Master of Science in Space Architecture

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Manned Mars Mission

• Master of Science in Space Architecture
• University of Houston
• Gerald D. Hines College of Architecture
• Sasakawa International Center for Space
  Architecture
• www.sicsa.uh.edu
  16 April 2004

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Mars Mission Designers

• Mehwash Abbas (B. Arch)
• Nirmal Gandhi (B. Arch)
• Marlo Graves (MSSA, Boeing)
• Derrick Kately (B. Arch)
• Daniel Luna (MSSA, UH)
• Christie Matthew (MSSA, USA)
• Carl Merry (MSSA, USA)
• Robert Morris (MSSA, UH)

• Peter Obeck (M. Arch)
• Hung Phan (B. Arch)
• Kris Romig (MSSA, NASA)
• Greg Scott (MSSA, USA)
• Nick Skytland (MSSA, NASA)
• Nikki Smith (MSSA, USA)
• Scott Stover (MSSA, USA)
• La Tosha Wallace (B. Arch)

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Mars Mission Overview

• Mission Statement and Objectives
• Support/Common Elements
• Mission Elements
• Mission Architecture

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Mission Statement

• To successfully establish a human presence on the
  surface of Mars. This includes developing the
  required infrastructure for the journey to and
  exploration of the Red Planet.

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Primary Objective

• Successfully transport and land a human crew on
  the surface of Mars and return them safely to
  Earth.

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Secondary Objectives

• Search for aqueous environments and signs of past
  and present life on Mars.
• Test and utilize advanced engineering,
  scientific, and operational concepts.
• Further international and commercial cooperation
  developed within existing space programs.
• Promote new business opportunities allowing
  companies to expand into the space industry.
• Return samples of Martian material to Earth for
  detailed analysis.

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Support/Common Elements

• Adaptive Translational Landing Structure (ATLaS)
• Androgynous Docking Attachment Mechanism (ADAM)

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Adaptive Translational Landing Structure (ATLaS)

• Provide deorbit and landing for large (150,000
  kg) Mars surface modules
• 900 m/s Dv via Four LO2/LH2 main engines
• ACS system for attached modules

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Adaptive Translational Landing Structure (ATLaS)

• Dimensions
• Height 11m (36ft)
• Diameter 13m (42ft)

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Androgynous Docking and Attachment Mechanism
(ADAM)

• Connect pressurized modules
• Androgynous Self-compatible
• Automated power, data, and fluid connections
  Provides connectivity for the transfer of
  utilities between modules
• Four deployable coarse alignment guides

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Androgynous Docking and Attachment Mechanism
(ADAM)

• Dimensions
• Overall Diameter
• 2.5m (8ft)
• Hatchway
• 1.25m x 1.25m
• (4ft x 4ft)

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Mission Elements

• Kepler Launch Vehicle
• Mars Information Infrastructure (MII)
• Transfer Propulsion Module (TPM)
• Consumable Resupply and Apparatus Transfer
  Element (CRATE)
• Power Module (Power)
• Mars Habitation Module (MarsHab)
• Transfer Habitation Module (TransferHab)
• Crew Transfer Vehicle (CTV)
• Mars Laboratory Module (MarsLab)

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Kepler Launch Vehicle

• Vehicle Mission
• Launch elements to LEO
• Vehicle Design
• 4 LO2/LH2 main engines
• 4 Solid Rocket Boosters (SRBs)
• Payload Capacity
• Fairing dimensions 14m (45ft) diameter by 20m
  (65ft) high
• 150 metric tons (t) to LEO

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Launch Vehicle (Kepler)
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Mars Information Infrastructure (MII)

• Function
• Provide high-bandwidth, global communications
• Perform weather monitoring
• Supply precision global navigation
• Provide high-resolution remote-sensing

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Mars Information Infrastructure (MII)

• Design Mars
• Areosynchronous communications/weather
  constellation
• Optical relay capability
• Semisynchronous navigation constellation
• Cross-link communications
• Low Mars Orbit Polar Observation Platform
• Autonomous Remote Ground Stations

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Mars Information Infrastructure (MII)

• Design Earth
• Geosynchronous pair
• Receives optical signal and relays to ground via
  radio link
• Single ground station
• Receives and distributes data to proper centers
• Capable of receiving optical directly

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Transfer Propulsion Module (TPM)

• The workhorse vehicle for this architecture.
• Responsible for transferring all of the elements
  to and from Mars.
• Uses nuclear plasma engines which provide
  continuous thrust to and from Mars
• Reduces the travel time from 8-9 months with
  chemical propulsion to lt90 days
• High power requirements 15 MW

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Transfer Propulsion Module (TPM)

• Sized for 9 km/s of delta V
• H2 propellant launched separately as H2O
• Three nuclear plasma engines
• Three 5 MW nuclear reactors
• Water electrolysis provides O2 and H2
• RCS
• Refueling of CTV
• ECLSS O2

