Lunar Base Architecture and Operations Proposal

Jamestown Moon Base (JMB)
Architecture and Operations Proposal
for
ASTE 524 Human Spaceflight
USC Viterbi School of Engineering
Department of Astronautical Engineering
Group 7: Nicholas Borquez, Max Donovan, Thomas Perkins
Edward Proulx, David Torre
Submitted: December 13, 2019

Jamestown Moon Base N. Borquez, M. Donovan, T. Perkins, E. Proulx, D. Torre
Architecture & Operations Proposal FINAL VERSION
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1. Needs, Goals, & Objectives
1.1. Needs
1.1.1. Reduce the possibility of extinction by expanding humanity’s presence beyond LEO.
1.1.2. Conduct research to improve our understanding of the solar system and our place in it.
1.1.3. Create new space-based industries and economic frameworks for the benefit of
humanity.
1.1.4. Improve international diplomacy through continued cooperation in commercial and
scientific space endeavors.
1.2. Goals
1.2.1. Establish and retain a human presence on the lunar surface. (Parent 1.1.1)
1.2.2. Learn how to build and operate an extraterrestrial crewed facility. (Parent 1.1.1, 1.1.3)
1.2.3. Further explore the geography and history of the Moon. (Parent 1.1.2)
1.2.4. Develop increased capacity to conduct science and research on the Moon for
applications within the solar system and beyond. (Parent 1.1.2)
1.2.5. Develop requisite technological and logistical capability to continue deeper exploration
of the solar system. (Parent 1.1.2, 1.1.3)
1.2.6. Develop material extraction, refining, and manufacturing capability to expand the
economic activity of humans beyond Earth. (Parent 1.1.3, 1.1.4)
1.3. Objectives
1.3.1. Develop technology and practices to keep humans safe on the lunar surface. (Parent
1.2.1, 1.2.5)
1.3.2. Create a surface habitat that supports a permanent rotational presence of four crew
with surge capacity to eight crew during crew changeover periods. (Parent 1.2.1)
1.3.3. Provide and maintain sufficient resources and consumables to support a resupply
interval of three months. (Parent 1.2.1)
1.3.4. Create a reusable landing pad within 3 km to the base habitat and associated
infrastructure to support crew rotation, spacecraft refueling and maintenance. (Parent
1.1.1, 1.2.2, 1.2.5)
1.3.5. Develop methods and technologies to support a closed cycle life support system.
(Parent 1.2.1, 1.2.2, 1.2.5)
1.3.6. Develop methods and technologies to utilize in situ resources (ISRU) for life support,
propellant, and manufacturing applications. (Parent 1.2.5, 1.2.6)
1.3.7. Conduct lunar surface exploration to learn more about the formation of the moon and
conditions present in the early solar system. (Parent 1.1.3, 1.2.4)
1.3.8. Deploy a rover capable of transporting up to 6 crew members to a range of 50 km for
launchpad transfer and LSE (Lunar Surface Excursion) operations. (Parent 1.2.1 - 1.2.6)
1.3.9. Deploy unmanned rovers for exploration and surface utilization. (Parent 1.2.3, 1.2.4)
1.3.10. Deploy communications and observation satellites capable of providing continuous
coverage of all mission areas and assets. (Parent 1.2.1, 1.3.3, 1.2.4, 1.2.5)

