer term missions.
More specifically, NORCAT, in collaboration with Colorado School of Mines, has developed,
constructed, and tested a bucket wheel excavator. The unit is based upon the design developed by
CSM's Mike Duke and Tim Muff.
The design of the test unit was developed with the CSM design as a guide. Considerations were
exercised to facilitate construction and testing of key operational parameters. This yielded some
changes in design and operating concepts, which were incorporated where appropriate. In
addition, some bottle necks and weak points were identified in the original design.
NORCAT engaged Natural Resources Canada (NRCan) to fabricate a lunar regolith simulant
from mine tailings that would exhibit some significant similarities to the reported mechanical
properties of lunar regolith. The Bucket wheel unit was tested in this simulant in October 2004.
This presentation will report some key results of the Bucket wheel re-design.
14 LP! Contribution No. 1224
THE LUNAR POLAR ILLUMINATION ENVIRONMENT: WHAT WE
KNOW & WHAT WE DON'T
D.B.J. Bussey and P.D. Spudis
The Johns Hopkins University Applied Physics Laboratory
1 1 100 Johns Hopkins Road
MP3-E180
Laurel MD 20723
Email: ben.bussey@jhuapl.edu
Introduction. The Moon's spin axis is nearly perpendicular to the ecliptic plane which results
in unusual lighting conditions at the lunar poles. Areas which have low elevation, such as the floors
of impact craters, may never see the Sun, i.e. they are permanently shadowed, whilst regions of high
elevation, relative to the local terrain, may be permanently illuminated. The polar illumination
conditions represent a key resource with respect to returning to the Moon. Possible ice deposits must
be located in areas of permanent shadow, whilst the existence of a region in permanent sunshine has
ramifications as a future base site.
Current Knowledge. An analysis of the lunar polar lighting using Clementine image data
revealed some interesting illumination conditions. No place in the south polar region appears to be
permanently illuminated (Figure 1L). However several regions exist which are illuminated for
greater than 70% of a lunar day in winter. Two of these regions, which are only 10 km apart, are
collectively illuminated for more than 98% of the time. Near' the north pole four areas on the rim of
Peary crater were constantly illuminated for an entire lunar day in summer. Both polar regions
contain numerous areas of permanent shadow close to each pole.
Modeling of simple impact craters has revealed that there is extensive permanent shadow
associated with these features, at least 7500 km 2 and 6500 km 2 at the north and south poles
respectively. Additionally permanent shadow can exist in craters more than 10° latitude away from a
pole (Figure 1R). These areas represent potential cold traps for volatile deposits.
Figure 1. The image on the left is an illumination map of the lunar south pole showing the percentage
of a lunar day that a point on the surface is illuminated. The mosaic on the right is a map of the
northern lunar polar region showing the location of simple craters that contain permanent shadow.
Future Data. In order to definitively understand the lunar illumination environment, more
data is required. Wide area imaging coverage over an entire year is necessary to identify all regions
of illumination extremes. Additionally lighting simulations using high resolution topography can
produce quantitative illumination maps.
Space Resources Roundtable VI 15
LUNAR SIMULANTS: JSC-1 IS GONE;
THE NEED FOR NEW STANDARDIZED ROOT SIMULANTS
James L. Carter 1 , David S. McKay 2 , Lawrence A. Taylor 3 , & W. David Carrier III 4
1 Dept. of Geosciences, University of Texas at Dallas, Richardson, TX 75083jcarter@utdallas.edu
2 Planetary Exploration, Johnson Space Center, Houston, TX 77058 david.s.mckay@jsc.nasa.gov
3 Planetary Geosciences Institute, University of Tennessee, Knoxville, TN 37996 lataylor@utk.edu
4 Lunar Geotechnical Institute, Lakeland, FL 33807-5056 dcarrier@tampabay.rr.com.
A workshop [1] was held in 1991 to evaluate the status of simulated lunar regolith material and to make
recommendations on future requirements and production of such material. As an outgrowth of that workshop,
a group centered at Johnson Space Center (JSC) teamed with James Carter of the University of Texas at
Dallas and Walter Boles of Texas A&M University to produce and distribute a new standardized lunar
regolith simulant termed JSC-1. Carter supervised the field collection, shipping, processing, and initial
packaging and transportation of JSC-1. Boles stored and distributed JSC-1. About 25 tons were created and
distributed to the lunar science and engineer community; none is left for distribution. JSC-1 served an
important role in concepts and designs for lunar base and lunar materials processing. Its chemical and
physical properties were described by McKay et al. [2], with its geotechnical properties described by Klosky
et al. [3]. While other lunar regolith simulants were produced before JSC-1 [4-6], they were not standardized,
and results from tests performed on them were not necessarily equivalent to test results performed on JSC-1.
JSC-1 was designed to be chemically, mineralogically, and texturally similar to a mature lunar mare regolith
(low titanium). The glass-rich character of JSC-1 (-50%) produced quite different properties compared to
other simulants that were made entirely of comminuted crystalline rock, but properties similar to lunar mare
near surface regolith.
While it would be difficult to completely duplicate JSC-1, it should be a model for new simulants in
which the chemical and physical properties of the lunar regolith are duplicated as closely as possible. We
propose that the concept of a standardized simulant be followed by the community, in which large quantities
(more than 100 tons) of simulant is produced in a manner that homogenizes it so that all subsamples are
equivalent. From this root simulant it would then be possible to produce other more specialized simulants,
for example, by implanting solar wind, by adding ice in various proportions, or by adding specific
components such as metallic iron, carbon, organics, or halogens to more closely simulate special properties
of lunar regolith needed for specific kinds of tests and experiments. In all cases, the specialized simulant
branches should begin with the standardized root simulant. While JSC-1 was a mare simulant, an additional
root highland simulant would be desirable. Many of the proposed landing sites are in highland terrain, and
the properties of lunar highland regolith have some fundamental differences compared to mare regolith.
Consequently, we suggest that it is important to design and produce a standardized root highland simulant,
as well.
We also propose that the new root lunar simulants be collected at a single locality and characterized by
a science and engineering team. New security restrictions make it difficult for JSC to be the collection and
distribution site; it will be necessary to perform this service elsewhere. While JSC-1 was distributed at no
cost to the customers other than shipping, in this new era of full-cost accounting, the new lunar simulants
must be paid for by the customers.
Although preparations are underway for the production of JSC-2, a "clone" of JSC-1, it would appear
that a workshop is necessary to bring the community together to form a consensus on requirements for new
lunar standardized root simulants and for some of the specialized branch simulants.
REFERENCES: [1] McKay, D.S. and Blasic, J.D. (1991) Workshop on Production and Uses of Simulated
Lunar Materials, LPI Tech Report 91-04, 83pp; [2] McKay et al. (1994) Space IV, ASCE, 857-866; [3]
Klosky et al. (1996) Space V, ASCE, 680-688; [4] Weiblen et al. (1990) Space H, ASCE, 428-435; [5] Desai
et al. (1992) J. Aerospace Eng. 5, 425-441; [6] Chua et al. (1994) Space IV, ASCE, 867-877.
1 6 LPI Contribution No. 1224
SPACE TRANSPORTATION FOR A LUNAR RESOURCES BASE (LRB)
Hubert P. Davis, Starcraft Boosters, Inc.
1032 Military Drive
Canyon Lake, TX 78133
(830) 935-2743
email: hudavis@gvtc.com
This is a report of a work in progress. So far as the author is presently aware, this topic has not
been previously addressed. Proprietary work by NASA or others may, however, exist that
address similar topics.
This work assumes that a base near the South Pole of our Moon will be established for the
purpose of exploiting the resources of the Moon; principally the water ice that many believe was
discovered by the Clementine and Lunar Prospector satellites. The ice is of particular value as,
with the aid of the ample solar resource available nearby, it may become an essentially limitless
source of oxygen / hydrogen propellants for continued visitation to and expansion of the base and
for the support of additional space exploration missions, including human exploration of Mars.
This work placed a total 1 29 tons initial base for both the in-crater and crater rim installations, as
well as a 90 tons "marshalling yard" at the Earth-Moon L-l libration point. For launch services,
the results of an in-house Shuttle-Derived Heavy Lift Launch Vehicle study were used. It is called
Aquila. This vehicle can deliver over 50 tons to low Earth orbit from the Kennedy Space Center,
using a combination of Space Shuttle and Delta IV-Heavy components.
A second stage of the Delta IV-Heavy vehicle was used to deliver 15 tons payloads from Earth
orbit to docking at L-l. By so doing, no "new start" systems are needed beyond those of the L-l
station and the LRB itself, provided the Aquila and Crew Exploration Vehicle have been
previously developed. At L-l, three of these once-used stages are fitted with landing gear and
other elements needed to produce a highly capable Lunar Vehicle and it is refueled from
propellants delivered from Earth to place the base and to provide a single visit of a six person
crew to aid the robotic operations necessary to produce a fully functional base.
If the ground rule is established that "dry" cargo and propellant must be launched separately, 34
launches were required. This will permit over 50% of the launches to launch only propellants.
Later missions, using propellants produced by the LRB, show a large net gain in propellants
available at L-l. For example, a round trip mission with the CEV results in a net gain of over six
tons of propellant at L-l; a cargo delivery nets over 69 tons.
Work continues on the "pay-off phase; that is, further missions making use of the propellants
obtained from the shallow "gravity well" of the Moon. Propellants produced on the Moon will
only be used from the lunar surface or from L- 1 ; no attempt will be made to deliver them to other
locations. That will come, but is "out-of-scope" for the present work.
A Mars mission departing from L-l with mass of 686 tons can be placed on the trans-Mars
trajectory expending lunar-origin propellants and just one of the Lunar Vehicles, requiring an
additional 13 Aquila launches. This will permit dual Mars spacecraft to be used for each mission
with a 28% mass margin over a single, similar mass vehicle departing from low Earth orbit.
Space Resources Roundtable VI 1 7
AUTONOMOUS IN-SITU RESOURCES PROSPECTOR
R.W. Dissly 1 , M.G. Buehler 2 , M.G. Schaap 3 , D. Nicks', G.J. Taylor 4 , R. Castano 2 , D. Suarez 3
1) Ball Aerospace & Technologies Corp., 1600 Commerce St., Boulder, CO 80301,
rdissly@ball.com, dnicks@ball.com
2) Jet Propulsion Laboratory, 4800 Oak Grove Dr., Pasadena, CA 91 109,
Martin.G.Buehler@jpl.nasa.gov, Rebecca.Castano@jpl.nasa.gov,
3) GEBJ Salinity Laboratory (USDA/ARS), 450 Big Springs Road, Riverside, CA 92507
mschaap@ussl.ars.usda.gov, dsuarez@ussl.ars.usda.gov,
4) University of Hawai'i, 1680 East- West Rd., Honolulu, HI 96822
gjtaylor@higp.hawaii.edu
This presentation will describe the concept of an autonomous, intelligent, rover-based rapid surveying
system to identify and map several key lunar resources to optimize their ISRU (In Situ Resource
Utilization) extraction potential. Prior to an extraction phase for any target resource, ground-based
surveys are needed to provide confirmation of remote observation, to quantify and map their 3-D
distribution, and to locate optimal extraction sites (e.g. ore bodies) with precision to maximize their
economic benefit.
The system will search for and quantify optimal minerals for oxygen production feedstock, water ice,
and high glass-content regolith that can be used for building materials. These are targeted because of their
utility and because they are, or are likely to be, variable in quantity over spatial scales accessible to a
rover (i.e., few km). Oxygen has benefits for life support systems and as an oxidizer for propellants.
Water is a key resource for sustainable exploration, with utility for life support, propellants, and other
industrial processes. High glass-content regolith has utility as a feedstock for building materials as it
readily sinters upon heating into a cohesive matrix more readily than other regolith materials or
crystalline basalts. Lunar glasses are also a potential feedstock for oxygen production, as many are rich in
iron and titanium oxides that are optimal for oxygen extraction.
To accomplish this task, a system of sensors and decision-making algorithms for an autonomous
prospecting rover is described. One set of sensors will be located in the wheel tread of the robotic search
vehicle providing contact sensor data on regolith composition. Another set of instruments will be housed
on the platform of the rover, including VIS-NTR imagers and spectrometers, both for far-field context and
near-field characterization of the regolith in the immediate vicinity of the rover. Also included in the
sensor suite are a neutron spectrometer, ground-penetrating radar, and an instrumented cone penetrometer
for subsurface assessment. Output from these sensors will be evaluated autonomously in real-time by
decision-making software to evaluate if any of the targeted resources has been detected, and if so, to
quantify their abundance. Algorithms for optimizing the mapping strategy based on target resource
abundance and distribution are also included in the autonomous software.
This approach emphasizes on-the-fly survey measurements to enable efficient and rapid prospecting
of large areas, which will improve the economics of ISRU system approaches. The mature technology
will enable autonomous rovers to create in-situ resource maps of lunar or other planetary surfaces, which
will facilitate human and robotic exploration.
