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\"Anniversaries are a time of recollection \.... Personally, I would
rather look ahead to things we\'re going to do in the future than the
things we did in the past.\"

*Neil A. Armstrong, 1994*

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There are many reasons for continuing the human exploration of the Moon.
Whether to emplace advanced astronomical instruments, to gather
information about the formation of the solar system, or to establish a
"testbed" for advanced exploration technologies, the return of humans to
the lunar surface represents a fundamental step beyond LEO. But is it
worth the cost? When the subject of future exploration is mentioned at
high government levels, the typical response is "it's too expensive, we
can't do that." However, it seems that such a reaction has the problem
exactly reversed and should be stated "when we find a less expensive
way, we'll go."

Finding an economical method of lunar exploration is what our current
study efforts are all about. Unsubstantiated arguments about the "best"
way to return to the Moon are analogous to quarrels over deck chairs on
the Titanic. Cost must be a primary engineering parameter which is
constantly traded against performance, risk, and schedule. Perhaps most
importantly, in this transitional period when new program starts are
problematic, the limited dollars available must be invested in those
technologies which hold the highest potential for exploration mission
cost reduction.

What are the reasons that human exploration missions are perceived to be
so expensive? The various "top-down" computer models that are used to
predict program costs give us some clues. Not surprisingly, one of the
most important parameters is the mass of the transportation systems. The
bigger a spacecraft is, the more it is likely to cost, and since
exploration missions are high-energy missions, they require lots of
propellant, big tanks, and heavy supporting structure. Another factor is
a somewhat vague concept called "complexity." This reflects the fact
that a vehicle which must perform rendezvous, proximity operations,
docking, and crew transfer is more costly than a simple crew module.
Also, a system that is an upgrade of a proven design has lower
development costs than a "clean sheet" approach. The final consideration
is the supporting infrastructure required to complete the mission. If
the total space budget is a priority, one program cannot

be permitted to "off load" costs to another; for example, we cannot
ignore the costs of building or modifying a space station if it is
needed to support exploration. So, to summarize, the ideal technology
for exploration missions is one that would enable the combination of low
mass, simplicity, heritage from current systems, and independence from
ancillary infrastructure -- a challenging combination, but one which we
think we have found with a mission concept we call "LUNOX," short for
"lunar oxygen."

Most persons interested in lunar exploration know that there are vast
reserves of oxygen locked up in the lunar soil. In fact, nearly half the
weight of lunar surface material is oxygen! Dozens of potential
extraction methods have been identified, several have been patented, and
one has been successfully tested on small amounts of returned Apollo
samples (see Beyond LEO Vol. 1., No. 2). Oxygen on the Moon would be
valuable for many different purposes, but using it as spacecraft
propellant oxidizer for the return to Earth is the application that
holds the highest promise for reducing mission costs. Eighty-five
percent of the weight of the propellant of a hydrogen-oxygen-powered
spacecraft is oxygen, and if the return oxidizer does not have to be
carried to the lunar surface, the size of the spacecraft and launch
vehicle required is drastically reduced. For example, when compared to
Apollo, or the "First Lunar Outpost" strategy (see Beyond LEO, Vol. 1,
No. 1), the weight that must be injected toward the Moon can be reduced
by nearly a factor of three! This is enough to avoid the development of
a large, new booster or the necessity of on-orbit assembly at a space
station -- a single launch of a Shuttle-derived vehicle ("Shuttle-C"),
long-known for expected low development costs, is sufficient. A supply
of lunar oxygen also makes the lunar-orbit-rendezvous technique utilized
by Apollo obsolete. Since the penalty of taking the Earth-return
oxidizer to the lunar surface is eliminated, there is no need for a
second spacecraft to remain in lunar orbit, and norequirement for any
kind of rendezvous at all. We've therefore met all of our cost-cutting
strategies for transportation: less mass, simpler systems, launchers
which are modifications of existing designs, and a reduction of required
infrastructure. The key to realizing these advantages is the
establishment of the oxygen production capability prior to sending
people back to the Moon.