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2. Site Selection
2.1. Location (1.2.3, 1.2.4, 1.2.6)
The JMB will be located near the South Pole on the lunar surface in the Amundsen
crater at 84.6°S, 85.6°E. Landing sites in the South Polar Region (SPR) meet the
requirements of the Diana DRM, support scientific exploration, and provide ready
access to in situ resources. The Amundsen crater, in particular, provides a large open
area, a consistent temperature profile, radiation protection, uniform flat topography for
ease of exploration, and an abundance of volatile compounds. Material contained in
these regions will serve as vital resources for future economic development and will
likely reveal new details of lunar history.
2.2. Scientific Value (1.3.7)
One of the primary driving factors for site selection is the scientific value it provides.
Orbital survey missions, including NASA’s Lunar Prospector Mission, have identified
significant concentrations of hydrogen in both the North and South Pole regions.
Amundsen crater in the SPR is considered a first choice candidate[2-1] to both discover
and study lunar volatiles due to its size and easily accessible shadowed areas. Of the
South Polar craters, the Amundsen crater with 90-126 ppm hydrogen[2-1] is one of the
largest, at about 105 km in diameter. The crater contains both sunlit areas and PSRs
(Permanently Shadowed Regions), with approximately 9% of the crater in permanent
shadow[2-1]. Because of its relatively large PSR area, Amundsen presents the lowest
average surface temperatures of the large craters in the SPR (37-43 K), which positively
correlates with volatile concentrations. Other considered sites for exploration included
Shackleton crater and Cabeus crater, with diameters of 21 km and 98 km, respectively.
The Shackleton crater presents steep rim slopes, with about 35-40°[2-2] slopes and deep
regolith deposits, making it favorable for volatile exploitation but unfavorable for
landing space and vehicle traverses[2-3]. In comparison, the floor of Cabeus crater is
relatively flat, but has an average temperature of 46 K, thus making it less attractive for
volatile studies. Due to these reasons, these locations are less optimal for surface
missions than Amundsen crater.
2.3. Logistical Value (1.3.6, 1.3.7)
The JMB will be located on the fringe of a PSR to avoid intensely cold environments,
while PV (photovoltaic) panel farms will be located in nearby sunlit regions, providing
power supply for ISRU and JMB operations. The surface area of the crater is attractive
because it provides sufficient space for a landing zone, lunar base, and exploration and
exploitation missions. In addition, relatively flat terrain (<5° slope) and shallow sloped
walls make the Amundsen crater more suitable for surface vehicle travel. A larger crater
floor provides safety margin for landing and allows for locating the landing pad in a
sunlit area to provide visual confirmation of the pad condition.
2.4. Solar Storm Event Radiation Protection (1.3.1)
Chronic exposure to ionizing radiation from galactic cosmic rays and solar energetic
particles pose a serious hazard to both crew and equipment on long duration space
missions. The geographic location and orientation of the JMB site relative to the Sun will

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provide built-in radiation shielding. If JMB was located outside of a crater, it would be
exposed to solar radiation and solar storm events throughout the lunar day, thus
requiring additional shielding mass, which would increase the overall cost of the
mission. Bounded by sloped walls (<25°)[2-4], the northern PSR of Amundsen crater
provides JMB with permanent protection from solar radiation.
Figure 2.1: JMB Proposed Site Selection
3. Base Layout and Crew Accommodations
3.1. Base Functionality (1.3.1, 1.3.2, 1.3.4, 1.3.5)
The base will provide pressurized areas to meet all crew living and working needs. This
includes providing designated areas for: sleeping, exercising, recreating, scientific
experimentation, medical procedures, hydroculture food growth, and electrical,
mechanical, and life support systems. Unpressurized pods will additionally be located
around the base for vehicle storage and maintenance, material storage, and ISRU
processing.
3.2. Base Modules and Layout (1.3.1, 1.3.2)
The JMB crew habitat will consist of a series of interconnected modules. Inflatable
modules will be used in the construction of the JMB, which will ease expansion and
minimize payload mass. There will be three standard module sizes: 4.6x4.6x2.6 m, 2.3x
4.6x2.6 m, and 2.3x2.3x2.6 m, known respectively as quad, transverse, and cube. Each
module will have at least one connection to an adjacent module via a universal locking
adapter that includes systems connections and a crew hatch. Modules will be classified
as Operations, Habitation, Logistics, or Hydroculture (see 4.5) modules. JMB will be
placed near the edge of a PSR within Amundsen crater with the airlocks oriented
towards the edge of the PSR and the crew berths and hydroculture mods oriented away