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Transfer Propulsion Module (TPM)

• Must dock with and retract TransferHab into
  itself
• As TransferHab is retracted, the engines and
  Translational Nacelle Trusses (TNTs) are deployed
  
• Propellant tanks provide radiation protection
• Must dock with MarsHab and CRATE, which are not
  retracted
• Provide primary power to docked vehicles
• Provide all attitude control, avoidance
  maneuvering, and main propulsion for attached
  modules

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Transfer Propulsion Module (TPM)
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Consumable Resupply and Apparatus Transfer
Element (CRATE)

• Provides transportation of logistics and Power
  module to Mars surface, via ATLaS
• Provides pressurized and unpressurized volumes
• Mechanisms are integrated into shell
• Cranes, ramps, etc

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Power Module (Power)

• Provide primary power on the Martian surface
• Redundant nuclear reactors producing 2MW peak
• Unmanned mobile located 0.5km from habitable
  modules
• Power distribution options
• Wired connection
• Wireless power transmission (WPT)

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Power Module Image
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Mars Habitation Module (MarsHab)

• Provide habitation for the crew while on Mars
• 14m (45ft) diameter, 13m (41ft) tall, not
  including ATLaS
• 3 levels sleeping/galley, science labs, and
  EVA/docking
• Food/water/shelter for 1 year design

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Mars Habitation Module (MarsHab)

• Utilizes ATLaS for precise module positioning
• Ramp provides surface access for crew and rover
• Dual-airlock system
• Module docking with ADAM
• Crew EVA for surface missions

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MarsHab, tractor tanks
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MarsHab lowered to surface
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MarsHab workstations
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MarsHab sleep stations
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TransferHabVehicle Requirements

• Support the crews needs including consumables,
  medical supplies, and radiation shielding for
• Nominal 3 month transfer from GEO to MMO
• Nominal 3 month transfer from MMO to GEO
• Contingency 1 year non-optimal return
  trajectories
• Interface with TPM and fit within the tanks
• Provide a pressurized docking interface with a
  minimum of two vehicles.

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TransferHabVehicle Description

• Crew Accommodations sleeping stations, galley,
  crew life support equipment and consumables,
  recycling capabilities, crew hygienic supplies
  and equipment, and entertainment
• Science payloads to study of low-g orbital
  transfer environment

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TransferHabVehicle Design

• Rack system
• Systems and payloads designed into racks to
  facilitate equipment replacement and to provide
  internal configuration flexibility
• Three sections
• Two sections split into 2 decks
• Each deck has a cross-section of 8 racks and 6
  stand-offs

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TransferHabZenith Deck
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TransferHabNadir Deck
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TransferHabVehicle Design

• Dimensions
• Diameter 7.5 m
• Length 23 m
• 2 sections _at_ 9.2 m
• 1 section _at_ 4.6 m
• Corridors
• 2 m X 4.5 m
• Hatchways
• 1.25 m X 1.25 m
• Internal Volume
• 885 m3 (including rack structure and internal
  bulkheads)

• Rack Layout
• 24 Systems
• 8 Propulsion
• 16 Crew Quarters
• 6 Hygiene
• 13 Medical/Exercise
• 4 Galley
• 5 Study/Work Area
• 42 Science/Stowage
• Total 118

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TransferHab Cross-section
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TransferHab, shell removed
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Ward Room
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Crew Quarters
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Hygiene Facility
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Crew Transfer Vehicle (CTV)

• Vehicle Mission
• Transfer crew and payloads
• From Earth surface to TransferHab in GEO and back
• From TransferHab in MMO to Mars surface and back
• Vehicle Design
• Provide pressurized space for 8 crew and limited
  payloads
• Reusable ballistic vehicle (integrated capsule
  and lander)
• Nominal 5 day mission (contingency for 10 days)
• Complete vehicle re-pressurization (no airlock)

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Crew Transfer Vehicle (CTV)

• Dimensions
• Overall Height 9.2m
• Crew Cabin Height 3.7m
• Storage Height 2.2m
• Crew Cabin Diameter 5m
• Storage Diameter 6.2m

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Crew Transfer Vehicle (CTV)
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Crew Transfer Vehicle (CTV)

• Subsystems
• EPS
• Radioisotopic Thermoelectric Generator (RTG)
• Propulsion
• 5500 m/s delta V for 15,000 kg
• Reusable 4 throttleable LO2/LH2 engines
• Capable of doing a touch and go abort
• On orbit refuel capability from TPM
• Structure
• TPS/Aerobraking structure part of petal system
• Telescoping landing structure
• Parachute pods (4)
• ADAM aperture

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CTV Aeroentry
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CTV on surface
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Mars Laboratory Module (MarsLab)