It is not possible at this point to advocate the "best" extraction
technique for LUNOX production. Trades involving system mass, power
requirements, process complexity, oxygen yields, reagent resupply, and
equipment maintenance must be made. However, a design study has been
performed for a plant utilizing the "hydrogen reduction" process
consistent with production quantities required to return a crew of four
from the Moon twice a year. This concept uses the combination of a small
teleoperated front-end loader and regolith hauler to mine and transport
feedstock and dispose of process tailings, a three-stage "fluidized bed"
reactor to produce the oxygen, and a 40 - 60 kilowatt nuclear power
supply. In addition, small oxygen "tankers" would be needed to transport
the liquefied oxygen to the waiting crew vehicle, where it would be
pumped into the empty oxidizer tanks.

The LUNOX production equipment and associated surface vehicles must be
transported to the Moon by dedicated cargo flights. If the
Shuttle-derived vehicle is used for both piloted and cargo missions, a
delivery capability of approximately 12 metric tons to the lunar surface
results. Our design studies indicate that all of the required lunar
oxygen production infrastructure could be delivered in only two flights,
at which point teleoperated oxygen production would begin. Human flights
would not take place until a sufficient cache of oxygen had been
extracted, liquefied, and stored, and the propellant transfer equipment
had been operationally verified.

The piloted flights would begin with the launch of a man-rated Shuttle-C
from the existing Shuttle pads at the Kennedy Space Center. After a
short pause in Earth orbit for proper phasing, the crew would be
injected into a\
4-day, translunar trajectory. After another short pause in lunar orbit,
the final descent and landing would occur. Upon completion of the
surface mission, the crew would refill the lander's oxidizer tanks with
ten tons of lunar oxygen for the trip home. The crew module would
reenter Earth's atmosphere in much the

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same way as the Apollo Command Module, but modern navigation and control
capabilities should allow touchdown at prepared landing sites, therefore
eliminating the expense of mid-ocean recovery forces.

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While much of the hardware in the LUNOX scenario is expended, there is
an opportunity to reuse the most costly element -- the crew module.

From this description of the LUNOX strategy, it is apparent that its
feasibility relies heavily upon the development of key technologies:
high duty-cycle electric surface vehicles for regolith and oxygen
transport, automation and robotics for surface mining, and highly
reliable chemical processing for unattended lunar oxygen production.
This is somewhat of a departure from the technology expertise of the
aerospace industry where the focus tends to be in the areas of vehicles
and propulsion systems. However, this can be viewed as an opportunity to
broaden the relevancy of government-sponsored space technology to the
commercial sector. In addition, the programmatic risk associated with
the oxygen extraction techniques can be mitigated by proof-of-concept
precursor missions involving small lunar landers or rovers equipped with
process demonstration packages.

When cost estimates of this strategy are compared with those of a more
"traditional" approach, the leverage of space resources becomes
apparent. The development costs of the piloted spacecraft and launch
vehicle are reduced by more than 55 percent, and the unit costs by more
than 60 percent! Even when the expected development, production, and
launch costs of the oxygen extraction equipment are included, this
investment is still less than the total development costs of the
traditional approach, and the per flight savings accrue from the first
piloted mission.

It appears that the use of space resources is the single highest payoff
technology yet identified for renewed human exploration of the Moon.

For Additional Reading

Altenberg, B. (1990) Processing Lunar In-Situ Resources, Technical
Research and Development Project No. 90634-002, Bechtel Group, Inc.

Joosten, B.K. and Guerra, L.A. (1993) Early Lunar Resource Utilization:
A Key to Human Exploration. AIAA Paper 93-4784, AIAA Space Programs and
Technologies Conference, Huntsville, AL.

Zubrin, R.M. (1992) The Design of Lunar and Mars Transportation Systems
Utilizing Extraterrestrial Resources, IAA Paper No. 92-0161, *43rd
Congress of the International Astronautical Federation*, Washington, D.
C.

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The Exploration Team at JSC has developed a hypertext World Wide Web
server for exploration mission concepts beyond low Earth orbit. This
system makes space exploration news, documents, and images available to
the internet community. You can access this information through the NCSA
Mosaic application (or similar WWW software) at the address
**exploration.jsc.nasa.gov**. The NCSA Mosaic application is shareware
available for various platforms (Macintosh, PCs, Suns, etc.)
downloadable from anonymous ftp sites.