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from the edge. JMB modules will be partially covered by regolith, with sleeping pods
and hydroculture modules receiving the deepest coverage.
3.2.1. Operations Modules (1.3.6, 1.3.7): The OMods will provide space for the crew to
operate the base and conduct day to day work. OMods will be used for
communications, surface operations control, internal base monitoring, scientific
experiments, and data analyses. OMods will also contain provisions for cleanroom
environments to support electronic, chemical, and biological research.
3.2.2. Habitation Modules (1.3.2) (HMods): HMods will include both living and sleeping
quarters for the crew. The large central module will contain a kitchen, dining room, and
living room area. Each sleeping module will consist of two-fold down bunks mounted to
the wall. A multi-purpose recreation module will be provided for use during crew
downtime. A health module will be provided that includes exercise equipment, crew
health monitoring capabilities, pharmaceuticals, and medical equipment. Two cupolas
will be mounted atop the main living habitat modules in order to provide crew viewing
capacity and combat the psychological effects of long-term habitation in an enclosed
space. Cupola modules are required because the base will otherwise be covered by
regolith for radiation protection.
3.2.3. Logistics Modules (LMods) (1.3.3, 1.3.5, 1.3.6, 1.3.8, 1.3.9): JMB LMods include the
airlocks, Equipment Lock, Power Plant, mechanical systems, ISRU, and vehicle hangar
modules. The airlocks will be used for surface access and LSMU (Lunar Surface Mobility
Unit) donning/doffing and decontamination. The Equipment Lock will be used for LSMU
and other LSE equipment storage and maintenance. A 50 MW nuclear reactor with
separate high and low voltage supplies will provide sufficient power for life support,
scientific operations, and heavy machinery[3-1]. The Power Module will be connected to
a high capacity battery system that will balance available power with demand at any
given time. Nuclear power will be supplemented by PV panel farms constructed from
ISR silicon and other materials. The Mechanical Systems LMod houses the functional
components of the life support and power distribution systems. The ISRU LMod is an
unpressurized module that houses reactors necessary for processing and refining
regolith into needed materials (see 4.2). The Vehicle Hangar module will also be
unpressurized and will berth all vehicles between surface operations. Conveyor systems
will transfer ISR raw materials from vehicle berths to the ISRU LMod.
3.3. Launchpad Complex (1.3.3)
3.3.1. Landing Pad: The JMB landing area will support launch operations as well as spacecraft
maintenance. The site will be expandable to support a higher launch cadence as
required. The pad will have a total diameter of 30 m, to support the planned size of the
landing vehicle with margin. The Launchpad Complex will be located at least 500 m from
the JMB habitat in a partially illuminated zone. Locating the pad 500 m from the main
habitat provides protection from kicked up regolith and debris from Rapid Unplanned
Disassemblies[3-2]. The launchpad surface will be able to support the mass of the landing
vehicle with 5000 kg of cargo during a resupply landing. The CELST (5.3.5) rover will be
used to transport supplies and crew to and from the landing pad and the JMB habitats.

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Figure 3.1: JMB Layout Schematic

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3.3.2. Ship Repair and Maintenance: Jamestown’s Launchpad LMod (not depicted in the base
layout diagram) will provide necessary equipment and materials needed to conduct
routine maintenance (including visual inspections) of both the spacecraft and surface
vehicles. This module will consist of pressurized and unpressurized spaces accessible by
crew. The unpressurized space will allow crew to effect maintenance and repairs on
large equipment while in LSMUs. Numerically controlled additive and subtractive
machining equipment and manual workspace will be available in a pressurized section.
4. ECLSS Architecture / CELSS Overview (1.2.1, 1.2.2, 1.2.5)
The JMB will employ a modular closed-loop regenerative ECLSS architecture (ref Fig 4.1),
also referred to as a Controlled Ecological Life Support System (CELSS)[4-1]. Due to
logistical constraints that are imposed by the energy required to move material out of
the Earth’s gravity well, the goal of the system is to minimize losses and required
consumable inputs associated with resupply missions. In the JMB CELSS architecture,
plants contained in a growing module will produce food for the crew, take in CO2
produced by the crew and simultaneously produce O2 for both crew respiration and use
in oxidizing waste materials. Plant matter will also produce water vapor, which will be
condensed, collected and used to supply the crew's water needs. Crew waste products
will be recycled by the waste processing system for subsequent use as nutrients by the
crop plants.
4.1. Atmospheric Composition and Pressure (1.3.4)
The JMB will provide an atmosphere of 29.5% Oxygen by volume and 70.5% Nitrogen by
volume at pressure of 8.4 psia[4-2]. In totality, four factors influenced the selection of this
atmospheric composition and pressure: hypoxia, hyperoxia, fire risk and decompression
sickness risk. This selection accounts for each of them and appropriately weights the
risks associated with them. Specifically, this pressure and composition compromise will
minimize LSE pre breathe time to facilitate frequent LSE operations while also
controlling fire risk and providing an environment that supports human physiological
needs.
4.2. Provisioning of Atmospheric Makeup Gases and other Elements (1.3.5)
Gases required for establishing and maintaining a breathable atmosphere on the lunar
surface in the JMB consist primarily of Oxygen and Nitrogen. While use of CELSS
architecture should minimize losses of these elements, slow rates of attrition will be
present from minute leakages and losses associated with LSEs. Oxygen is readily
abundant in lunar regolith and will be extracted from a variety of sources including
Ilmenite[4-3]. Water for hydration, hygiene, food preparation and medical procedures will
be derived from ISRU processing. Nitrogen, while present in some regolith, is not
significantly available[4-4] and will have to be brought to the lunar surface by regular
resupply.