1 8 LPI Contribution No. 1224
EXTRACTION OF OXYGEN FROM THE MARTIAN ATMOSPHERE
C. England
'Jet Propulsion Laboratory, Pasadena, CA 91 109, cengland@jpl.nasa.gov
A mechanical process was designed for direct extraction of molecular oxygen from the martian
atmosphere based on liquefaction of the majority component, C0 2 , followed by separation of the
lower-boiling components. The atmospheric gases are compressed from about 0.007 bar to 13
bar and then cooled to liquefy most of the C0 2 . The uncondensed gases are further compressed
to 30 bar or more, and then cooled again to recover water as ice and to remove much of the
remaining C0 2 . The final gaseous products consisting mostly of nitrogen, oxygen, and carbon
monoxide are liquefied and purified by cryogenic distillation. The liquefied C0 2 is expanded
back to the low-pressure atmosphere with the addition of heat to recover a majority of the
compression energy and to produce the needed mechanical work. Energy for the process is
needed primarily as heat to drive the C0 2 -based expansion power system. When properly
configured, the extraction process can be a net producer of electricity.
The conceptual design, termed "MARRS" for Mars Atmosphere Resource Recovery System, was
based on the NASA/JSC Mars Reference Mission (MRM) requirement for oxygen. This mission
requires both liquid oxygen for propellant, and gaseous oxygen as a component of air for the
mission crew. With single redundancy both for propellant and crew air, the oxygen requirement
for the MRM is estimated at 5.8 kg/hr. The process thermal power needed is about 120 kW,
which can be provided at 300-500°C. A lower-cost nuclear reactor made largely of stainless steel
could serve as the heat source.
The chief development needed for MARRS is an efficient atmospheric compression technology,
all other steps being derived from conventional chemical engineering separations. The
conceptual design describes an exceptionally low-mass compression system that can be made
from ultra-lightweight and deployable structures. This system adapts to the rapidly changing
martian environment to supply the atmospheric resource to MARRS at constant conditions.
The large amounts of liquid C0 2 by-product that are produced enable a comprehensive martian
surface architecture using this liquid as an open cycle working fluid. While most of the 1000
kg/kg oxygen is expanded for power recovery, a small fraction is stored and made available for
emergency or backup power, transportation, and surface operations such as drilling. The
availability of highly redundant backup power and transportation systems makes the MARRS
concept particularly attractive for piloted missions to Mars.
The current study outlines an inherently flexible surface architecture for Mars exploration that
uses nuclear heat, a compression-dominated process for extraction of atmospheric resources, and
provides a mechanism for highly redundant and reliable operations. The amounts of minor
components in the atmosphere, however, are uncertain. While the conceptual design for MARRS
is based on a 0.13% oxygen concentration, the actual average value is now believed to be about
0.3%. Such a high value would allow even greater flexibility in design, and greatly reduce the
energy and mass requirements to produce oxygen for the MRM. A more detailed design is
needed to account for the uniquely high variability in composition, pressure and temperature that
characterize the martian atmospheric environment.
Space Resources Roundtable VI 19
MINIMIZING LAUNCH MASS FOR ISRU PROCESSES
C. England 1 andK.P. Hallinan 2
'Jet Propulsion Laboratory, Pasadena, CA 91 109, cengland@jpl.nasa.gov
2 University of Dayton, Dayton, OH 45469-0210, kevin.hallinan@notes.udayton.edu
The University of Dayton and the Jet Propulsion Laboratory are developing a methodology for
estimating the Earth launch mass (ELM) of processes for In-Situ Resource Utilization (ISRU)
with a focus on lunar resource recovery. ISRU may be enabling for both an extended presence on
the Moon, 1 ' 2 and for large sample return missions and for a human presence on Mars. 2 To
accomplish these exploration goals, the resources recovered by ISRU must offset the ELM for the
recovery process. An appropriate figure of merit is the cost of the exploration mission, which is
closely related to ELM. For a given production rate and resource concentration, the lowest ELM
- and the best ISRU process - is achieved by minimizing capital equipment for both the ISRU
process and energy production.
ISRU processes incur Carnot limitations and second law losses (irreversibilities) that ultimately
determine production rate, material utilization and energy efficiencies. Heat transfer, chemical
reaction, and mechanical operations affect the ELM in ways that are best understood by
examining the process's detailed energetics. Schemes for chemical and thermal processing that
do not incorporate an understanding of second law losses will be incompletely understood.
Our team is developing a methodology that will aid design and selection of ISRU processes by
identifying the impact of thermodynamic losses on ELM. The methodology includes mechanical,
thermal and chemical operations, and, when completed, will provide a procedure and rationale for
optimizing their design and minimizing their cost. The technique for optimizing ISRU with
respect to ELM draws from work of England and Funk 3 that relates the cost of endothermic
processes to their second law efficiencies. Our team joins their approach for recovering resources
by chemical processing with analysis of thermal and mechanical operations in space.
Commercial firms provide cost inputs for ELM and planetary landing.
Our initial goal is to provide a generally-useful method for analysis of resource recovery in space
that is applicable to the Moon (vacuum environment) and Mars (convective environment). We
will develop a listing of irreversibility factors for important operations (such as countercurrent
heat recovery from solids) that will make the methodology easy to use. Our sample case is an
analysis of a hydro-winning process for oxygen from the lunar regolith.
Operations in space that generate irreversibilities are best understood by analyses that locate
where in the operation these losses are produced. Without having this information, designers are
limited in their understanding of process efficiency, much like 19 th century designers of power
production equipment prior to development of the second law of thermodynamics. Our
methodology not only can remove this guesswork, but can provide a cost-related figure of merit
by which ISRU methods and other processes conducted in space can be compared.
'Criswell ME and Abarbanel JE, "In-Situ Resource Utilization for Support of a Lunar Base,"
AIAA paper A98-16487, 36 th Aerospace Sciences Meeting and Exhibit, Reno, NV
January 12-15, 1998.
2 Sanders GB et al, "Preparing For Robotic And Human Exploration Missions. . . ," AIAA-paper
2000-5317, AIAA Space 2000 Conference and Exposition, Long Beach, CA, Sept. 19-21,
2000.
3 England C and Funk JE, "Reduced Product Yield in Chemical Processes by Second Law
Effects," ENERGY, 5, 941-947; 1980.
20 LPI Contribution No. 1224
REMOTE SENSING ASSESSMENT OF LUNAR RESOURCES: WE
KNOW WHERE TO GO TO FIND WHAT WE NEED
JJ. Gillis, G. J. Taylor, and P.G. Lucey, Hawai'i Institute of Geophysics and Planetology, 1680 East-
West Rd., University of Hawai'i, Honolulu, HI 96822. Gillis@higp.hawaii.edu
The utilization of space resources is necessary to not only foster the growth of human activities in
space, but is essential to the President's vision of a "sustained and affordable human and robotic program
to explore the solar system and beyond." The distribution of resources will shape planning permanent set-
tlements by affecting decisions about where to locate a settlement. Mapping the location of such re-
sources, however, is not the limiting factor in selecting a site for a lunar base. It is indecision about which
resources to use that leaves the location uncertain [1]. A wealth of remotely sensed data exists that can be
used to identify targets for future detailed exploration. Thus, the future of space resource utilization pre-
dominately rests upon developing a strategy for resource exploration and efficient methods of extraction.
The Clementine [2] and Lunar Prospector [3] missions have provided global datasets that already
provide the distribution of many potential lunar resources. Clementine acquired multispectral images
from ultraviolet through near-infrared wavelengths. These data allow assessments of the abundances of
major minerals (plagioclase, pyroxene, ilmenite, and olivine) on the Moon [4]. In addition, the data can be
used to determine the FeO and Ti0 2 contents of the surface to ~lwt% accuracy and high spatial resolution
[5-8]. The distribution of pyroclastic materials with their enrichments of FeO and Ti0 2 and possible vola-
tile elements are mapped using Clementine multispectral data and derived optical maturity data [9]. Per-
haps even more important, 3 He can be mapped by. association with Ti0 2 and surface maturity [10]. The
abundance of 3 He in the lunar regolith depends
on surface maturity, the amount of solar wind
flux, and titanium content. Clementine bi-static
radar data provided initial evidence that water-
ice exists in permanently-shadowed regions near
the poles.
Lunar Prospector gamma-ray and neutron
spectrometers determine the concentrations of
Fe, Ti, Th, K, H, Sm, and Gd [8, 1 1, 12]. Fe and
Ti data provide an independent check on the
concentrations determined by reflectance spec-
troscopy [6]. Neutron spectrometer data indicate
the presence of hydrogen deposits at the lunar
poles, which if present as water-ice suggests a
H 2 concentration of 1-2 wt% [13].
Earth-base radar observations (70 cm) also
have a sensitivity to bulk FeO and Ti0 2 abundance. The correlation of abrupt changes in radar return with
color boundaries in Clementine color and Ti0 2 images indicates that the data are controlled, to a signifi-
cant degree, by the Ti0 2 (ilmenite) composition of the regolith [14]. The greater depth of penetration of
radar data compared to the Clementine data (several meters versus microns) will allows the assay of Ti0 2
abundance to greater depth. Earth-based radar does not, however, concur with Clementine concerning the
existence of ice at the south pole of the Moon [15]. This apparent discrepancy in the presence of ice has
not been satisfactory explained, and will require closer study by orbiting and landed missions
References: [1] Taylor, G.J. & Martel L.M.V., Adv. Space Res. 31(11), 2003; [2] Nozette et al., Sci-
ence 266, 1994; [3] Binder, Science 281, 1998; [4] Lucey, GRL 31, 2004; [5] Lucey et al., JGR-P 105(E8)
2000; [6] Blewett et al., JGR-P 102, 1997; [7] Gillis et al., JGR-P 108(E2), 2003; [8] Lawrence et al.,
JGR-P 107(E12), 2002; [9] Lucey et al., JGR-P 105(E8) 2000; [10] Johnson et al., GRL 26(3), 1999; [11]
Lawrence et al., JGR-P 105(E8), 2000; [12] Elphic et al., JGR-P 105(E8), 2000; [13] Feldman et al.,
JGR-P 105, 2000; [14] Campbell et al., JGR-P 102 (E8), 2000; [15] Stacy et al, Science 276, 1997.
Mission
Measurements
Apollo ,
-100-150 km/pixel
Gamma-ray and X-ray data
Th, K, Mg, Si, Al
Clementine
(0.415,0.75,0.9,0.95,
1.0, 1.1,1.25, 1.5,2.0,
2.6, and 2.7 urn)
-200 m/pixel
Multispectral images:
FeO and Ti0 2
Mineralogy /Pyroclastics
Optical Maturity
3 He
Lunar Prospector
15-150 km/pixel
Gamma-ray and Neutron data
Fe, Ti, Th, K, H, Sm, Gd
Earth-based observa-
tions
2-5 km/pixel (spectra)
400 m/pixel (radar)
Visible to near infrared spectra
Mineralogy /Pyroclastics
Radar Backscatter
Maturity
Opaque abundance
Ice
Space Resources Roundtable VI 21
ROBOTIC SUBSURFACE ANALYZER AND SAMPLE HANDLER FOR
RESOURCE RECONNAISSANCE AND PRELIMINARY SITE ASSESSMENT
FOR ISRU ACTIVITIES AT THE LUNAR COLD TRAPS
S. P. Gorevan 1 ' ", J. Wilson 1 , P. Bartlett 1 , J. Powderly 1 , D. Lawrence 2 ' 12 , R. Elphic 2 , G. Mungas 3 ' 13 , E.
McCullough 4 ' 14 , C. Stoker 5 ' 15 , H. Cannon 5 , B. Glass 5 , W.D. Carrier 6 ' 16 , H. Schmitt 7 ' 17 , J. Johnson 8 ' ,8 , Cole 8 , C.