The documents available on the Exploration server include full-text
**reports** (both ascii and MSWord versions) relating to exploration of
the Moon and Mars. **Fact sheets** available include chronologies of
missions to the Moon and Mars including mission name, country, date,
mission objectives, and results. There is also a fact sheet on lunar
EVA's including flight number, EVA date(s), astronauts, activities, and
time spent in EVA. The **image files** that are available include
computer generated scenario concept images, Apollo images, Viking
images, and a few miscellaneous images. Most images include a short
description and the NASA image number.

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We maintain a current database of individuals who wish to receive
current issues of \"Beyond LEO.\" Anyone wishing to be added or deleted
from the list may contact Roy Boyer (713-483-6820,
boyer@newton.jsc.nasa.gov) or John Connolly (713-483-5899,
jconnolly@snmail.\
jsc.nasa,gov) at JSC\'s Planetary Missions and Materials Office.

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Construction and Operation of a Mars In Situ Propellant Production Unit

by Dave Kaplan

kaplan@snmail.jsc.nasa.gov

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Between October 1993 and January 1994, Martin Marietta Astronautics in
Denver, Colorado, built and operated a chemical synthesis unit
representing the core of a machine capable of manufacturing rocket
propellant, primarily out of indigenous materials freely available on
Mars. This activity was funded by the Planetary Missions and Materials
Branch (formerly the Planetary Projects Office) at NASA/Johnson Space
Center (JSC). David Kaplan was the JSC program manager; Steve Price was
the project manager at Martin Marietta.

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The following material is extracted from the Martin Marietta report
issued at the end of the contract. The Martin Marietta authors are
Robert Zubrin, Steve Price, Larry Mason, and Larry Clark:

"Prior to the project reported on here, a study, also funded by the
\[Planetary Missions and Materials Branch\] of JSC, had been undertaken
at Martin Marietta, to examine the benefits and feasibility of
accomplishing a Mars Sample Return (MSR) mission using locally produced
propellant to fuel the rocket vehicle that would return the sample to
Earth. That study, led by Robert Zubrin, found that a large mission
enhancement could be achieved by such means, and recommended that the
propellant production process employed be one termed the
"Sabatier/Electrolysis" or "S/E" cycle. Using such a system, it was
found that an S/E unit producing 1 kg of propellant per day could be
used to support an MSR mission that would return a 4 kg soil and rock
sample from Mars to Earth. A single Delta 7925 launch vehicle was found
sufficient to support the mission, which consisted of a single
spacecraft being sent directly from Earth to the Martian surface,
refueling there during a year and a half surface stay, and then
returning directly from the Martian surface to Earth, without any
intervening Mars orbit rendezvous maneuver.

"The S/E cycle propellant plant employed in the mission works as
follows: Hydrogen is transported from Earth to Mars where it is combined
with CO2 acquired from the Martian atmosphere in a Sabatier reactor to
produce methane and water in a 1:2 molar ratio. The methane produced by
this process is drawn off and liquefied, while the water is condensed
and sent to an electrolysis unit to be split into hydrogen and oxygen.
The oxygen produced by the electrolysis unit is liquefied, and the
hydrogen is fed back into the Sabatier reactor.

"The technology required to accomplish this cycle is well understood,
and in fact has been in use on Earth for over a century. This high
degree of heritage of the required component technology was the basis
for the selection of the S/E cycle for the MSR mission.

However, despite the fact that each of the component technologies has
long been used, to the best of our knowledge, putting all of them in a
cycle to make a complete system of the type described has never been
done."

". . . In the course of just three months, with a total budget of
\$47,000, a full scale working system was built and made to operate with
a conversion efficiency of 94%. The combined mass of all operating
components of the prototype S/E system was less than 20 kg, with
potential improvements that would cut that mass roughly in half clearly
in sight. The output of the current prototype system, 720 grams of
propellant a day, would allow it to produce close to 20 times its own
weight in propellant in the course of a typical 500 day conjunction
class Mars surface stay."