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Figure 4.1: ECLSS Concept Schematic

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4.3. Atmosphere Gas Balancing (1.3.1, 1.3.4)
Air component partial pressures will be balanced by the CELSS to support crew and
hydroculture needs. Excesses of O2 or CO2 will occur due to imbalances between crew
and plant respiration rates. CO2 levels will be kept under 0.5% for pressurized habitat
modules.[4-5] O2 levels will be held within a tolerance of partial pressure as described in
section 4.1. Excess CO2 will be removed and stored via CO2 Removal Assembly.[4-6] If an
excess of O2 occurs, partial atmosphere will be removed, separated and recycled via
cryogenic air separation, and then makeup gases will be reintroduced. Excess stowed
CO2 will be converted to CH4 by a CO2 Reduction Assembly utilizing the Sabatier
Reaction.[4-6] Individual LiOH scrubbers will be available for contingencies in the case of a
major CELSS component failure. Any system overcapacity of gasses can be vented as a
contingency.
4.4. Temperature, Ventilation, and Humidity Control (1.3.1, 1.3.2)
A centralized air distribution system will regulate temperature, humidity, and airflow
throughout the base in tandem. Heat will be provided by routing air through a heat
exchanger that is coupled to the primary power plant cooling exchanger. Cooling will be
selectively provided by routing air next to externally exposed thermal radiator fins[4-7].
Humidity control will be effected by selective use of an evaporative humidifier
downstream of the heat exchanger. Humidity removal will be effected by heat
exchanger condensation. Condensation will be collected in drainage pathways and
routed to the evaporator reservoir, which will discharge water into the main water
recycling system.
4.5. Food production (1.3.4)
The JMB CELSS will contain expandable plant and animal growth units for the
production of a nutritionally adequate diet. This diet will be supplemented with multi-
vitamins and a periodic resupply of food from Earth for nutritional variety to increase
crew morale. These gardens will consist of three quad size hydroculture modules.
Within each hydroculture module, tank units will be tiered vertically 3 high with the
bottom layer will be hydroponic and the upper two aeroponic. This arrangement will
support approximately 30 m² of growing area per crew member[4-8]. Lighting in each
growing area will be optimized for photosynthesis of that crop. Use of hydroculture
supports the JMB CELSS closed loop architecture for food and O2 production and directly
helps to minimize resupply requirements.
4.6. Waste Product Recycling (1.3.4)
Crew solid and liquid waste products, gray water, hydroculture biowaste, and CRA
produced methane will be processed by a multistage oxidation and filtering system.[4-8]
Water will be separated from solids then filtered and recycled into a central base supply
reservoir. Resultant solids will be processed in a bioreactor and converted into fertilizer
suitable for aeroponic/hydroponic use.