Dreyer 9 ' 19 , D.S. McKay 10 , R.V. Morris 10 ' 20
'Honeybee Robotics, New York, NY, ' 'gorevan@honeybeerobotics.com, 2 Los Alamos National Laboratory, Los
Alamos, NM, !2 djlawrence@lanl.gov, 3 Jet Propulsion Laboratory, Pasadena, CA, 13 Greg.S.Mungas@jpl.nasa.gov,
4 Boeing Phantom Works, Seal Beach, CA, 14 edward.d.mccullough@boeing.com, 5 Ames Research Center, Moffett
Field, CA, 15 cstoker@mail.arc.nasa.gov, ^unar Geotechnical Institute, Lakeland, FL,
16 dcarrier@tampabay.rr.com, 'University of Wisconsin, Madison, WI, 17 hhschmitt@earthlink.net, 8 Army Corp of
Engineers Cold Region Research and Engineering Laboratory, Hanover, NH,
18 Jerome.B.Johnson@erdc.usace.army.mil, 'Colorado School of Mines, Golden, CO, 19 cdreyer@mines.edu,
1 Johnson Space Center, Houston, TX, 20 richard.v.morris@nasa.gov
Since the 1960s, claims have been made that water ice deposits should exist in permanently shadowed
craters near both lunar poles. Recent interpretations of data from the Lunar Prospector-Neutron Spectrometer (LP-
NS) confirm that significant concentrations of hydrogen exist, probably in the form of water ice, in the
permanently shadowed polar cold traps. Yet, due to the large spatial resolution (45-60 km) of the LP-NS
measurements relative to these shadowed craters (-5-25 km), these data offer little certainty regarding the precise
location, form or distribution of these deposits. Even less is known about how such deposits of water ice might
effect lunar regolith physical properties relevant to mining, excavation, water extraction and construction. These
uncertainties will need to be addressed in order to validate fundamental lunar In Situ Resource Utilization (ISRU)
precepts by 2011. Given the importance of the in situ utilization of water and other resources to the future of
space exploration a need arises for the advanced deployment of a robotic and reconfigurable system for physical
properties and resource reconnaissance. Based on a collection of high-TRL designs, the Subsurface Analyzer and
Sample Handler (SASH) addresses these needs, particularly determining the location and form of water ice and
the physical properties of regolith. SASH would be capable of: (1) subsurface access via drilling, on the order of
3-10 meters into both competent targets (ice, rock) and regolith; (2) down-hole analysis through drill string
embedded instrumentation and sensors (Neutron Spectrometer and Microscopic Imager), enabling water ice
identification and physical properties measurements; (3) core and unconsolidated sample acquisition from rock
and regolith; (4) sample handling and processing, with minimized contamination, sample containerization and
delivery to a modular instrument payload. This system would be designed with three mission enabling goals,
including: (1) a self-contained, low power, low mass, "black box" configuration for operations from a lander,
various classes of rovers or a surface-based platform with human assistance or robotic anchoring mechanisms; (2)
reconfigurable and scalable sample handling for delivery to various types of instrumentation, depending on
mission requirements; and (3) the use of advanced automation control and diagnostic techniques that will afford
local human deployed, remote teleoperation and fully autonomous intelligent operations.
Though a great deal of technology has been advanced toward these objectives, the SASH system faces
significant design challenges, including the low gravity environment, various levels of autonomy in operations,
radiation exposure, dust contamination, and temperature extremes and deltas. Significant input from the scientific
and engineering communities, as well as a significant environmental testing program, will be required to guide the
design process.
The impact of this technology would be far-reaching. SASH would reduce cost, time and risk in the
pursuit of mission architectures and landing site selections for Lunar Planetary Surface Operations (LPSO),
specifically ISRU activities. During crewed missions, SASH would reduce unnecessary Extra- Vehicular Activity
risks to human safety. De-coupling SASH from a fixed surface instrumentation suite and delivery platform will
require a modular and flexible design. This will enable maximum reconfiguration and reuse over years of field
deployments, and multiple missions. The SASH system would significantly contribute to the OExS Technology
portfolio and would increase the potential success of ISRU on both the Moon and Mars.
22 LPI Contribution No. 1224
ECONOMIC LAWS AND THE LUNAR IMPERATIVE:
OUTLINE OF COMPONENTS FOR A SUSTAINED
DEVELOPMENT STRATEGY
Klaus P. Heiss
Director, High Frontier Inc.
With the renewed attention to Space Exploration and the role of humans in Space questions of
the uses of the Moon and other bodies of the Solar system have come to the forefront: is human
Space flight but a romantic quest of childhood dreams or are there key opportunities to be opened
and explored for the benefit of mankind - on Earth or in Space.
Economic laws - which apply in Space as well as on Earth - will limit beneficial uses of Space
for Earth to the immediate vicinity of Earth in the solar system, the Moon. These 'constraints'
will limit the uses for Earth to essentially observations, communications and energy - all
commodities with 'low mass' and 'speed of light' transmission.
The revolutionary concept of a 'condominium' of observation facilities is proposed for
observations of the universe, the sun and the Earth - providing a stable, nearly limitless aperture
across the electromagnetic spectrum with, huge advantages in reliability, costs and assurance of
continuity of observations. Similarly, communications, navigation, command and control of
civil and scientific activities on the Moon and for Cis-.and Translunar space will change
fundamentally.
Beyond these uses, the 'tapping' of the vast Solar energy resources available on the Moon
promises fundamental changes in Space operations, Space transportation and potentially clean
energy supplies across all regions of Earth. E.g. with 1 GWe supply on the Moon a new age of
'fuel less' space transportation across Cis- and Translunar space is enabled, ultimately allowing
speeds of up to one third the speed of light for missions to nearby solar systems.
Last and not least, with such assured energy supplies, all the lunar resources can be tapped for
the establishment of Closed Ecological Life Support Systems (CELSS) leading to the first
settlement independent of Earth - a most historic step for mankind to assuring its survival and
expansion into Space.
Key words:
Space observations, Space communications, Space transportation, energy supplies, lunar
resources, fuel less transportation, Space operations, closed ecological life support systems, Space
power, Space asset management, Space enterprise, Space exploration, Humans in Space,
assurance of survival.
Space Resources Roundtable VI 23
GRANULAR FLOW AND IN-SITU RESOURCE UTILIZATION
J. T. Jenkins*, M. Y. Louge # , and E. Rame +
♦Department of Theoretical and Applied Mechanics, Cornell University, Ithaca, NY 14853,
jtj2@cornell.edu
#Sibley School of Mechanical and Aerospace Engineering, Cornell University, Ithaca, NY 14853,
myl3@cornell.edu
+National Center for Microgravity Research in Fluids and Combustion, %NASA Glenn
Research Center, Cleveland, OH 44135, Enrique.Rame@grc.nasa.gov
The long-term human or robotic exploration of the Moon and Mars will require the ex-
ploitation of indigenous mineral and/or atmospheric resources. Technologies for In-Situ Resource
Utilization (ISRU) must be developed for propellant production, habitat, infrastructure, and the
extraction of water and breathable gas. Although a few of the required minerals are abundant,
others are present only in trace. Consequently, ISRU will require mining, transporting, process-
ing, and separating massive quantities of solid materials.
On Earth, these activities have been carried out on a large scale in the oil, chemical,
mining, and construction industries for more than a century. However, because the basic princi-
ples governing the transport of granular solids and their interaction with gases are poorly under-
stood, the design of reliable solids processes still involves conception on the lab scale, exhaustive
tests in a pilot unit, and operation of a demonstration plant. Because it is difficult to mimic condi-
tions of reduced gravity at the pilot scale, technology development for ISRU must strike a differ-
ent balance between empirical design and rational predictions. ISRU development must rely on
computer simulations and theoretical models to carry out scale-up.
In many computer simulations of granular solids, the particles are followed as discrete
entities. The challenge is to model accurately the interactions with the surrounding gas and the
collisions between particles. Theoretical models, on the other hand, employ a set of differential
equations, usually treating the gas and solid phases as inter-penetrating continua. A limitation of
models is that the constitutive laws, drag relations and boundary conditions employed in them are
not yet well-established. At this stage of their development, neither the simulations nor the mod-
els can be used blindly for design.
Experimental research in granular flow is necessary to test the predictions of the simula-
tions and theory against well-controlled experiments before they can be extended to reliable proc-
ess design. We will describe experiments that have been undertaken in microgravity to provide
such tests for particle segregation in collisional grain flows and for the transport of colliding
grains driven by a gas. In these two situations, there are preliminary indications that theory and
simulations capture important features of the flow, but additional experiments are required to
build confidence in the predictive powers of the simulations and the models.
24 LPI Contribution No. 1224
POWER LANDER FOR SUPPORT OF LONG-TERM LUNAR
PRESENCE
Russ Joyner 1 and Gary "ROD" Rodriguez 2
1) P&W
2) Systems Architect, sysRAND Corporation
Emerging industrial base and the consequent sustained manned Lunar presence will require
consistent high power capacities. This paper proposes a first iteration design of a flyable electric
power platform which could serve as an enabler of Lunar Development and Exploration. It is
intended to support a small facility solo or an emerging industrial base as part of a grid.
Lunar Missions, Habitats and Facilities stand to benefit from an expected decade of non-stop
operation, the economics of scale, Commercial Off-The-Shelf (COTS) availability,
standardization of design, and logistical support for Lunar encampments provided by this
architecture. The unattended and unmanned vehicle design is to be man- and robotics-serviceable
after delivery by current and proposed heavy-lift boosters. Design continuity within a family of
systems will improve reliability through "lessons learned" in the field.
Further, various configurations of the proposed scalable architecture will provide reference
platforms for the indigenous construction of similar power plant facilities from in-situ Lunar
resources (ISRU). The baseline design should be directed towards those materials available on
the Moon and expected to be manufacturable on-site within the first decade of operation.
Space Resources Roundtable VI 25
NEAR EARTH OBJECT CHARACTERIZATION, EXPLORATION
AND EXPLOITATION
Kurt Klaus
The Boeing Company, 13100 Space Center Blvd., Houston TX 77059
kurt.k.klaus@boeing.com
Introduction - The purpose of this paper is to outline how asteroid exploration can leverage
from Project Constellation technologies and the benefits to space exploration that can result from
exploiting asteroid resources. There are multiple reasons for exploring these bodies: 1) Little is
known about their characteristics to help us with mitigation strategies in the event of an impact
threat; 2) Many Near Earth Asteroids (NEAs) contain raw material and ore required for
manufacturing, fuel production and a basis for testing in situ resource utilization concepts
(consider the case of Iron/Nickel asteroids); 3) Asteroid exploration provides unique
opportunities to further expand the human/robotic interaction required for advanced exploration;
4) Some of these objects are relatively close especially when considering human missions to
Mars; 5) There is a great deal to be learned about the origin of the solar system and primordial
history of the planets through the study of asteroids; 6) Asteroid rendezvous missions are a
logical step in a spiral approach to human deep space missions.
Asteroid Resources - Resources expected to be abundant on some asteroids are water, iron,
nickel, platinum group metals, and organic compounds. Earth based observation for the
characterization and detection of NEAs as well as their resources potential could be amplified by
Lunar based observation.
Technology Requirements - The technology required for these types of missions are within the
bounds of the Exploration Initiative and Project Constellation. Some of the required technologies
would be: 1) A highly maneuverable, reusable, refuelable Crew Exploration Vehicle (CEV); 2)
Robotic Landers/Explorers; 3) Equipment to support mining operations (drilling equipment,
excavation, and processing equipment); 4) Advanced EVA; 5) Advanced power systems; 6)
Technologies that are part of Project Prometheus (nuclear power systems, RTGs, NEP, etc.); 7)
ISRU production systems; 8) Close proximity rendezvous, station keeping and operations.
Public Outreach - Human missions to NEAs would provide an excellent opportunity to capture
the public attention on deep space missions. The benefits and applications of humans and robots
producing fuel and refueling vehicles while in deep space must be clearly explained to the public.
Several NEAs should be targeted and evaluated for initial missions. Mission concepts should be
proposed and evaluated to drive out mission and system requirements. Early robotic missions to
resource rich NEAs could provide sample returns to validate the remotely sensed information.
Summary/Conclusion - NEAs offer an opportunity for short-duration, low delta v missions and
arc a logical step for human activities beyond low earth orbit (Chapman 1990). NEA resources,
like those of the Moon, begin to build an economic base for a sustained human presence in space.
Accessible targets such as these provide an opportunity to conduct in situ research as well as
provide a test bed for systems necessary for long duration missions.
Resources:
1 . The Future of Solar System Exploration, 2002-2013, ASP Conference Series, Vol. 272,
2002, Mark V. Sykes, editor, T.D. Jones et al, pages 141-15.
2. The New Solar System, J.K. Beatty and A. Chaikin, editors, Cambridge University Press,
1990, C. Chapman, pages 23 1-240.
26 LP1 Contribution No. 1224
MISSION DESIGN FOR ECONOMICALLY SELF-SUPPORTING
LARGE SCALE LUNAR TELEPRESENCE
G. A. Konesky
ATH Ventures, Inc., 3 Rolling Hill Rd., Hampton Bays, NY 1 1946, g.konesky@att.net
Telepresence provides the ability to sense and interact with a potentially hostile environment without the
difficulties of getting there, being there, and then returning. Given the limitations of the speed of light, the
Moon, which is approximately two and a half seconds round trip distant, is accessible to near-real time
telepresence. In addition to the obvious scientific motivations to further explore the surface of the Moon,
there is also substantial mass appeal among the general public to interact. The popular access of "live"
pictures over the internet from various Mars Rover missions exemplifies this and demonstrated a level of
internet activity that was (and still is) without precedent.
A mission design is presented to provide on-going large scale telepresence opportunities on the lunar
surface at various levels of interaction with an access fee structure to provide economic self-support. A
baseline study includes 10 rover vehicles, each carrying 50 independently controlled stereoscopic camera
heads, collectively supporting 500 simultaneous Earth-bound users. A Lander acts as an Earth relay link,
permitting the rovers to be relatively simple, light weight, and low cost. The Lander, which provides
terminal transport of the rover fleet to the lunar surface, can be relocated, expanding the exploration area.
The entire operation is solar powered and without consumables. Rover steering and camera pan and tilt
commands are up linked from Earth-bound users over a relatively low bandwidth RF to the Lander, and
relayed to the rover fleet. Stereoscopic camera feeds from the 50 camera heads on each rover are relayed
to the Lander, which combines them with those of the other rovers, and down links them to the Earth over
a high bandwidth optical data link. A one watt Laser (820 nm) on the Moon, transmitted through a one
meter telescope, and received on the Earth by a similar sized telescope, results in a positive link margin.