". . . Much work remains to be done before the complete practicality of
in-situ propellant production to support Mars missions is demonstrated
end-to-end. Yet the relative ease with which so much was accomplished in
so short a time on the present project can only be viewed as extremely
encouraging. Taken together with the enormous benefits in-situ
propellant production provides to both automated and piloted Mars
exploration, the success of the current demonstration speaks forcefully
for the wisdom of further development efforts."

For Additional Reading

Zubrin, Robert M., Price, S., Mason, L., Clark, L. (1994) \"Report on
the Construc-tion and Operation of a Mars In-Situ Propellant Production
Unit\", AIAA 94-2844, AIAA Joint Propellant Conference, Indianapolis,
IN.

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To her crew, she's the "Weightless Wonder," to her passengers, she's the
"Vomit Comet." But regardless of the name, this unusual aircraft helped
the Planetary Missions and Materials Office take another step closer to
renewed human exploration of the Moon.

The "Comet" is a specially modified Boeing KC-135A turbojet transport,
designation NASA 930, operated by the Johnson Space Center's Reduced
Gravity Office. By flying a series of "roller-coaster" parabolic
maneuvers, short periods of reduced gravity are experienced onboard.
While most flights are dedicated to zero-g astronaut training and
equipment tests, in February two missions were flown simulating the
one-sixth gravity environment of the lunar surface.

The principle payload consisted of test equipment aimed at furthering
the understanding of industrial-scale lunar resource extraction
processes. A team from Carbotek Development Laboratories of Houston,
Texas and Shimizu Corporation of Tokyo, Japan constructed a
"fluidized-bed" reactor to investigate the interactions of solids and
gases in a lunar gravity environment. Fluidization -- the rapid,
efficient mixing of fine-grained solids with reacting gas -- is one of
the most promising candidate processes for lunar oxygen extraction. In
an operational pro-duction plant, hydrogen gas would be bubbled up
through a reaction chamber containing heated lunar soil to break the
chemical bonds and release oxygen. Terrestrial fluidized bed
applications include synthetic fuel production and steel making, and the
reaction mechanics in one-g are well understood. The rules change
drastically in a lunar gravity field however, and the test apparatus'
Plexiglas reactor and standpipe allowed investigators to observe the
flow behavior of simulated lunar soil during the 30-second periods of
one-sixth gravity (1/6-g) flight.

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A second, related experiment flown by Carbotek is part of a
NASA-sponsored investigation into another potential lunar resource
extraction technique -- magma electrolysis. In this process, lunar
material would be heated beyond its melting point, around 1500º C, and
oxygen would be produced by electrolyzing the molten feedstock. Because
it will be difficult to observe the oxygen bubbles and their circulation
characteristics in a reactor filled with magma, a Plexiglas model was
constructed

using clear silicone oil to simulate the highly viscous molten rock and
steel tubes delivering nitrogen gas to simulate oxygen forming at an
anode. During the 1/6-g periods, the bubbles were videotaped for later
analysis to determine bubble size, rise velocity, and disengagement
time.

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Not all activity onboard the KC-135 had to do with equipment and
chemical processing -- other passengers were more interested in human
responses to 1/6-g. Griffin Design of Huntsville, Alabama was eager to
investigate the implications of reduced gravity on an engineering model
of their spacesuit concept called the Command and Control Pressure Suit.
Designed specifically for lunar construction and exploration, the suit
features a combined helmet-upper torso assembly allowing it to become,
in effect, a "cockpit" for lunar rovers or other equipment. A mechanical
and data interface at the mid-torso would structurally connect the
suited astronaut to these vehicles and allow commands to be issued to
vehicle systems. The suit also has a rear-entry feature to reduce the
number of seals which must be protected against lunar dust. During the
lunar gravity flight regimes, test subjects evaluated the ease of
donning and doffing the suit, engaging and disengaging the mechanical
interface, positioning feet in restraints, and general mobility.

Finally, the Flight Crew Support Division at the Johnson Space Center
prepared a series of "human factors" tests involving lifting and fine
motor tasks. Subjects stowed and un-stowed heavy objects at different
heights to

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evaluate the need or usefulness of foot restraints in 1/6-g, bolted and
unbolted equipment as rapidly as possible at different angles, and
tested their bench press and arm lift capabilities on an exercise
dynamometer. The results of these tests will aid in the design of lunar
base workstations and equipment maintenance aids.