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5. Surface Exploration Concept of Operations
5.1. Surface Exploration Operations (2.3.7)
5.1.1. Site Exploration: Surface exploration will begin by identifying potentially viable target
areas and material sites. The intent of this reconnaissance will be to support the
development of ISRU capabilities and further scientific study. Resource locations will be
prioritized by size, quality, and range. Features of scientific interest including impact
sites and unusual surface or mineralogic features will be identified. Once areas are
identified, SAMOV (6.3.3) rovers will investigate potential high value sites sites. The non-
crewed operational radius for these missions will be limited only by RCom (6.3.1)
coverage and terrain compatibility. Sites requiring complex operations will be
investigated by crewed LSE with CELST (6.3.5) transport. The operational radius for
CELST LSE survey missions will be governed by EMU capability and terrain compatibility.
5.1.2. LSE Data Management: Data recorded during surface investigations will be uploaded in
real time to EMC and allied partners. Specific channels will be sent to the JMB for
mission execution. Similarly, CELST and EMU telemetry/data will be broadcast to both
EMC and JMB in real time. Full sensor data will be stored on LSE asset local storage that
will be transferred to the JMB network for full analysis at the conclusion of an LSE.
5.1.3. Surface sample stowage and disposition: Surface samples will be classified for mission
value and dispositioned as retain, return, or dispose. All samples will have permanent
records of 3D scan data, spectroscopy, and additional sensors/scientific readings. At no
time will a surface sample be exposed in an uncontrolled fashion to the habitat module
atmosphere.
5.2. In Situ Resource Utilization Operations (1.3.6)
5.2.1. ISRU Capability Development: Because the technology for resource exploitation is at
varying levels of maturity, the continued success of the overall mission will not be
dependent on successful ISRU. However, the Jamestown Mission will attempt to
identify, classify, extract, refine, and utilize in situ resources within operational range.
5.2.2. ISR extraction / processing: Resources within crewed operational radius of sufficient
size will be extracted via SEU (5.3.6). Due to its size and complexity, each SEU will be
installed via crewed LSE mission with SAMOV (5.3.3)/FARLOV (5.3.4) support as needed.
Once installed, the SEU will perform autonomous resource extraction and break down
the material into an acceptable form factor for transport to the LMod. Resource sites of
lower capacity that are outside crewed radius will be extracted via FARLOV. Recovered
material will be autonomously sorted and processed into finished products at the
appropriate LMod (e.g. via electrolysis reactor).
5.2.3. ISRU Applications:
H2O and Volatiles: Hydrogen-bearing compounds are present in trace amounts in lunar
regolith and surface ice deposits have been found in polar regions. ISRU hydrogen will
be used for life support, fuel production, chemical synthesis, and radiation shielding.
Metallic Bearing Regolith: Elements in surface regolith include silicon, iron, aluminum,
magnesium, titanium, calcium, and oxygen[5-1]. These metals will be used for fabricating
module and vehicle components, crew equipment, and surface infrastructure (including