Levels of telepresence are organized into a hierarchy of interaction, with associated access fees. Remote
steering command of a given rover represents the highest level, with the highest associated access fee.
Prior "driver's education" and demonstration of proficiency on a simulator are needed. A remote co-pilot
monitors actual lunar navigation, and may intervene to prevent potentially disastrous maneuvers. Areas of
historic importance on the Moon must be treated with respect, and we must be careful not to run over Neil
Armstrong's footprints. The next level of telepresence interaction involves active viewing where an
Earth-bound user can direct the pan and tilt of a given stereoscopic camera head on a given rover to
visually explore the surrounding lunar landscape. The lowest level of telepresence is the passive user,
where the user simply goes along for the ride, looking wherever the active viewer (or driver) has chosen.
An essentially unlimited number of users can share a given camera feed, or hop among the 500 channels.
Operational availability, due to the solar powered nature of this mission, occurs for at most 14 Earth days
every synodic month, and low sun angle limits this to perhaps 12 working days. 13 synodic months per
year yields 156 working Earth days and since a lunar day is in continuous sunlight 24 hours per Earth
day, there are 3744 working hours per year. If we partition user access into 15 minute time slices then
there are 14,976 15 minute time slices per year per active channel from the Moon. An example of an
access fee structure is that drivers are charged $100, active viewers $10, and passive viewers $1 per 15
minute time slice. A 10 vehicle fleet with 500 viewer channels will receive about $15 million from driver
revenue, and almost $75 million from active viewers. If there are 10 passive viewers per active viewer, an
additional roughly $75 million is added. If there are 100, this number is closer to $750 million. Additional
income may derive from cable access television ("The Moon Channel"), theme park sites, and so on.
In conclusion, this proposed mission design provides near-real time telepresence exploration to a large
number of simultaneous users, with an access fee structure to make it economically self-supporting. An
additional and perhaps greater benefit in personal access to space and the surface of another world is the
enhanced desire to significantly expand human presence there. Need a 1 5 minute break? Why not spend it
on the Moon?
Space Resources Roundtable VI 27
TUMBLEWEED: A NEW PARADIGM FOR SURVEYING THE SURFACE
OF MARS FOR IN-SITU RESOURCES
K. R. Kuhlman 1 , A. E. Behar 1 , J. A. Jones 1 , F. Carsey 1 , G. A. Hajos 2 , J. J. Flick 2 and J. Antol 2 'Jet Propul-
sion Laboratory, California Institute of Technology, 4800 Oak Grove Dr., Pasadena, CA 91109 USA,
kkulilman@jpl.nasa.gov, 2 NASA Langley Research Center, Hampton, VA 23681-2199 USA.
Introduction: Inflatable and rigid Tumble-
weeds are wind-propelled long-range vehicles
based on well-developed and field tested tech-
nology (Figure 1 and Figure 2) [1,2]. Different
Tumbleweed configurations can provide the ca-
pability to operate in varying terrains and ac-
commodate a wide range of instrument packages
making them suitable for autonomous surveys
for in-situ natural resources. Tumbleweeds are
lightweight and relatively inexpensive, making
them very attractive for multiple deployments or
piggy-backing on larger missions. Modeling
and testing have shown that a 6 meter diameter
Tumbleweed is capable of climbing 25° hills,
traveling over 1 meter diameter boulders, and
ranging over a thousand kilometers. Tumble-
weeds have a potential payload capability of
about 10 kg with approximately 10-20W of
power. Stopping for measurements can be ac-
complished using partial deflation or other
braking mechanisms (Figure 1).
Surveys for In-situ Resources: Tumble-
weeds are capable of performing autonomous
long-duration surveys over large areas on Mars.
The presence of liquid water, for example, can
potentially be mapped as a function of depth
using simple low mass and low power instru-
ments and an onboard positioning system.
During recent field-testing of the inflatable
Tumbleweed, data was relayed back to JPL via
an Iridium modem. Many of the desired instru-
ments for resource discovery are currently under
development for in-situ applications, but have
not yet been miniaturized to the point where
they can be integrated into Tumbleweed. It is
anticipated that within a few years, instruments
such as gas chromatograph mass spectrometers
(GC-MS) and ground-penetrating radar (GPR)
will be deployable on Tumbleweed.
Acknowledgements: This work was carried
out at the Jet Propulsion Laboratory, California
Institute of Technology, under a contract with
the National Aeronautics and Space Administra-
tion and at the NASA Langley Research Center.
7 — Wass y/ u
T* — "TV: '". ?:■ :■ : ;■■■:■ ■■;
~ ■■ : "::■ .".-■-■:■;.■:;.. .
Figurel. Inflatable Tumbleweeds can be
stopped by partially deflating the ball and pull-
ing on one of the central payload tension cords
to create a "turtle effect."
Figure 2. NASA Langley Research Center rigid
Tumbleweed concept [2].
References: [1] Behar, A., F. Carsey, J.
Matthews, et al. (2004) IEEE Aerospace Con-
ference, Big Sky, Montana. [2] Carsey, F., P. J.
Boston, L. J. Rothschild, et al. (2004) "Tumble-
weed: Wind Driven Sampling on the Surface of
Mars," Inter. J. ofAstrobiology, (SI) 85-86.
28 LPI Contribution No. 1224
SIMULATION OF HELIUM-3 EXTRACTION FROM LUNAR ILMENITE
K.R. Kuhlman 1 '* G.L. Kulcinski 1 and H.H. Schmitt 1 , 'Fusion Technology Institute, University of Wiscon-
sin, Madison, WI 53705, 'Currently at the Jet Propulsion Laboratory, California Institute of Technology,
4800 Oak Grove Dr., Pasadena, CA 91 109 USA, kkuhlman@jpl.nasa.gov
Introduction: Knowledge of the trapping
mechanisms and diffusion characteristics of solar-
wind implanted isotopes in the minerals of the lu-
nar regolith will enable the optimization of the
processes to extract solar wind gases from regolith
particles. Extraction parameters include the tem-
perature and duration of extraction, particle size,
and gas yield [1]. Diffusion data will increase the
efficiency and profitability of future mining ven-
tures. This data will also assist in optimizing the
evaluations of various potential mining sites based
on remote sensing data. For instance, if magne-
sian ilmenite (Mg x Fe!. x Ti0 3 ) is found to retain He
better than stoichiometric ilmenite (FeTi0 3 ), re-
mote sensing data for Mg could be considered in
addition to Ti and maturity data.
The context of the currently discussed work is
the mining of helium-3 for potential use as a fuel
for fusion energy generation [e.g. 2]. However,
the potential resources deposited by the solar wind
include hydrogen (and derived water), helium-4,
nitrogen and carbon. Implantation experiments
such as those performed for helium isotopes in
ilmenite are important for the optimized extraction
of these additional resources. These experiments
can easily be reproduced for most elements or
isotopes of interest.
Helium-3 Implantations of Ilmenite: Helium
isotopes were implanted into terrestrial ilmenite
using plasma source ion implantation (PSII), a
non-line of sight technique developed for uni-
formly implanting a variety of atoms orthogonally
into materials [3]. It is very conducive to simula-
tion of solar wind implantation because implanta-
tion energies of 1 keV/amu are easily achieved.
The target — in this case a silicon wafer with thin
polished samples of terrestrial ilmenite lying on
top - is placed in a 1 m 3 chamber which is evacu-
ated to a base pressure of about 10" 6 torr. Helium-
4 and helium-3 gas is allowed to flow through the
chamber at a pressure of several millitorr. A
plasma is generated using tungsten filaments to
ionize the gas by energetic primary electron im-
pact. The evolution of helium isotopes from the
implanted samples was performed using isochro-
nal and isothermal annealing similar to the ex-
periments performed on the Apollo samples. The
measured release profiles were found to be quite
similar to the release profiles measured for rego-
lith samples from the Apollo 1 1 site [4].
Reconnaissance of Lunar Solar-wind Re-
sources: Since remote sensing of helium-3 has
been shown to be impossible without an added
source of protons or neutrons [5], helium-3 con-
centrations are currently associated with titanium
concentrations and maturity indices measured by
remote sensing. We propose that in-situ mapping
of lunar helium-3 concentrations or other species
. of interest is possible using well-developed bore-
hole neutron or proton sources in concert with
gamma-ray detectors. Such instruments should be
considered for in-situ discovery of in-situ re-
sources on both the Moon and on Mars.
Acknowledgements: This work was carried
out in the Fusion Technology Institute (FTI) at the
University of Wisconsin — Madison. Funding was
generously provided by the Wisconsin Space
Grant Consortium, NASA Johnson Space Center
and the Graduate School of the University of Wis-
consin. Special thanks to R.O. Pepin, University
of Minnesota for performing the measurements of
helium release.
References: [1] Kulcinski, G.L, et al. (1988)
The Second Conference on Lunar Bases and Space
Activities of the 21st Century, (Houston, Texas:
Lunar and Planetary Institute), 459-74; [2]
Schmitt, H.H. (2003) Adv. Space Res. 31(11)
2441-2447; [3] Conrad, J. et al. (1990) J. Vac. Sci.
Tech. A, 8, 3146; [4] Harris-Kuhlman, K.R. (1998)
Ph.D. Thesis, University of Wisconsin - Madison.;
[5] Harris, K.R., H.Y. Khater, and G.L. Kulcinski
(1994) Proc. of the 4th International Conference
on Engineering, Construction, and Operations in
Space, R.G. Galloway and S. Lokaj, eds. (ASCE
Albuquerque, New Mexico) 1, 648-657.
Space Resources Roundtable VI 29
MARS DEEP DRILLING REMAINS A HIGH PRIORITY
Humboldt C. Mandell
mandell@csr.utexas.edu
THE UNIVERSITY OF TEXAS CENTER FOR SPACE RESEARCH
In 1992, The University of Texas Center for Space Research (CSR) submitted a proposal to the
NASA Scout Program to drill a "deep" well on Mars. The proposal was unsuccessful. However,
the mission remains viable, and can still be accomplished for a very low cost.
The science of this mission remains of utmost interest to the science community, and no deep
drilling mission is scheduled currently. Deep drilling is the only way to verify the character of
the Martian subsurface, particularly to characterize any water to be found there, and eventually to
explore for liquid water.
During the preparation of the Scout proposal, a very strong team was forged, and several of the
team members, including NASA Centers, have expressed a strong interest in pursuing this
mission in the near future.
In its existing programs (GRACE, ICESAT, others), CSR has developed strong international ties,
particularly with Germany. The GRACE partnership resulted in a sharing of mission expenses
between the two countries. This type of partnership remains very viable for a Mars Deep Drilling
Mission.
Baker Hughes, Inc., and the NASA Johnson Space Center have built and tested a prototype Mars
deep drill, so the technology risk has been greatly reduced.
All of these factors come together to suggest that a very low cost, low risk mission can be
proposed to NASA, either in response to a future Scout mission call, or as an independent
international mission.
30 LPI Contribution No. 1224
SELENE SCIENTIFIC DATA PRODUCTS
AND THEIR APPLICATION TO CHARACTERIZATION
OF LUNAR POTENTIAL RESOURCES
K. Matsui, R. Nakamura, M.Kato and Y. Takizawa
Japan Aerospace Exploration Agency
2-1-1, Sengen, Tsukuba-shi, Ibaraki, 305-8505 JAPAN
matsui.kai@jaxa.jp
SELenogical ENgineering Explorer (SELENE) is a Japanese mission to investigate the origin and
evolution of the moon. The 14 scientific instruments will provide massive datasets of great
importance not only for science but also for future utilization of the moon. For example, we can
completely map the permanently shadowed/illuminated areas around the poles. The terrain camera
(TC) can monitor the seasonal variation of the illumination conditions during the SELENE mission
period of one year, while Clementine/UVVIS covered only two months. With the high energy
resolution, the gamma-ray spectrometer (GRS) will identify the hydrogen emission line if water ice
exists in the permanently shadowed areas. TC and the Laser ALTimeter (LALT) will measure the
surface topography with the high spatial resolution and accuracy. The global element distribution
can be determined by the GRS and X-ray fluorescence spectrometer (XRS). Spectral Profiler (SP)
and Multi-band Imager (MI) reveal the mineralogy of lunar surface in detail. In this presentation,
we describe the SELENE datasets and discuss their vital role in characterizing the potential
resources on the moon.
Space Resources Roundtable VI 31
THE IDENTIFICATION OF GAS HYDRATE RESOURCES ON MARS:
IMPLICATIONS FOR HUMAN EXPLORATION AND LONG-TERM
HABITATION
M.D. Max 1 and S. Clifford 2
'Marine Desalination Systems, L.L.C. 1601 3 rd St. South, St. Petersburg, FL 33701,
mmax@mdswater.com, 2 Lunar and Planetary Institute, 3600 Bay Area Blvd., Houston TX 77058,
clifford@lpi.usra.edu.