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So what is it like to work in lunar gravity? Well, you can do push-ups
with one finger, catch spilled liquids before they hit the floor, and do
a triple-axle without even trying. Perhaps the first large structure
built on the Moon should be the Lunar Olympic Stadium.

For Additional Reading

Gibson, M.A., Knudsen, C.W., Roeger, A. (1990) \"Development of the
Carbotek Process for Lunar Oxygen Production,\" Engineering,
Construction, and Operations in Space II, Albuquerque, NM.

Griffin, B.N. (1994) \"A Space Suit for Productive and Safe
Extravehicular Activity (EVA),\" Engineering, Construction, and
Operations in Space IV, Albuquerque, NM.

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Image Catalog

**LUNOX Lunar Exploration Mission Concept**

Note: All of the following are photo-realistic computer-generated
images.

S94-27634 Cargo flights to the Moon using the Russian Energia launch
vehicle

S94-27636 An automated cargo lander delivers an oxygen production plant
to the surface of the Moon

S93-45590 Lunox plant with rego-rover and propellant tanker

S94-27631 A pressurized lunar rover is unloaded from a cargo lander

S94-27630 Lunar habit components are assembled telerobotically

S93-45585 Lunar habitat with docked pressurized rovers

S94-27632 Piloted flight to the Moon launched on a booster based on
Space Shuttle components

S93-45589 Crew lander descent

S93-45583 Pressurized surface rovers allow lunar explorers to extend
their surface range

S93-45592 Refueling ascent vehicle for the trip home

S94-27633 The lunar crew returns to Earth via parachute

**Mars ISRU Sample Return Mission**

S93-50645 MISR Vehicle on the Martian surface with deployed microrovers

S93-50647 MISR Vehicle with deployed ISRU module, captioned

**One-Sixth Gravity KC-135 Flights**

S94-28788 Carbotek/Shimizu three-dimensional fluidized bed apparatus
undergoing one-sixth gravity testing

S94-28311 Fluidized-bed reactor and standpipe during one-sixth gravity
testing. Material in the bed is glass microbeads.

S94-28815 Fluidized-bed reactor using lunar regolith simulant

S94-28797 Magma electrolysis dynamic model

S94-28308 Observation of the Magma Electrolysis cell in 1/6 gravity

S94-28312 One-sixth gravity testing of Griffin Design's Command/Control
Pressure Suit Prototype

S94-28313 Test of Griffin Design's Command/Control Pressure Suit in
docking station

S94-28323 Griffin Command and Control Pressure Suit, front view

S94-28303 Griffin Command and Control Pressure Suit showing hinged
backpack

S94-28793 Instrumented partial gravity human factors test

**New Faces, Names, and Mail Codes**

by John Connolly, jconnolly@snmail.jsc.nasa.gov

Retirements, reorganizations, and realign-ments continue to change the
face(s) of Explor-ation at NASA, and most notably at JSC. Last March the
New Initiatives Office at JSC was closed and its constituent parts
distributed within the center. The new Planetary Missions and Materials
Office within the Earth Science and Solar System Exploration Division
(ESSSED) was given the challenge of continuing its advocacy of human
lunar and Mars missions. Leaving the original Planetary Projects Office
group via retirement were Dwayne Weary, Phil Deans, and Dallas Evans. Ed
Svercek, Darrell Kendricks, Doug Peterson, Nick Lance, Heidi Glaisyer,
and David Lamar transferred to other JSC organizations. David Weaver
left NASA in July for a position in the Judicial Branch of the federal
government. The remaining PPO'ers; Nancy Ann Budden, John Connolly, Bret
Drake, Kent Joosten, David Kaplan, and Eileen Stans-bery, are now joined
with long-time exploration advocates Wendell Mendell and David McKay in
the ESSSED. The new office now allows the former Exploration Office
engineers and ESSSED scientists to work more closely with one another,
and the "materials" focus combines the talents of the JSC curatorial
office with the planetary "missions" team.