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power distribution[5-2]). Silicon will be used for manufacturing of photovoltaic cells and
for hydroculture. Molecular oxygen can be used for life support, fuel, and chemical
synthesis. Other Applications: In addition to the above, powdered aluminum with water
ice (ALICE) is a potentially effective propellant[5-3].Unprocessed regolith can be used in
base module construction as an effective radiation shield[5-4].
5.3. Surface Operation Assets (1.2.5)
5.3.1. Roanoke Communications Satellites (RCom)(1.3.10): A network of small, multiband,
high-capacity communication satellites. The RCom constellation will maximize uptime
via high eccentricity polar orbits with at least two redundant units. All mission assets will
have constant two-way links with RCom, and RCom will have a constant link with EMC.
5.3.2. Jamestown Survey Orbitor (JSO)(1.3.10): At least one imaging satellite will be in low
polar orbit and will include visible and near visible spectrum cameras, laser range
finding, and X-ray spectrometer.[5-5] In addition to scientific and resource survey
support, JSO will provide detailed (resolution = ~0.2 m) 3D topographical mapping data
of the JMB operational area for autonomous vehicle navigation.
5.3.3. Semi-Autonomous Modular Operations Vehicles (SAMOV)(1.3.9): This vehicle is a small
long range rover designed to support general surface operations including site survey,
sample collection, surface science, and LSE mission support. Each SAMOV will have a
flexible modular framework to allow for application-specific equipment loadouts. The
survey module will have a suite of sensors for site investigation including optical (wide
and narrow angle), thermographic, range-finding, and spectrographic sensors.
5.3.4. Fully Autonomous Resource Logistical Operations Vehicles (FARLOV)(1.3.9): This
vehicle is designed to support ISRU Operations; transport ISR products and provide
diagnostic and maintenance support for SEUs. Each FARLOV will be equipped with a
material holding bin with retractable cover, articulating scoop arms, and an articulating
multi-end effector arm. FARLOV rovers will be utilized to provide regolith coverage over
habitat modules.
5.3.5. Crew / Equipment Lunar Surface Transport (CELST)(1.3.8): As the primary crew mobility
vehicle, the CELST will have six seat locations, four of which are capable of being
removed to accommodate other equipment (such as a stretcher). The CELST can be
configured for either launchpad transport or LSE capability. In pad transport mode, the
cabin will be pressurized and seats compatible with crew escape suits will be installed.
In LSE mode, the cabin will be unpressurized, and seats compatible with LSMUs will be
installed. The main hatch of the CELST will include an airlock mating adapter. The CELST
will include advanced self-driving capability. Roadside assistance not available in all
areas.
5.3.6. Site Extraction Unit (SEU)(1.3.5): The SEU is a portable, field installed unit that can
extract and perform raw processing of ISR material. Each SEU is designed and configured
for a particular source and material type. The maximum dimensions of the SEU will be
determined by its compatibility for loading into the CELST (in LSE mode). All SEUs will
have data links, and except for those in PSRs, all will have PV generation capability.

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Figure 5.1: Surface Exploration Concept of Operations

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Figure 5.2: ISRU Exploration Concept of Operations

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6. Surface Operations Rules and Procedures (1.3.1)
6.1. Surface Operation Flight Rules
6.1.1. Lunar Surface Excursion Decompression Event: No LSE crew member shall be further
than 30 seconds of LSMU travel time from their partner during a LSE. This time accounts
for 30 seconds of uncontrolled decompression where the LSMU is compensating for a
loss of environment and allows the partner crew member 30 seconds to get to the crew
member with a damaged suit and provide assistance prior to the damaged suit running
out of consumables. The crew will additionally be required to stay within 2 minutes of
LSMU travel time from the CELST. All LSE crew must carry a LSMU leak patch kit in their
equipment pouch. Patch kits will be effective on any leak on a LSMU of less than 15 cm
in length. Patch kit application time will not exceed 30 seconds. If a leak cannot be
patched, the LSE will activate CELST emergency pressurization and return to JMB
immediately.
6.1.2. Lunar Surface Excursion Scientific Sample Control: Lunar surface sample materials will
not be exposed to direct human contact. Materials will always be segregated in a
vacuum environment unless being processed for a controlled experiment. Sample
containers will be cleaned, inspected, catalogued, and routed via an autonomous
handling process after entering the airlock. Samples not in use will be stored in the
unpressurized LMod and will be retrievable by drone.
6.1.3. Lunar Surface Excursion Loss of Communications: In the event of a communications
blackout between crew conducting a LSE and the JMB, crew will cease LSE activities
following a period of not more than 10 minutes. If direct communication (LSE to JMB) or
indirect communication (LSE to EMC to JMB) is reestablished within 10 minutes, LSE
activities may be resumed at the discretion of the LSE leader. Otherwise, the LSE leader
will establish visual communication with the LSE follower and attempt to troubleshoot
the communications failure. Both the JMB and Earth Mission Control will also attempt to
reestablish communications.
6.2. Airlock Control & Operations (1.3.1)
6.2.1. Airlock Depressurization Procedure
1. Open inner airlock hatch to airlock. (In Emergency: performed by other crew)
2. Enter airlock with LSE partner and equipment (as required).
3. Close inner airlock hatch (In Emergency: performed by other crew)
4. Don LSE suit as presented on umbilical rack in airlock.
5. Visually inspect LSE partner’s suit. (In Emergency: abbreviated checklist or skip)
6. Don helmet, connect tool pouch to suit, pressurize suit.
7. Detach suit from internal life support umbilical, close suit rack cover.
8. Partially depressurize airlock for Confidence check. (In Emergency: skip this step)
9. Conduct final suit checkout (leaks, power, life support, comms, visibility) with LSE partner. (In
Emergency: skip this step)