Terrestrial experience, and the recent discovery of trace amounts of methane in the Martian
atmosphere that is almost certainly leaking from subsurface Mars, suggests that Mars may be rich in a
primary natural resource that could aid future human exploration and long-term habitation. This resource
would be methane hydrate. Deposits similar to those found on Earth may provide potable water for
drinking, agriculture and oxygen, fuel for return trips and outward exploration as well as local power, and
industrial feedstock for manufacturing plastic products such as building, vehicle, and utility components.
In Earth's permafrost regions, methane hydrate and water ice form a compound cryogenic zone
whose extent is determined by the local surface temperature, geothermal gradient, and increasing pressure
that occurs with depth. The region of the crust that satisfies these criteria is called the Hydrate Stability
Zone (HSZ). Water ice is stable from the surface down to about zero degrees C whereas methane hydrate
on Mars may be found at depths ranging from several tens of meters to as much as a km below the base of
the local Martian cryosphere. Hydrate can be formed anywhere in the HSZ and high methane (or other
hydrocarbon gas) fluxes can cause water-ice to recrystallize to hydrate. Relatively near-surface hydrate
accumulations could also have been caused as downward propagation of the freezing-front at the base of
the prograding cryosphere during the original freeze-up of Mars had the potential to have incorporated
subsurface methane as hydrate — in concentrations that may range from a dispersed, low grade diagenetic
mineralization, to high grade deposits formed by focused flow of methane. The extent to which the HSZ
is occupied by hydrate is unclear but on Earth, shallow permafrost hydrate in commercial concentrations
has been tested, and may have been extracted for some years from Russian (West Siberian) deposits.
Because the lifetime of atmospheric methane is so short, its recent detection on Mars is generally
attributed to leakage from a subsurface methanogenic biosphere although volcanic emissions from
igneous fractionation could also be a source. Regardless of the source, if significant methane is being
produced at depth on Mars, it is almost inescapable that much of it would be sequestered in the form of
hydrate deposits in the cryosphere in a manner similar to that which occurs in permafrost regions on Earth
Identification of methane hydrate resources is vital. Exploration for subsurface hydrate on Mars
can be accomplished by adapting remote sensing techniques such as seismic analysis that are currently
employed on Earth. For the final phase of resource evaluation, development of remote, autonomous
drilling capability will be necessary (autonomous Earth seafloor drilling capability already exists). In
addition, lightweight, rapid prototyping, plastics fabrication apparatus that could be sent to Mars with
early human explorers will allow a variety of life and expedition-sustaining items to be fabricated on
Mars. Gas to liquid fuel fabrication apparatus will allow the natural gas to be converted to higher energy
density liquid fuels for use in chemical rockets, vehicles or other local uses. In other words, a wide
variety of portable industrial capability will have to be developed that can be brought to Mars to support
human exploration and colonization that will utilize the subsurface methane hydrate (and C0 2 ) resources.
Max, M.D. (ed). 2003. Natural Gas Hydrate: In Oceanic and Permafrost environments (2nd Edition).
Kluwer Academic Publishers, London, Boston, Dordrecht, 422pp.
Max, M.D. & Clifford, S. 2000. The state, potential distribution, and biological implications of
methane in the Martian crust. Journal of Geophysical Research-Planets, 105/E2, 4165-4171.
Pellenbarg, R.E., Max, M.D. & Clifford, S.M. 2003. Methane and carbon dioxide hydrates on Mars:
Potential origins, distribution, detection and implications for future in-situ resource utilization.
Journal of Geophysical Research-Planets, 108/E4, DOI 10.1029/2002JE001901.
32 LPI Contribution No. 1224
MICRO-STRUCTURED HEAT EXCHANGERS AND REACTORS
FOR ISRU AND ENERGY CONVERSION
A. McCandless 1 , S. Motakef 2 , D. Guidry 1 , andM. Overholt 2
1) International Mezzo Technologies, Baton Rouge, LA 70803
mccandless@mezzotech.net, guidry@mezzotech.net
2) Cape Simulations, Natick, MA 01760
motakef@capesim.com, overholt@capesim.com
A large fraction of technologies for in-situ resource utilization on the Moon and Mars
involves high temperature processes and catalytic reactions. Conversion of energy from
a chemical source is also an important element in both space travel as well as
establishment of human habitat in space. Heat exchangers and catalytic reactors with
micro-scaled features can provide significant weight and volume reductions compared to
currently available systems. We report on development of micro-machined thermal and
chemical devices that have surface features of the order of 100's of microns, over areas
of the order of 10's to 100's of cm. These devices are fabricated by the LIGA technique,
which utilizes x-ray lithography and electroplating to form micro-structures with aspect
ratios in the range of 1:10. These micro-structured surfaces provide significant
enhancement to heat and mass transfer, and thus allow for miniaturization of thermo-
chemical devices.
A number of thermo-chemical devices suitable for ISRU and energy conversion will be
introduced. We will report on the performance of micro-machined cross-flow heat
exchangers with a performance to volume ratio which is 10 times higher than the best
heat exchanger currently available. We will also report on the development and
performance of a novel cooling device based on micro jet cooling arrays (MJCA). MJCA
consists of arrays of 200-400 micron jets created in three dimensional structures that
allows localized removal of coolant immediately after contact with the target surface.
These devices provide extremely high heat transfer coefficients over large areas.
Progress in development of micro-machined ceramic devices suitable for high
temperature heat exchangers and catalytic combustors will be discussed. Micro-
machined ceramic substrates which can be sealed to form leakage-free fluid conduits are
currently under construction. These structures will open the door to miniaturization of a
large number of high temperature applications, ranging from integrated catalytic
combustor and heat exchanger to intimately coupled endo- and exo-thermic reactive gas
streams. We will report on prototype devices under fabrication, and demonstrate a
number of key enabling technologies in this area.
Space Resources Roundtable VI 33
ROCKS TO ROBOTS:
A BIOLOGICAL GROWTH APPROACH TO RAPID LUNAR
INDUSTRIALIZATION
OR
HOW TO REALIZE VON NEUMANN'S VISION
L. M. E. Morin
Deputy Assistant Secretary for Health, Space, and Science
United States Department of State, Washington, DC
morinlm@state. gov
We propose a strategy for rapidly attaining and maximizing lunar industrial capability.
Consider a series of 1000 kg EELV (Evolved Expendable Launch Vehicle) lunar payloads.
These payloads bring the following technologies: Telepresence robotics for mining and material
manipulation, ISRU (In Situ Resource Utilization) production of solar electric power, solar
furnaces for fusion of regolith ceramics, and electrolytic reduction of metals from regolith.
Using telepresence, regolith is mined on a kilogram scale for ISRU. Telepresence-operated ISRU
apparatus immediately produces metals and ceramics, also on kilogram scales. Metals,
particularly iron, are shaped using casting, powder metallurgy, and light machining methods. This
produces a versatile kit of assorted stock mechanical components. These lunar kits, together with
required earth-based components, are assembled by telepresence to generate additional mining
and fabrication equipment, as well as more telepresence robots.
Re-supply missions provide critical earth-based ingredients, such as miniature cameras, computer
controllers, reagents for thin-film solar cell production, electrodes, forming dies, and tool bits.
However, the overall proportion of earth-based content is reduced as rapidly as possible by
several strategies. Designs maximize use of lunar iron, the first metal that will be produced.
Simple mechanical devices, built with lunar materials using methods at hand, are favored over
more sophisticated earth-based technologies. As mining operations are scaled up, more elements
and minerals become available, which provides more options to eliminate earth-based content.
Accumulating know-how also yields new methods of substituting lunar for earth-based content.
The key element of this approach is the geometric, or biological, growth rates that are possible.
Consider this illustration: If the initial 1000 kg ISRU package produces an average of 0.1-0.2 kg
of apparatus per hour, the mass doubles in one year. At this point, the production rate has also
doubled since more production apparatus has been built. At the end of ten years, the cumulative
apparatus is a million kilograms, capable of producing 100 kilograms of apparatus per hour. This
is the power of the force Einstein called the most powerful in the Universe - compound interest.
We view extensive telepresence as essential. Abundant, tool-wielding robotic telepresence
permits the flexibility to rapidly realize the pragmatic solutions needed for this pioneering
enterprise, and to assemble, operate and maintain all the required apparatus.
The advantage of beginning ISRU immediately on a kilogram scale is that spacecraft required to
deliver 1000 kg are available now, and are affordable. Using "biological" growth, we can start
small and "grow" the millions of kilograms of industrial capability we need in situ. This
capability will otherwise wait decades or longer for the required heavy lift to materialize.
34 LPI Contribution No. 1224
SOLAR ENERGY UTILIZATION FOR IN-SITU RESOURCE
UTILIZATION
T. Nakamura
Physical Sciences Inc.
2110 Omega Rd. Suite D. San Ramon CA 94583
nakamura@psicorp.com
Physical Sciences Inc. (PSI) has been developing the Optical Waveguide (OW) system
for solar energy utilization. In this system, solar radiation is collected by the concentrator which
transfers the concentrated solar radiation to the OW transmission line. The OW transmission line
transports the solar radiation to the location of solar energy utilization. Applications of this
system include: material processing, plant lighting and power generation in space.
Since 1988, the author and his colleague have been working on development of the
Optical Waveguide (OW) Solar Power System with funding from Air Force Astronautics
Laboratory. The work undertaken in this program includes theoretical and experimental
investigation of key components of the OW system, and conceptual design, performance analysis
and survivability evaluation of the OW Solar Power. Subsequently, Physical Sciences Inc. (PSI)
has been developing the OW System for utilization of solar energy in space as well as on the
ground.
The first embodiment of the OW system discussed above was implemented for lunar
material processing with funding from NASA/JSC (SBIR Phase I and II). In this program, we
developed an engineering prototype of the solar energy system for thermochemical reduction of
lunar oxide. The product oxygen is to be used as a propellant for space transportation. Figure 1
shows a photo of the ground test model of the OW solar energy system developed in this
program. The system consists of three major components: the concentrator, the solar power
transmission line, and the thermal reactor.
FIGURE 1. The Ground Test Model of the OW Solar Energy System.
In this presentation, a review of our work conducted during the last 10 years for in-situ
resource utilization, plant growing and power generation in space is presented.
Space Resources Roundtable VI 35
LESSONS FROM EARTH:
EXPERIENCES WHICH CAN GUIDE
LUNAR AND ASTEROIDAL DEVELOPMENT
CD. O'Dale
Senomix Software Inc.
64 Fairfax Drive, Suite 501
Halifax, Nova Scotia, Canada, B3S 1N5
charles.odale[a-t]senomix.com
Although space-based projects face unique technical challenges, they will encounter many of the
same regulatory, logistical and financial issues which other large-scale enterprises have been
presented with in the past. Given this commonality, it is possible many of the same solutions
engineered for issues confronted on Earth may be applied to the challenges faced in space as well.
This paper will examine the successes of a few key technologies, social policies and business
frameworks of the past century and consider what lessons may be learned from those examples to
assist public and private sector projects involving the Moon, Mars and Near Earth Asteroids.
These examples will include:
the development of global infrastructure for the Liquid Natural Gas industry;
the increased effectiveness of asset use due to land title reform;
the objective of resource claims for assets extracted from public land;
asset distribution to citizens through the Alaska Permanent Fund Dividend Program; and
the regulatory environment behind the rapid emergence of 802. lib / Wi-Fi technology.
By looking to these past projects and social frameworks for examples of success in their
respective fields of endeavour, the Space Resources Roundtable may assist national space
agencies and emerging private sector enterprises by proposing policies and frameworks which
draw upon the best of this industrial experience. Actions which may be taken within the scope of
the SRR's activities over the next year to assist this goal will be proposed as part of this paper's
conclusions.
36 LPI Contribution No. 1224
SILVER: SURFACE IMAGING FOR LUNAR
VOLATILES, RESOURCES, AND EXPLORATION
R. T. Pappalardo (LASP, University of Colorado, Boulder, CO 80309-0392;
robert_jpappalardo@colorado.edu); E. Cobabe-Ammann (LASP, University of Colorado);
A. C. Cook (University of Nottingham, UK); R. Greeley (Arizona State University);
V. C. Gulick (SETI/Ames); W. E. McClintock (LASP, University of Colorado); J. M. Moore (Ames);
S. A. Stem (Southwest Research Institute); A. R. Vasavada (Caltech/Jet Propulsion Laboratory);
M. McClelland (Southwest Research Institute); and J. Westfall (LASP, University of Colorado).
The Surface Imaging for Lunar Volatiles, Exploration, and Resources (SILVER) instrument is a
proposed imaging investigation for the 2008 Lunar Reconnaissance Orbiter (LRO) mission. SILVER and
its experienced Measurement Team will prepare for and support future lunar human exploration activities,
especially landing site identification and certification on the basis of potential resources.