• Vehicle Mission
• Provide specialized scientific experimentation on
  the surface of Mars
• Vehicle Design Requirements
• Fits within Kepler fairing
• Uses ATLaS and ADAM
• Can be a MarsHab shell outfitted as a laboratory
  or alternate design, e.g. inflatable, deployable

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Mission Architecture Requirements

• Safely transport a crew from Earth to the surface
  of Mars and back
• Support a sustainable human presence on Mars
• Each part of the mission should be repeatable in
  order to meet the needs of human habitation
• Each mission element should be reusable or
  referbishable
• No on-orbit construction, only vehicle dockings
  and integration

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Mission Architecture Requirements

• A viable Martian global positioning system must
  be in place before landing craft on the surface
  of Mars
• Sufficient power supply must be available on the
  surface of Mars before human habitation
• The crew must have the means of returning to
  Earth when they enter Mars orbit
• The crew must have the ability to leave the
  Martian surface within 36 hours of landing
• There must be a functioning habitat on the
  Martian surface when the crew lands

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Mission Architecture Phase I

• TPM1 transfers Mars Information Infrastructure
  (MII) from Earth to Mars orbit (3 months)
• MII deploys around Mars (3 months)
• TPM1 returns to Earth as MII deploys

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1
Transfer MII to Mars orbit TPM1 returns to Earth
orbit
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Mission Architecture Phase II

• TPM2 carries MarsHab and CRATE to Mars orbit (3
  months)
• MarsHab and CRATE undock, deorbit and land
  independently (1 month)
• Once on the surface, CRATE deploys the Power
  module which is then connected to MarsHab for
  systems checkout.
• TPM2 returns to Earth orbit

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MarsHab CRATE transfer to Mars orbit. MarsHab
and CRATE land on Mars. TPM2 returns to Earth
orbit.
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Mission Architecture Phase III

• TPM1 docks with TransferHab in LEO (1 week)
• CTV-M docks with TransferHab in LEO and TPM1
  pushes the stack to GEO (1 month)
• The crew launches in CTV-E and travels to GEO to
  dock with TransferHab (5 days)
• TPM1 then accelerates the stack (TransferHab,
  CTV-E, and CTV-M) and crew to Mars orbit (3
  months)

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MarsHab
CRATE
TransferHab, CTV-E, CTV-M, and the crew transfer
to Mars orbit. The crew lands on Mars in CTV-M.
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Mission Architecture Phase III

• Once in Mars orbit, the crew enters CTV-M and
  undocks from TransferHab
• CTV-M deorbits and lands within range of MarsHab
  (3 days)
• The crew enters MarsHab and executes their
  surface mission (1 year)

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The crew executes its surface mission.
MarsHab
CRATE
CTV-M
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Mission Architecture Phase III

• After the surface mission is complete, the crew
  ascends in CTV-M to rendezvous with TransferHab
  (3 days)
• TPM1 then brings the crew and stack back to Earth
  orbit (3 months)
• The crew undocks from TransferHab in CTV-E and
  lands (5 days)

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MarsHab
CRATE
The crew ascends in CTV-M. TransferHab, CTV-M,
and CTV-E transfer to Earth orbit. The crew lands
on Earth in CTV-E.
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Continuous Habitation

• Phases II or III can be repeated in any order to
  continue human habitation of Mars
• Phase II can be used to add surface modules
  (i.e., MarsHabs or MarsLabs) or send more
  supplies (i.e., CRATEs) to the Martian surface.
• Phase III is repeated to maintain a human
  presence on Mars.
• To allow a continuous manned outpost on Mars an
  additional TPM, TransferHab, CTV-E, and CTV-M
  will be required

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MarsHab
CRATE
Steps 2 or 3 can be repeated in any order. Step 2
adds new Mars surface modules. Step 3 maintains a
human presence on Mars.
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Conclusions

• This design provides a modular and sustainable
  manned Mars mission architecture requiring
• Heavy-lift launch vehicle
• Multifunctional equipment and elements
• Advanced propulsion systems
• Nuclear power

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Acknowledgements

• Larry Bell UH Director of SICSA
• Dr. Valery Aksamentov Program Consultant
• Robert Morris UH Architecture Professor
• Scott Baird NASA Prop. and Fluid Systems
  Engineer
• Dr. Doug Hamilton NASA/Wyle Flight Surgeon
• Amy Ross NASA Advanced Suit Technology
• Bob Sauls John Frassanito and Associates
• Brent Sherwood Boeing Space Architect
• Dr. Rube Williams Los Alamos National Lab
• Dr. Leonard Yowell NASA Carbon Nanotube Project

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Questions?
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Backup Slides
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Human Factors

• Crew Considerations
• Size, selection
• Psychological Factors
• Medical

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Crew Selection

• Crew Size
• 8 crew members
• Allows for shift rotation
• Provides an overlapping skill base
• Crew Training
• Simulator training on Earth
• Computer based reference manuals onboard