At Marshall Space Flight Center, Bill Huber and Archie Young, both of
the Program Development Directorate, retired after a com-bined 75+ years
of service. Jimmy Lee has been working as Marshall's point man for
explora-tion studies.

Stan Borowski and Bob Cataldo continue to wave the exploration banner at
Lewis Research Center and are looking at new combinations of power and
propulsion systems, such as solar electric propulsion.

Ames Research Center's Jeff Briggs and Doug O'Handley continue their
Mars endeav-ors, with focused emphasis on working with the
McDonnell-Douglas Marsokhod team, and anticipate a return to Amboy
crater some time in the near future. Finally, Mars scientist Chris McKay
was recently honored with the first Thomas Paine award.

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The accomplishments of the Apollo missions to the Moon unfolded on the
TV screens of the world almost as a given. While there were certainly
moments when things did not go as planned, for the most part it looked
easy. Of course, it wasn't that easy. Years of planning, training,
rethinking, and improve-ment had gone into those operations.

The progress made in the late 60's and early 70's was not as well
documented as one might have hoped. The space program was running so
hard that no one had the time to write down the operational lessons
learned in an organized fashion. This new catalogue reviews the Apollo
mission reports, prelimi-nary science reports, technical crew
debrief-ings, lunar surface operations plans, and various other relevant
lunar experiment docu-ments, collecting engineering and
operation-specific information. It does not focus on the science or
scientific results, but does list the purpose of the experiment and a
brief description of it. It is organized by experiment and equipment
items emplaced or operated on the lunar surface during the Apollo
missions.

Within each experiment, general infor-mation about the principal
investigator (PI) and

other contacts, experiment mass and dimensions, manufacturer, and the
mission(s) it flew on is provided. Brief descriptions of the hardware
and its purpose are included. After this, a general set of questions
that are operational in nature is applied to the experiment so that the
interaction of the crew with the experiment or hardware can be
understood. Not all questions make sense for each experiment, but a
standard battery of questions was applied to all with the idea that it
might trigger the recollection of someunique aspect of that operation.
Many experiments flew on more than one mission, and improvements were
made for the follow-on flights based on the difficulties experienced. A
cross reference to other similar experiments from Apollo or other
efforts is provided. In addition to the usual meaning of the term
"experiment," some pieces of equipment and hardware, such as the lunar
rover and some of the tools the crew had available, are included. (You
can access this information through the NCSA Mosaic application at the
address http:\\\\exploration.jsc.nasa.gov)

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The "Catalog of Apollo Experiment Opera-tions" is not great literature,
but it is a good reference on the reality of science operations on the
Moon in the past. Hopefully, it will be useful to the PIs of the future.
Interested readers can obtain a copy by contacting Jim Gooding at NASA -
JSC, Mail Code SN2, 2101 Nasa Road One, Houston, TX 77058.

Apollo Experiments and Missions

  ----------------------- ------------------------- ------------------------------------ -- -- -- -- --
  [Num-ber]{.underline}   [Surface                  [Apollo Mission]{.underline}                     
                          Experiment]{.underline}                                                    

  ----------------------- ------------------------- ------------------------------------ -- -- -- -- --

  -------- ----------------------- ------------------ ------------------ ------------------ ------------------ ------------------ ------------------
                                   [11]{.underline}   [12]{.underline}   [14]{.underline}   [15]{.underline}   [16]{.underline}   [17]{.underline}

  -------- ----------------------- ------------------ ------------------ ------------------ ------------------ ------------------ ------------------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 031    Passive Seismic         X      X     X     X      X      
           Experiment                                               

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 033    Active Seismic                       X            X      
           Experiment                                               

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 035    Solar-Wind Spectrometer        X           X             

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 036    Suprathermal Ion               X     X     X             
           Detector                                                 

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------- ------
  S 037    Heat Flow Experiment                       X      \(l\)   X

  -------- ----------------------- ------ ----- ----- ------ ------- ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 038    Charged Particle Lunar               X                   
           Environ.                                                 

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 058    Cold Cathode Gage              X     X     X             