SILVER combines a high-resolution pushbroom visible imaging channel (SILVER-HR) and a wide-
field-of-view (45°) framing imaging channel (SILVER- WF). SILVER-HR will obtain a single-detector 6
km imaging swath of 12,228 pixels at 0.5 m/pixel to image >100 km 2 target areas from 50 km altitude,
imaging >15% the lunar surface during a 1 year nominal mission. SILVER-HR has excellent stray-light
rejection and its imaging detector has selectable time delay integration (TDI) with up to 128 stages for
extreme low-light sensitivity, permitting direct imaging of permanently shadowed polar regions in
scattered sunlight or earthshine. SILVER- WF will obtain geodetic framing images in a 2048 x 2048
format at 20 m/pixel, with 60% along-track overlap stereo for imaging context and for derivation of a
global digital elevation model of meter-scale lunar topography.
SILVER addresses 5 of the 8 Measurement Investigations for the Lunar Reconnaissance Orbiter
(LRO: (1) Assessment of submeter-scale features to facilitate safety analysis for potential lunar landing
sites; (2) Geodetic lunar global topography; (3) Landform-scale imaging of lunar surfaces in
permanently shadowed regions; (4) Identification of putative deposits of near-surface water ice in the
Moon's polar cold traps; and (5) Characterization of the Moon's polar region illumination environment at
relevant temporal scales.
The SILVER investigation combines the experience and heritage of the University of Colorado's
Laboratory for Atmospheric and Space Physics (LASP) with that of the Southwest Research Institute
(SwRI) to build a superb imaging investigation optimized to the exploration objectives of the Lunar
Reconnaissance Orbiter mission and the Lunar Exploration Program. The SILVER Operations Facility,
which partners with Applied Coherent Technologies (ACT), will be co-located with the primary
instrument builder and the Principal Investigator at LASP. Moreover, SILVER utilizes the experience
and heritage of the Exploratory Computing Environments group at Ames Research Center — producers of
the landing site selection planning products for the Mars Exploration Rovers— to create and distribute
high-level data products that enable planning for future landed missions of the Lunar Exploration
Program, addressing the goals of NASA's Exploration Vision.
The SILVER team includes an Apollo- Veteran Advisory Committer, cementing ties to the experience
of humanity's previous lunar field expeditions. Its members are: M. Duke (Colorado School of Mines);
N. Hinners (LASP and Lockheed Martin, retired); H. Schmidt (Apollo 17 astronaut and University of
Wisconsin); G. J. Taylor (University of Hawaii); and D. Wilhelms (U.S. Geological Survey, retired).
SILVER'S Education and Public Outreach (E/PO) program will develop a deep understanding of lunar
geology and geography in the context of Earth's geology and history with a focus on topography,
mapping and remote sensing. The E/PO program will create curricular enhancements, including 3-D
visualizations, and will engage Explorer Schools and Colorado MESA after school programs in a year-
long set of lessons and activities, culminating in a contest for choosing a lunar landing site. LASP leads
these E/PO efforts in conjunction with the SILVER Measurement Team, NASA Explorer Schools,
Colorado MESA Program, NASA Ames and RMC Research Corporation.
Space Resources Roundtable VI 37
EXPLORATION OF THE IMPACT OF ISRU ON
ARCHITECTURAL SYSTEM MASS AND COST
Dr. C. M. Reynerson
The Boeing Company
5316 Desert Mountain CT, Boulder, CO 80301
creyners@alum.mit.edu
This paper addresses a concept-level model that produces technical design parameters
and economic feasibility information addressing future Human Exploration platforms. A design
methodology and analytical tool is used to create feasible concept design information for these
space platforms at the architectural level. The design tool has been validated against a number of
actual facility designs, and appropriate modal variables are adjusted to ensure that statistical
approximations are valid for subsequent analyses. The tool is then employed in the examination
of the impact of various payloads on the power, size (volume), and mass of the platform
proposed.
The development of the analytical tool employed an approach that accommodated
possible payloads characterized as simplified parameters such as power, weight, volume, crew
size, and endurance. In creating the approach, basic principles are employed and combined with
parametric estimates as necessary. Key system parameters are identified in conjunction with
overall system design. Typical ranges for these key parameters are provided based on empirical
data extracted from actual human spaceflight systems.
Using this tool a sample Exploration architecture is formulated with emphasis on cost
minimization through variance of key mission requirements. Further, the use of ISRU (In Situ
Resource Utilization) is considered to minimize the consumables needed for transport from Earth.
A baseline architecture is compared to one that uses ISRU and the impact on system mass and
cost is determined.
This paper is based on work Dr. Reynerson completed at George Washington University
in fulfillment for the degree of Doctor of Science in Astronautics. Dr. Mike Griffin, former head
of NASA's Human Mars Mission, was a member of the dissertation committee.
Summary Biography for Dr. Charles Martin Reynerson
Associate Technical Fellow, The Boeing Company, Boulder, Colorado. Dr. Reynerson received
his Doctorate of Science in Astronautics from the George Washington University, Engineers
degree (between MS and D.Sc.) in Aeronautics and Astronautics (EEA) from MIT, Engineers
(NE) degree in Naval Engineering from MIT, and BS from U.C. Berkley. He has extensive
experience in the development of space systems with NASA where he was the Assistant Deputy
for Space Shuttle Integration, National Reconnaissance Office (NRO) Liaison for Space
Technology Programs, and Project Manager and Contracting Officer's Technical Representative
at the National Reconnaissance Office. He is an ex-Naval Engineering Duty Officer also
qualified in submarines. Dr. Reynerson is member of AIAA, AAS, and Tau Beta Pi (National
Engineering Honor Society). Dr. Reynerson is also a licensed private pilot.
38 LPI Contribution No. 1224
LUNAR AND MARTIAN FIBERGLASS AS A VERSATILE FAMILY
OF ISRU VALUE-ADDED PRODUCTS
Gary "ROD" Rodriguez, Systems Architect, sysRAND Corporation
Lunar Regolith consists principally of silicates, in some cases as volcanic or impact glasses. We
continue to contend that silicon is more versatile in application than all of the other Lunar-
available elements combined and shouldn't end up in Lunar slag-heaps and instead should be the
fundamental building block for a wide range of value-added products in a CisLunar economy.
Fabrication of silicate glasses are conventional industrial processes and anticipated tensile
strength of glass made under hard vacuum is an order of magnitude greater than glass produced in
atmosphere containing water vapor.
The logic employed in our reasoning includes the fact that any In Situ Resource Utilization
(ISRU) effort is going to yield copious masses of silicon oxides which can be used in bulk as
conventional glass products or, after further separation, can be synthesized as Silicon and Silicon-
Carbide Fullerenes for more exotic applications. Additionally, mechanical wrapping of Silicon
Webbing could prove to be more practical and durable and a lot less brittle than attempting large-
scale hot glass molding of structural components.
Identified fuel production ISRU efforts yield partially heated masses of metal oxides as waste
byproduct - rich in silicates and metal oxides useful in bulk as conventional glass products.
Fiberglass manufacturing increases effectiveness of prior ISRU fuel production by taking
advantage of mineral benefaction and elevated process exit temperatures. The resulting structures
would be spheres and cylinders with various configurations that could apply to human support
systems, along with structures useable as storage tanks for the very Oxygen liberated in ISRU
applications.
ISRU can manufacture more than fuels: even spacecraft are feasibly and affordably manufactured
on Moon based upon fiberglass "tankage" integrated with fiberglass keels. Second-generation
structural components may take advantage of Silicon Nanotubes for additional composite
strength. Diverse products for human systems support are manufactureable in-situ using glass
fibers and fabrics, and CNC-type programmable manufacturing delivering state-of-the-art
flexibility of remote design and parts manufacture. These concepts suggest extensibility and
evolutionary capability derived when machining tool parts from fiberglass.
Contemporary Terrestrial industrial composite fiber products range from pressure vessels to
lightweight sporting goods. A large number of products related to human systems support can
similarly be manufactured in-situ using fiber fabric made from lunar silicate glass. Building
structures using spun glass would be similar to those currently employed by Raytheon Aircraft or
Scaled Composites to build composite aircraft. Pressure containers, structural components,
woven fiberglass fabrics, molded and machined solid objects, glass fiber and filament are each
large classes of value-added products.
Space Resources Roundtable VI 39
TELEPOSSESSION TRANSFORMS ASTEROIDS INTO
RESOURCES
Gary "ROD" Rodriguez, Systems Architect, .sysRAND Corporation
A deep-space probe with integral RADAR transponders should be a sufficient improvement to a
space rock to qualify as a resource mining claim. Such a legal device would allow Aldrin (Earth-
Mars) Cycler Orbiters to develop the asteroids, widely viewed as a menace to Earth, into valued
resources. Technologies and Capabilities are outlined to encourage new legal conversations.
40 LPI Contribution No. 1224
POWER LANDER FOR SUPPORT OF LONG-TERM LUNAR
PRESENCE
Russ Joyner 1 and Gary "ROD" Rodriguez 2
1) P&W
2) Systems Architect, .rysRAND Corporation
Emerging industrial base and the consequent sustained manned Lunar presence will require
consistent high power capacities. This paper proposes a first iteration design of a flyable electric
power platform which could serve as an enabler of Lunar Development and Exploration. It is
intended to support a small facility solo or an emerging industrial base as part of a grid.
Lunar Missions, Habitats and Facilities stand to benefit from an expected decade of non-stop
operation, the economics of scale, Commercial Off-The-Shelf (COTS) availability,
standardization of design, and logistical support for Lunar encampments provided by this
architecture. The unattended and unmanned vehicle design is to be man- and robotics-serviceable
after delivery by current and proposed heavy-lift boosters. Design continuity within a family of
systems will improve reliability through "lessons learned" in the field.
Further, various configurations of the proposed scalable architecture will provide reference
platforms for the indigenous construction of similar power plant facilities from in-situ Lunar
resources (ISRU). The baseline design should be directed towards those materials available on
the Moon and expected to be manufacturable on-site within the first decade of operation.
Space Resources Roundtable VI 41
INTELLIGENT EXCAVATION FOR THE MOON
Schissler, A.
Kecojevic, V.
Pennsylvania State University
Hosier Building
University Park, PA 16802
Andrews@eee.psu.edu, vuk2@psu.edu
Intelligent Excavation (IE) is an emerging technology on earth. This technology is being utilized
by Fortune 200 mining companies. IE has application to the intensified NASA objective of space
exploration. Mining on the moon will require precise spatial reference of mineralization, as
identified by evasive and remote sensing exploration methodologies. During the actual extraction
process, mining and haulage machines will also require real-time spatial reference, and remote
mineral inventory management. Existing mining information technology in the form of IE offers
adaptability to geo-base moon requirements. Researching existing earth-based Intelligent
Excavation system capacity and accuracy for alteration for mining on the moon offers promise.
Such a program meets NASA's Technology Readiness Levels 1-5. These readiness levels have
as a benchmark; ground truth earth-based evaluation and synthesis into space environments. IE
technology is available to meet this in-process research protocol. The benefit of IE to the
extraction process is a reduction in cost per unit mined.
42 LPI Contribution No. 1224
SOLAR WIND HELIUM CONCENTRATIONS IN UNDISTURBED
LUNAR REGOLITH
H. H. Schmitt
University of Wisconsin-Madison, P.O. Box 90730, Albuquerque, NM 87199, schmitt@engr.wisc.edu
Considerations of the geology of helium in the lunar regolith strongly indicate that agitation of regolith
samples before laboratory analysis has caused the loss of solar wind volatiles. For example, the
undisturbed concentration of Apollo 1 1 helium-3 subject to recovery through mining and processing
of titanium-rich areas of Mare Tranquillitatis is significantly higher than the 1 1.8 wppb average
measured for samples of Apollo 1 1 fines. A similar conclusion appears to hold for solar wind helium-
4 and hydrogen.
A review of analyses of samples of Apollo 1 land other regolith fines as a function of grain-size
fraction offer insights into the concentrations of volatiles in undisturbed regolith. For example, the
finest size fraction, <20 urn, of 10084,18 show the helium-3 and helium-4 concentrations 27-35% and
19-39% greater, respectively, than the sample as a whole. (1) In the analysis of 10084,47 grain sizes
less than 1.4 urn, the concentrations reach 221 wppm and 71 wppb, respectively.(2) Similarly,
analysis of 10087,8 grain sizes less than 5 urn, shows the concentrations are 76.1 wppm and 20.1
wppb, respectively.(3) These results almost certainly reflect the increase in total surface area with
decreased grain size fraction. On the other hand, helium-3 and helium-4 concentrations in 10084
reach minimums at about 150 um that are respectively 78-83% and 77-84% lower than in the <20 urn
fraction. Concentrations then increase in the coarser factions suggesting that agitation affects the
intermediate size fractions more that the small and large fractions. Data also show a correlated
decrease in 4He/3He mass ratios with increased grain size fraction in regolith fines, changing from
about 3500 to about 3300 before again increasing in the courser fractions. These concentration vs.
grain size relationships may reflect the interplay of implantation energy vs. particle mass vs. surface
area during repeated agitation as samples were handled and processed from the undisturbed regolith on
the Moon to the analyst's mass spectrometer.