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Crew Composition

• Crew Composition
• Mixed gender crew
• Age considerations
• Mixed race international crew
• Physical educational requirements will be
  similar to NASAs standards

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Human Factors Image 2
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Restraints

• Foot restraints
• Should be adjustable for socks and shoes
• Microgravity Hand Rails
• Needed along length of TransferHab
• Need 2 translational paths for safety
• 120cm (47in) hand to hand reach
• Everything designed to fit and an anthropometric
  population of
• 5th percentile Japanese female
• 95th percentile American male

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Medical Requirements

• Supplies
• Surgical Supplies
• Anesthesia
• Wound Dressing
• Splints
• Reusable needles and IVs
• Blood products

• Equipment
• Ventilation Equipment (Respirator)
• Defibrillator
• Ultrasound Equipment
• Refrigeration
• Dental Equipment
• Pharmaceuticals with a shelf life of 3 5 years

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Esuit

• Pressurized Helmet with a Life Support Interface
• Mesh Dry Suit Layer
• Gloves and Boots
• Hard Torso Shell
• Variable-Pressure Life Support Backpack
• Mechanical Counter Pressure (MCP) applied by
  knitted elastometric fibers
• Increased mobility over current EMU
• Radiation protection provided by reflective
  fiber coatings and layers
• Micrometeorite protection provided by advanced
  fibers

Courtesy of Amy Ross (NASA JSC)
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MCP Technology

• Developed by Dr. Paul Webb in the 1960s
• Mechanical Counter Pressure equalizes the
  difference in breathing pressure and external
  pressure for under-pressure conditions

Courtesy of Amy Ross (NASA JSC)
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Normal Conditions

• Balance of Two Pressures
• Arterial Pressure (P1) is dictated by breathing
  pressure
• Tissue Pressure (P2) is dictated by external
  presssure on the skin (P0)
• In normal atmospheric condition P0 P1 P2
• Pressure Imbalance
• P0 lt P1 or P0 gt P1 can cause Edema or decreased
  blood flow
• Effect of MCP
• Pressure difference can be overcome by applying
  additional pressure to skin

Atmosphere (P0)
P1
Blood Vessels
Tissue (P2)
Under-Pressure
Atmosphere (P0)
P1
Blood Vessels
Tissue (P2)
Over-Pressure
Atmosphere (P0)
P1
Blood Vessels
Tissue (P2)
Under-Pressure with MCP
Atmosphere (P0)
Blood Vessels
P1
Tissue (P2)
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Mars Information Infrastructure (MII)

• Subsystems
• CCDH
• Focus on high-data rates, autonomy, and
  redundancy
• Optical and cross-link communications key
• Autonomous status monitoring and maintenance will
  reduce crew/ground workload
• High-volume onboard storage for relay and crewed
  modules
• MCS
• Near Earth and Mars satellite based
• Integrated Guidance, Navigation, and Attitude
  Determination functions
• Autonomy key for interplanetary phases

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Mars Habitation Module (MarsHab)

• Subsystems
• EPS
• Power supplied by Power module 1MW
• TCS
• Passive thermal control and active internal water
  loop
• Radiators for external ammonia loops located on
  the surface of the module.

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MarsHab w/tractor
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TransferHab Elevation
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TransferHabVehicle Subsystems

• Subsystems
• Unmated
• MCS Propulsive attitude control system
• EPS RTG
• TCS Passive thermal control
• Mated with TPM
• MCS Controlled by TPM
• EPS Primary power provided by TPM
• TCS Passive thermal control and active internal
  water loop with heat rejection provided by TPM

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Hydroponics Lab (MarsLab-1)

• Structural Design
• Lowest portion of lab used provides water storage
• Rigid lower level contains equipment and supplies
• Rigid upper level contains inflatable lift and
  balloon

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Hydroponics Lab (MarsLab-1)

• Gardening System
• Deploys inflatable structure
• Vertically revolving container units
• Maximize planting volume
• Flexible to account for varying plant heights

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Mars Landing Site Criteria

• Abundant natural resources (ISRU)
• Low radiation
• Topography
• Semi-flat surface
• Small rocks and obstacles
• Scientific points of interest
• Climate
• Pressure and temperature changes, dust storm
  possibilities
• Access to/from orbit

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Site Selection

• The Lunae Planum is currently selected for this
  mission based on the following
• Location
• 60-90o longitude, 0-30o latitude
• -1000 to 1000 m elevation
• Natural resources
• Possible frozen water
• Topography
• Few Impact Craters
• Scientific points of interest
• Kasei Valles-possible old river
• Close to Viking 1 landing site

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Site Plan

• 3 zone site plan
• Habitation
• Power
• Landing / Launching