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10. Fully depressurize airlock. Check airlock for proper configuration.
11. Open outer hatch and register time with Mission Control.
12. Egress airlock with LSE partner. Close outer hatch upon exit. (E-mode: hatch to be closed remotely
by crew in JMB)
6.2.2 Airlock Pressurization Procedure
1. Open external hatch. (In Emergency: hatch to be opened remotely by crew in JMB)
2. Enter airlock with LSE partner.
3. Connect suit to internal life support umbilical.
4. Equalize pressure in suit to match base pressure. (E-mode: steps 2 & 3 simultaneous)
5. Pressurize airlock. (In Emergency: steps 2 & 3 simultaneous)
6. Verify pressure inside airlock matches pressure in suit.
7. Disconnect the umbilical.
8. Perform airlock self-clean procedure. (In Emergency: skip step)
10. Reconnect the umbilical for suit stowage, take off the suit and hang up on service rack. (In
Emergency: skip step)
11. Open inner airlock hatch.
12. Egress airlock to base with LSE partner. Close inner hatch to base. (In Emergency, skip closing
hatch.)
Figure 6.1: Airlock Controls Schematic

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7. References
[2-1]
Thomas Marshall Eubanks, “Amundsen Crater: Access To Lunar Volatiles And Sunlit Areas On A Level
Plain”, Cleveland, Ohio, 2011, Oral
[2-2]
James J. Zakrajsek et al, Exploration Rover Concepts and Development Challenges, Glenn Research
Center, Cleveland, Ohio, 2011
[2-3]
J. E. Gruener, D. B. Bussey , S. J. Lawrence , and L. S. Mason, Polar Volatiles Exploration In Peary Crater
Enabled By Nasa's Kilopower Project, NASA Glenn Research Center (21000 Brookpark Rd, Cleveland, OH,
44135)
[2-4]
The National Research Council, Division on Engineering and Physical Sciences, Space Studies Board,
Committee on the Scientific Context for Exploration of the Moon, The Lunar Poles Are Special
Environments That May Bear Witness to the Volatile Flux Over the Latter Part of Solar System History,
Washington, DC, 2006
[3-1]
Brumfiel, G., “Miniaturized Nuclear Power Plant? U.S. Reviewing Proposed Design” NPR. National
Public Radio, Web, 13 January, 2017
[3-2]
National Aeronautics and Space Agency, “NASA’s Recommendations to Space-Faring Entities: How to
Protect and Preserve the Historic and Scientific Value of U.S. Government Lunar Artifacts”, NASA, 20 July,
2011
[4-1]
Schlacht, I. L., et al, “Space Analog Survey: Review of Existing and New Proposal of Space Habitats with
Earth Applications”, 46th International Conference on Environmental Systems, 10-14 July 2016, Vienna,
Austria
[4-2]
Lange, K.E., et al, “Bounding the Spacecraft Atmosphere Design Space for Future Exploration
Missions”, Jacobs Sverdrup ESC Group, June 2015, Houston, Texas
[4-3]
Allen, C. C., R. V. Morris, and D. S. McKay 1996. Oxygen Extraction from Lunar Soils and Pyroclastic
Glass. J. Geophys. Res. 101. 26,084-26,095.
[4-4]
Füri, E., Barry, H., Taylor, L., Bernard, M., “Indigenous nitrogen in the Moon: Constraints from coupled
nitrogen-noble gas analyses of mare basalts”, Earth and Planetary Science Letters, 1 October 2015
[4-5]
James, J., Macatangay, A., “Carbon Dioxide - Our Common Enemy”, SAMAP Submarine Air Monitoring
Air Purification Conference, 19 October 2009, San Diego, CA
[4-6]
Murdock, K., “Integrated Evaluation of Closed Loop Air Revitalization System Components”, NASA/CR -
2010-216451, November 2010
[4-7]
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