Regolith breccias offer some more specific insights into the undisturbed concentrations of solar wind
volatiles. Volatiles sealed into some regolith breccias indicate that the undisturbed concentration of
helium-3 may be 20.5 wppb or higher. Data indicate that rapid shock or base surge induced induration
of regolith, may seal in at least 57% more helium-3 than is preserved in the analyzed samples of
Apollo 1 1 fines. This difference, as well as consideration of 4He/3He ratios as a function of grain
size, indicates that losses of helium-3 from Apollo 1 1 fines due to agitation may be at least 42% of its
concentration in undisturbed regolith.
Systematic variations in 4He/3He ratios between fines and breccias and between various grain size
fractions also suggest losses of solar wind volatiles due to sample agitation. There also appears to be
secondary enrichment of helium-4 relative to helium-3 in regolith modified by impact processes.
REFERENCES
(1) Hintenberger, H., H. W. Weber, H. Voshage, H. Wanke, F. Begeman, and F. Wlotzka, 1970, Concentrations
and isotopic abundances of the rare gases, hydrogen, and nitrogen in Apollo 1 1 lunar matter, Proceedings Apollo
1 1 Lunar Science Conference, 2, pp. 1270, 1271, 1277, 1278; See also Baur, H, U. Frick, H. Funk, L. Schultz,
and P. Signer, 1972, Thermal release of helium, neon, and argon from lunar fines and minerals, Proceedings
Lunar and Planetary Science Conference 3, Table 1, p. 1954.
(2) Eberhardt, P., J. Geiss, H. Graf, N. Grogler, U. Krahenbuhl, H. Schwaller, J. Schwarzmuller, and A Stettler,
1970, Trapped solar wind noble gases, exposure age and K/Ar-are in Apollo 1 1 lunar fine material, Proceedings
Apollo 1 1 Lunar Science Conference, 2, p. 1040.
(3) Hintenberger, H., H. W. Weber, and N. Takaoka, 1971, Concentrations and isotopic abundances of rare
gases in lunar matter, Proceedings Lunar Science Conference 2, Table 1, p. 1608.
Space Resources Roundtable VI 43
SYNTHESIS OF SOL-GEL PRECURSORS FOR CERAMICS FROM
LUNAR AND MARTIAN SOIL SIMULARS
L. Sibille 1 , J.A. Gavira-Gallardo 2 , and D. Hourlier-Bahloul 3
'BAE SYSTEMS Analytical Solutions
NASA Marshall Space Flight Center SD46
Huntsville, AL 35812
Laurent.Sibille@msfc.nasa.gov
2 Laboratorio de Estudios Cristalograficos
I.A.C.T. CSIC-Univ. Granada.
Facultad de Ciencias
Campus Fuentenueva
18002 Granada, Spain
jgavira@ugr.es
3 Science des Procedes Ceramiques et de Traitement de Surface,
Universite de Limoges, France
hourlier@unilim.fr
Recent NASA mission plans for the human exploration of our Solar System has set new priorities
for research and development of technologies necessary to enable a long-term human presence on
the Moon and Mars. The recovery and processing of metals and oxides from mineral sources on
other planets is under study to enable use of ceramics, glasses and metals by explorer outposts.
We report initial results on the production of sol-gel precursors for ceramic products using
mineral resources available in martian or lunar soil. The presence of Si0 2 , Ti0 2 , and A1 2 3 in
both martian (44 wt.% Si0 2 , 1 wt.% Ti0 2 , 7 wt.% A1 2 3 ) and lunar (48 wt.% Si0 2 , 1.5 wt.%
Ti0 2 , 16 wt.% A1 2 3 ) soils and the recent developments in chemical processes to solubilize
silicates using organic reagents and relatively little energy indicate that such an endeavor is
possible. In order to eliminate the risks involved in the use of hydrofluoric acid to dissolve
silicates, two distinct chemical routes are investigated to obtain soluble silicon oxide precursors
from lunar and martian soil simulars.
Clear solutions of sol-gel precursors have been obtained by dissolution of silica from lunar soil
similar JSC-1 in basic ethylene glycol (C 2 H 4 (OH) 2 ) solutions to form silicon glycolates.
Similarly, sol-gel solutions produced from martian soil simulars reveal higher contents of iron
oxides. Characterization of the precursor molecules and efforts to further concentrate and
hydrolyze the products to obtain gel materials will be presented for evaluation as ceramic
precursors.
44 LPI Contribution No. 1224
DRILLING TO EXTRACT LIQUID WATER ON MARS: FEASIBLE AND
WORTH THE INVESTMENT
C. Stoker, (carol.r.stoker@nasa.gov), MS 245-3, NASA Ames Research Center, Moffett Field, CA
A critical application for the success of the Exploration Mission is developing cost effective means to
extract resources from the Moon and Mars needed to support human exploration. Water is the most
important resource in this regard, providing a critical life support consumable, the starting product of
energy rich propellants, energy storage media (e.g. fuel cells), and a reagent used in virtually all
manufacturing processes. Water is adsorbed and chemically bound in Mars soils, ice is present near the
Martian surface at high latitudes, and water vapor is a minor atmospheric constituent, but extracting
meaningful quantities requires large complex mechanical systems, massive feedstock handling, and large
energy inputs. Liquid water aquifers are almost certain to be found at a depth of several kilometers on
Mars based on our understanding of the average subsurface thermal gradient, and geological evidence
from recent Mars missions suggests liquid water may be present much closer to the surface at some
locations. The discovery of hundreds of recent water-carved gullies on Mars indicates liquid water can be
found at depths of 200-500 meters in many locations. Drilling to obtain liquid water via pumping is
therefore feasible and could lower the cost and improve the return of Mars exploration more than any
other ISRU technology on the horizon. On the Moon, water ice may be found in quantity in permanently
shadowed regions near the poles.
A system of modular, reconfigurable, autonomous and human- tended deep drilling technologies
should be developed for use initially on Mars precursor missions and later for subsequent crewed
missions that are less mass and power constrained. For the Mars application, the drilling technology will
be focused on obtaining liquid water via pumping for resource utilization purposes. Early testing on the
Moon could be used to establish viability of this technology so that it can be a cornerstone architecture
element of Mars exploration, as well as a tool for resource exploration and science.
The required technologies for the Moon and Mars have much in common but there are important
differences. On the Moon, directional drilling is likely to call for the use of a conventional drill string
(similar to one under development for robotic Mars application) and a steerable down-hole unit. Hole
stability in the lunar regolith will require the use of casing or of microwave sintering. Exploitation of
lunar resources identified by drilling will subsequently be a mining and processing operation. On Mars
the main task will be deep penetration to gain access to liquid water. Penetration to depths of kilometers
would require massive equipment if a drill string is used but could be implemented using a wire-line
device (one that anchors itself to the bottom of the hole and exerts force on bit from there rather than from
the surface) where additional depth penetration requires only the addition of more cable. Its advantages
include lightweight and convenience in automating its control since digital data can be more easily
communicated. Mars ISRU goals will involve gaining controlled access to liquid water that can be
pumped to the surface. Because of the stabilizing effect of ground ice, much of a Martian drill hole may
not need stabilization. Preventing bit freeze up may require controlling bit temperature, and cuttings
removal may require use of low temperature drilling fluids, such as liquid C0 2 derived from Mars air. It
may also be necessary to line the hole with an insulating material to ensure that water does not freeze on
its ascent to the surface.
Drills developed for robotic Mars mission applications have been field tested to 1 m depth. Deeper
depths suggest a wire line drill string (downhole motor driving the bit) suspended on a cable and an
elevator bailer to remove cuttings. Design issues to be addressed for a deep drill include operational
simplicity and low mass, bit development and change-out strategies to respond to bit wear and the need to
cut a range of materials, cuttings removal approach, systems for anchoring the drill string in the hole and
providing weight on bit, casing for hole stability and capping to prevent destructive effects of pressure
differentials.
While NASA Code S has recently invested in technology development for robotic drills for Mars
exploration (and useful progress has been made) the investment is not consistent in scope with the new
Space Exploration vision.
Space Resources Roundtable VI 45
THE UNCERTAIN NATURE OF POLAR LUNAR REGOLITH
G. Jeffrey Taylor 1 , Joshua Neubert', Paul Lucey 1 , and Edward McCullough 2
'Hawaii Inst, of Geophysics and Planetology, Univ. of Hawaii, 1680 East-West Rd., Honolulu, HI 96822;
gjtaylor@higp.hawaii.edu. 2 Boeing, Huntington Beach, CA; edward.d.mccullough@boeing.com
Lunar polar regions are receiving considerable attention because they might contain sizeable
quantities of H 2 0, which could be useful for lunar development and space commerce [1]. Plans to use
those resources are limited by our ignorance of the nature of polar regions. Major uncertainties are
outlined here. All can be addressed by missions to permanently shadowed polar regions on the Moon.
Regoltih characteristics: The typical lunar regolith has a mean grain size of -100 nm, with -10%
of the material smaller than 10 [im [2]. However, the polar regions are in the most ancient lunar
highlands, which have been subjected to the most intense bombardment for more than 4 billion years.
Hartmann [3] suggests that the upper hundreds of meters have been reworked so extensively that it
resembles the typical lunar regolith. Since the heavy bombardment ceased about 3.8 billion years ago, the
upper several meters of the Moon have been modified by micrometeorite impacts. That regolith may be
much finer grained than typical regolith as it developed on hundreds of meters of fine-grained material. If
so, we cannot predict with confidence the physical properties of the regolith (porosity, thermal
conductivity, shear and bearing strength, angle of repose, tribology). A finer grain size provides a much
larger surface area for a given mass of regolith, which could enhance adsorption of H 2 and other
volatiles and their reaction with regolith grains.
Characteristics of the H 2 deposits: There is clear evidence for enrichment in H in lunar polar
regions [4], but what form is it in? Models depict the observed enrichments in hydrogen as being due to
solar wind hydrogen, water ice deposited by H 2 released from soil grains that have been bombarded
with solar wind hydrogen, and more complex ices released by impacting comets. These deposits could
form thin films around regolith grains (adsorbed chemically or physically [5]), partially- to completely-
filled pore spaces, or form layers of ice (in the case of comet impacts). Each of these scenarios leads to
potentially different physical and geotechnical properties of the regolith, and different properties of the
resource. To show the complexities, consider a cometary source for H 2 0. In this case the H 2 would be
accompanied by CO, C0 2 , CHt and other gases. If the H 2 precipitated as one of the many forms of ice,
it could be relatively pure because of the low solubility of gases it in, but might be associated with
deposits of less stable carbon gases. If the H 2 precipitated as amorphous ice, the amorphous ice might
contain dissolved CO and other gases. When heated during exploration or extraction, the amorphous ice
would crystallize, releasing the trapped gases and possibly producing jets of dust and gas, as happens as
comets are heated [e.g., 6]. Moreover, the crystallization is exothermic, possibly leading to a runaway
effect, release of C0 2 from its frozen form, loss of the resource, and possibly damage to extraction
equipment. At the very least it prevents us from knowing how to design equipment for surface mobility or
to extract volatiles from polar regolith. Finally, whatever its state, we do not know how the H 2 resource
is distributed with depth or laterally.
References: [1] Duke, M. B. (2000) Lunar polar ice: Implications for lunar development. J. Aerospace
Eng. 11, 124-128. [2] McKay, D. S., Heiken, G. Basu, A., Blanford, G., Simon, S., Reedy, R., French, B.
M., and Papike, J. J. (1991) The lunar regolith. Lunar Sourcebook (G. H. Heiken, D. T. Vaniman, and B.
M. French, eds.), 285-356. Cambridge University Press. [3] Hartmann, W. K., Megaregolith evolution
and cratering cataclysm models — Lunar cataclysm as a misconception (28 years later). Meteor. Planet.
Sci. 38, 579-593. [4] Feldman, W. C. et al. (2001), Evidence for water ice near the lunar poles. J.
Geophys. Res. 106,23232-23252. [5] Cocks, F. H. et al. (2002) Lunar ice: adsorbed water on subsurface
polar dust. Icarus 160, 386-397. [6] Prialnik, D. (1997) A model for the distant activity of comet Hale-
Bopp, Astrophys. 7.478, L107-L110.
46 LP1 Contribution No. 1224
THE NATURE OF LUNAR SOIL:
CONSIDERATIONS FOR SIMULANTS
Lawrence A. Taylor 1 , David S. McKay 2 , W. David Carrier III 3 ,
James L. Carter 4 , and Paul Weiblen 5
'Planetary Geosciences Institute, Univ. of Tennessee, Knoxville, TN 37996 lataylor@utk.edu ; 2 Planetary
Exploration, Johnson Space Center, Houston, TX 77058; 3 Lunar Geotechnical Institute, Lakeland, FL 33807-
5056; 4 Dept. of Geosciences, University of Texas at Dallas, Richardson, TX; 5 Dept. of Geol. & Geophys.,
Univ. of Minnesota, Minneapolis, MN 55455
Introduction: It is obvious that many factors must be considered in making lunar simulants for various
ISRU projects. This subject is of major importance (also, see abstract by Carter et al., this meeting) as we
move into the near-future endeavors associated with a return to the Moon. Herein, we address the detailed
geologic specifics of lunar soil and list many of the geotechnical properties that should be considered before
we produce simulants for definitive study purposes.