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 059    Lunar Geology           X      X     X     X      X      X
           Experiment                                               

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 078    Laser Ranging           X            X     X             
           Retroreflector                                           

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 152    Cosmic Ray Detector                               X      X

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 198    Portable Magnetometer                X            X      

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 199    Traverse Gravimeter                                      X

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 200    Soil Mechanics          X      X     X     X      X      X
           Experiment                                               

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 201    Far UV                                            X      
           Camera/Spectrograph                                      

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 202    Lunar Ejecta and                                         X
           Meteorites                                               

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 203    Lunar Seismic Profiling                                  X

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 204    Surface Electrical                                       X
           Properties                                               

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 205    Lunar Atmospheric                                        X
           Composition                                              

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 207    Lunar Surface                                            X
           Gravimeter                                               

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  S 229    Neutron Probe                                            X
           Experiment                                               

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
  M 515    Dust Detector           X      X     X     X             

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  -------- ----------------------- ------ ----- ----- ------ ------ ------
                                                                    

  -------- ----------------------- ------ ----- ----- ------ ------ ------

  ------------------------------- -- ------ ----- ----- ------ ------ ------
  Time on Moon (hours)               22     32    33    67     71     75

  ------------------------------- -- ------ ----- ----- ------ ------ ------

  ------------------------------- -- ------ ----- ----- ------ ------ ------
  Number of EVAs                     1      2     2     3      3      3

  ------------------------------- -- ------ ----- ----- ------ ------ ------

  ------------------------------- -- ------ ----- ----- ------ ------ ------
  Duration of EVAs (hours)           2.8    7.8   9.4   18.6   20.2   22.1

  ------------------------------- -- ------ ----- ----- ------ ------ ------

  ------------------------------- -- ------ ----- ----- ------ ------ ------
  Total Traverse Length (km)         0.25   2.0   3.3   27.9   27.0   35.0

  ------------------------------- -- ------ ----- ----- ------ ------ ------

\(l\) Cable broken during deployment.

Other lunar surface equipment items considered: Lunar Rover Vehicle,
Erectable S-Band Antenna, Modularized

Equipment Transporter, TV stand, Flag, Universal Handling Tool, Dome
Removal Tool, Fuel Transfer Tool, Radioisotope Thermal Generator, Lunar
Equipment Conveyor, Cameras, Surveyor 3 Retrieval, Thermal Degradation
Sample Experiment, ALSEP -- General Information, and EASEP -- General
Information.

  ----------------------------------- ------------------------------- -- -- -- -- --
  [Microgravity                       [Apollo Mission]{.underline}                
  Experiment]{.underline}                                                         

  ----------------------------------- ------------------------------- -- -- -- -- --

  ------------------------------------- ------------------ ------------------ ------------------ ------------------ ------------------ ------------------
                                        [11]{.underline}   [12]{.underline}   [14]{.underline}   [15]{.underline}   [16]{.underline}   [17]{.underline}

  ------------------------------------- ------------------ ------------------ ------------------ ------------------ ------------------ ------------------

  ------------------------------------- ----- ----- ----- ----- ----- -----
  Composite Casting Demonstration                   X                 

  ------------------------------------- ----- ----- ----- ----- ----- -----

  ------------------------------------- ----- ----- ----- ----- ----- -----
  Electrophoresis Demonstration                     X           X     

  ------------------------------------- ----- ----- ----- ----- ----- -----

  ------------------------------------- ----- ----- ----- ----- ----- -----
  Heat Flow and Convection                          X                 X
  Demonstration                                                       

  ------------------------------------- ----- ----- ----- ----- ----- -----

  ------------------------------------- ----- ----- ----- ----- ----- -----
  Light Flashes Experiment              X     X     X     X     X     X

  ------------------------------------- ----- ----- ----- ----- ----- -----

  ------------------------------------- ----- ----- ----- ----- ----- -----
  Liquid Transfer Demonstration                     X                 

  ------------------------------------- ----- ----- ----- ----- ----- -----

![](media/image30.pct){width="3.138888888888889in"
height="2.763888888888889in"}

![](media/image31.pct){width="3.138888888888889in"
height="2.0694444444444446in"}