Formation of Lunar Soil: The lunar soil formed by space weathering processes, the most important of
which is micrometeorite (< 1mm) impact dynamics. Although of small mass, these particles possess large
amounts of kinetic energy, impinging on the lunar surface with velocities up to 100,000 km/hr. Much of the
impacting energy goes into breaking and crushing of fragments into smaller pieces; however, due to the high
energy of many of the impacts, the lunar soil is partially to completely melted on a local scale of millimeters.
The melted soil incorporates soil fragments and quenches to glass. These aggregates of minerals, rocklets,
and glasses are welded (i.e., cemented) together into "agglutinates" [1]. It is the glass in these fragile aggluti-
nates that further becomes comminuted into smaller pieces making for ever-increasing amounts of glass to
the lunar soils. Portions of these silicate melts also vaporize, only to condense upon the surfaces of all soil
grains. Other cosmic, galactic, and solar-wind particles also perform minor weathering, largely by sputtering;
but many of these particles remain imbedded in the outer portions of all lunar soil grains. As demonstrated by
Taylor & McKay [2], as the number of lithic fragments decreases, the amount of liberated free minerals in-
creases to a point, with continuing exposure to impact processes actually decreasing the abundance of these
mineral fragments. With these changes in rock and mineral fragments, the major accompanying process is
the formation of the glass-welded agglutinates; and the abundances of agglutinitic glass increase significantly
with decreasing grain size [3]. Due to complicated interactions of the impact melts with solar-wind, as well
as productions of vaporized chemistry, the glass of the lunar soil contains myriads of nano-sized Fe grains
(4-33 nm), with the soil containing 10X more Fe° than the rocks from which it was derived. As a result of all
this space weathering, the resulting lunar soil consist of rocklets, minerals, and agglutinates, with major
amounts of glasses, impact-produced but also volcanic in origin.
The abundances of glass in lunar soil increases with decreasing grain size, such that the "dust" (i.e., <50
^m) portion of the lunar soil contains over 50% glass, present as sharp, abrasive, interlocking, fragile glass
shards and fragments. It is this same "dust" at <50 (im that constitutes approximately 50% of mature lunar
soils, as a rule-of-thumb for size distributions. It is the mainly the presence of these huge quantities of glass
that contributes to the unusual engineering properties of lunar soil [4].
Geotechnical Soil Properties for Consideration in Simulants: Particle Size Distribution; Particle Shapes;
Specific Gravity; Bulk Density; Soil Porosity; Compressibility; Shear Strength; Permeability; Diffusivity;
Bearing Capacity; Ultimate Slope Stability; Trafficability; Electrical Conductivity; Dielectric Permittivity;
Magnetic Susceptability; etc.
References: [1] McKay, D.S., and A. Basu, 1983, The production curve for agglutinates in planetary regoliths. Jour.
Geophys. Res. 88, B-193-199; [2] Taylor, L.A., and D.S. McKay, 1992, Beneficiation of lunar rocks and regolith:
Concepts and difficulties. In Engineering, Construction, Operations in Space III . Vol. I, ASCE, New York, 1058-1069;
[3] Taylor, L.A., Pieters, C, Keller, L.P., Morris, R.V., McKay, D.S., 2001, Lunar mare soils: Space weathering and
the major effects of surface-correlated nanophase Fe. Jour. Geophys. Lett. 106, 27,985-27,999; [4] Taylor, L.A., Piet-
ers, C, Keller, L.P., Morris, R.V., and McKay, D.S., 2001, The effects of space weathering on Apollo 17 mare soils:
Petrographic and chemical characterization. . Meteor. Planet. Sci. 36, 285-299; [5| Carrier, W.D., III, Olhoeft, G.R.,
and Mendell, VV., 1991, Physical properties of the lunar surface, in Lunar Sourcebook, ed. by G. Heiken, D. Vaniman,
and B. French, Cambridge University Press, New York, 475-594.
Space Resources Roundtable VI 47
STEEL PRODUCTION UTILIZING IRON EXTRACTED
FROM LUNAR ORES AND SOILS
Richard Westfall 1 and William C. Jenkin 2
1) President, Galactic Mining Industries, Inc.
4838 Stuart St. Denver, CO 80212-2922
303-433-1978
mail@space-mining.com
http://www.space-mining.com
2) 382 Dorchester Road, Akron, OH 44320
330-867-3628
wmcjenkin@neo.rr.com
Steel compositions will be developed using iron extracted from lunar ores and soils. Research
will focus on the hydrogen reduction of iron contained in the lunar simulants MLS-1 (Minnesota
Lunar Simulant) and JSC-1 (Johnson Space Center Simulant). This reduced iron will be extracted
using carbonyl (CO - carbon monoxide) chemical processes. Extracted iron is in the form of iron
pentacarbonyl (Fe(CO) 5 ). Iron pentacarbonyl is used in the Chemical Vapor Deposition (CVD) of
various steel coatings onto and inside of mandrel surfaces such as inflatables and slush mold
contours.
Inflatable and slush mold forms are to be used to produce components necessary for the
establishment of lunar bases and operations. The first mandrel contours which we will investigate
will be in the form of cylindrical shapes. Steel compositions will be deposited on the interior or
exterior surfaces of these cylindrical shapes to form steel pressure vessels. These pressure vessels
will serve as storage for gases and housings for crews and operational activities on the moon.
There are specific steel compositions which include boron which are analogous to nickel
compositions which have been deposited using Chemical Vapor Deposition (CVD) by William
Jenkin and show substantial tensile strengths.
The research proposal submitted to NASA (Steel Production Utilizing Iron Extracted from Lunar
Ores and Soils) will in Phase I look in detail at the extraction of Iron from lunar simulants. We
will examine a matrix of processing conditions and hardware configurations that can be scaled up
to produce flight hardware that can be tested in space and on the Moon. In Phase I, iron extraction
will be examined in detail. In Phase I we will also explore rudimentary deposition hardware and
basic deposition conditions to a limited degree. In Phase II, we will manufacture and test
apparatus capable of extracting iron from lunar simulants and we will expand our research into
the deposition of various steel compositions. The first depositions inside of cylindrical inflatables
will be carried on in Phase II of the research program, with a sample pressure vessel as one of the
deliverables to NASA at the end of the Phase II work. Phase III will actually involve the
manufacture of flight hardware suitable for launch and testing in Earth orbit and on the Moon.
Manuals suitable for the construction of processing plants on the Moon will be provided as
deliverables at the end of Phase III of this research program. Questions regarding the suitability
and scalability of these processes will be answered and future work will be proposed to provide
for the In-Situ Resource Utilization of lunar materials in the construction of manned and
unmanned lunar bases and operations.
48 LP! Contribution No. 1224
SPACE LAW UPDATE:
REAL PROPERTY RIGHTS AND RESOURCE APPROPRIATION
W. N. WHITE
Attorney at Law
2969 Baseline Road
Boulder CO 80303
303-440-8789
wn_white@earthlink.net
During the past year, real property rights has become the most important issue in the field
of space law. Gregory Nemitz pursued his claim to Asteroid 433 Eros in Federal District Court,
where his case was dismissed. That precedent-setting case, Nemitz vs. the United States, is now
before the Ninth Circuit Court of Appeals. Also in the past year, the International Institute of
Space Law, a member organization of the International Astronautical Federation, issued its first
ever position paper, "Statement of the Board of Directors Of the International Institute of Space
Law (IISL) on Claims to Property Rights Regarding the Moon and Other Celestial Bodies."
Finally, the Report of the President's Commission on Implementation of United States Space
Exploration Policy (the "Aldridge Commission Report") said that "it is imperative that [property
rights] issues be recognized and addressed at an early stage in the implementation of the vision,
otherwise there will be little significant private sector activity associated with the development of
space resources, one of our key goals." The author will discuss the implications of these
developments, including the prospects for future U.S. legislation regarding property rights and
mining law in outer space.
Space Resources Roundtable VI 49
CONCEPT FOR LANDED MEASUREMENTS OF MARS THAT WILL
HELP D3ENTIFY AND CHARACTERIZE POTENTIAL SURFACE
RESOURCES
Woodworth-Lynas*, C.M.T., J.Y. Guigne, D. Hart and R. Davidson
Guigne Space Systems Inc., Golden Colorado
* chriswl@guigne.com
We describe the concept for a very shallow seismic subsurface imaging capability (< 10 m, equivalent to
~ 10-20 ms) based on proven concepts and commercial techniques with the scientific goal of studying
very near-surface planetary structure. The technical goal is to develop a miniaturized percussion-seismic
source and geophone receivers, with a long-term goal of full integration with a Mars rover. The seismic
system may be used to image the very shallow subsurface region of Mars to detect specific boundaries
such as near-surface permafrost and buried layers that may contain easily accessible mineral resources
that could be used for in situ fabrication and repair of facilities. These near-surface layers may then be
reached for direct in situ sampling using a mechanical percussion seismic source as a shallow drill or by a
customized piezoelectric shallow drilling tool, such as a small Ultrasonic/Sonic Driller/Corer (USDC).
The challenges for very shallow seismic profiling are:
• to reduce transmit pulse length so that near-surface reflectors are not lost in the transmit pulse or
surface wave;
• to ensure sufficient high frequency content in the transmit pulse to resolve narrow layers;
• to ensure sufficient energy is transmitted into the ground so that reflected energy is recorded by the
geophones.
A Percussion Seismic Source (PSS) is based upon the concept of a solenoid operating in percussive mode
with only one moving part: the free mass. The free mass tip will be designed based on concepts for
commercial button bits with venturi holes and retrac shank. Manufacture of the bit will be carried out in a
single step casting likely based on a titanium carbide alloy using a combustion synthesis method.
Optimum operation of the PSS relative to the geophones would require it to beat against an exposed
bedrock surface. In the event that bedrock is mantled by unconsolidated regolith (e.g. as found by the
Opportunity MER in the region between bedrock craters at Planum Meridiani) the PSS would have to
operate in and penetrate through unconsolidated material before reaching bedrock. Using a bit based on
the commercial retrac concept will allow penetration of loosely consolidated surface soil and fractured
bedrock. The ridged shank is designed specifically to allow the bit to reverse drill in the event of hole
collapse.
The commercial bits have integral compressed air channels in the bit shaft. Compressed air is forced into
the channels and out through venturi holes in the bit face to blow out rock dust and cuttings produced at
the drill face.
Additional benefits of the bit design, that were not intended for the commercial application are:
• compressed air flushing will clean out the hole leaving a pristine cross section in bedrock ideal for in
situ, rock analysis and imaging;
• grooves of the retrac bit would allow insertion of a miniature downhole sensor suite such as a LIBS
and Raman spectrometer (currently under development by Dr. Chris Dreyer, Colorado School of
Mines).
50 LP1 Contribution No. 1224
USING SPENT FUEL TANKS AS HABITATS
Tom Wray 1 and Gary "ROD" Rodriguez 2
1) Space Architect, 3 rd Millenium Construction Company
2) Systems Architect, jysRAND Corporation
The idea of using an expended liquid fuel rockets as a serviceable container for human habitation
and technical spaces is a recurring topic. With the advent of Dr. Robert Zubrin's simulated
habitats the concept has achieved a certain credibility, even acceptance, as a state-of-the-art
practice. This paper outlines some design considerations for habitats and supporting structures in
low-gravity, and is intended to encourage architects with other constraints and considerations to
join the conversation.
Keywords: In Situ Resource Utilization (ISRU) structures, habitat design, expended fuel tanks.
Space Resources Roundtable VI 51
THE APPLICATION OF SELF-PROPAGATING
HIGH TEMPERATURE (COMBUSTION) SYNTHESIS (SHS)
FOR IN-SPACE FABRICATION AND REPAIR
Xiaolan Zhang 1 , Hu Chun Yi 2 , Jacques Y. Guigne 2 , A. Mannerbino 2 , John J. Moore
1 Center for the Commercial Application of Combustion in Space (CCACS),
Colorado School of Mines, Golden, Colorado
2 Guigne' Space Systems Inc. Golden, CO
Self-propagating high temperature synthesis (SHS), also called combustion synthesis, is
an extremely versatile, rapid and energetically favorable process: the energy needed to sustain the
process coming from the chemical energy of the exothermic reaction mix. SHS can be used to
synthesize, repair and join a wide range of advanced materials, fully dense or with controlled
porosity (20-90%), in low vacuum, low and microgravity environments, and in oxygen-free or
oxygenated (including a C0 2 ) environments. As such, these engineered SHS reaction systems can
be designed to take advantage of the ambient environment, rendering an extremely high degree of
process versatility and flexibility.
A research team based in Golden, Colorado comprising materials scientists from the
center for the Commercial Application of Combustion in Space (CCACS) at Colorado School of
Mines, and Guigne Space Systems Inc. (GSSI) has developed SHS technologies that are capable
of producing net- and near-net-shaped components, and to join both similar and dissimilar
materials such as intermetallics, metals, ceramics and composites.
The paper will discuss the application of SHS to fabricate and repair a wide range of
materials with examples that include acoustic damping materials for rocket engines, joining of
components, shuttle wing repair, and mineral sterilization. In particular, the application of this
technology for in-space fabrication and repair will be highlighted.
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