NASA Human Exploration and Operations Update (October 23, 2014)
Transcript of NASA Human Exploration and Operations Update (October 23, 2014)
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National Aeronautics and Space Administration
NASAs Human Exploration and
Operations UpdateWilliam H. Gerstenmaier
Associate Administrator for Human Exploration and Operations
NASA Headquarters
October 23, 2014
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Strategic Principles for Sustainable Exploration
Implementable in the near-term with the bu y ing p ower of current budgets
and in the longer term with budgets commensurate with economic growth;
Explorat ion enables science and science enables exploration, leveraging
robotic expertise for human exploration of the solar system
Application of hig h Techno log y Readiness Level (TRL) technologies for
near term missions, while focusing sustained investments on technologies
and c apabi l i t ies to address challenges of future missions;
Near-term missio n oppo rtunit ieswith a defined cadence of compelling and
integrated human and robotic missions providing for an incremental buildup of
capabilities for more complex missions over time;
Opportunities for U.S. commercial bu siness to further enhance theexperience and business base
Mul t i-use, evolv able space infrastructure, minimizing unique major
developments;
Substantial internat ional and commercial part ic ipat ion, leveraging currentInternational Space Station and other partnerships. 2
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The Future of Human Space Exploration
NASA
s Building Blocks to Mars
Ear th Reliant Proving Ground Ear th Independent
Missions: 6 to 12 months
Return: hours
Missions: 1 month up to 1 2 months
Retur n: days
Missions: 2 to 3 years
Return: months
Mastering the
fundamentals
aboard the
International
Space Stat ion
Developingplanetary
independence
by exploring
Mars, its
moons, and
other deep
spacedestinations
U.S. companies
provide
affordable
access to low
Earth orbit
Pushing the
boundaries in
cis-lunar space
The next step: travelingbeyond low-Ear th orbit with
the Space Launch System
rocket and Or ion crew
capsule
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Human Exploration Pathways
Toward Earth IndependentCrewed Orbit of Mars or Phobos/Deimos
Land on Mars
Mastering the Fundamentals Extended Habitation Capability (ISS)
- High Reliability Life Support Deep-space Transportation (SLS and Orion)
Exploration EVA
Automated Rendezvous & Docking
Docking System
Bringing the moon within
Earths economic sphere.
Pushing the Boundaries Deep Space Operations
- Deep Space Trajectories
- Deep Space Radiation Environment
- Integrated Human/Robotic Vehicle
Advanced In-Space Propulsion (SEP)
- Moving Large Objects Exploration of Solar System Bodies
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EARTH RELIANT
DEVELOP AND VALIDATE EXPLORATION CAPABILITIES IN AN IN-SPACE ENVIRONMENT
Long duration, deep space habitation systems
Next generation space suit
Autonomous operations
Communications with increased delay
Human and robotic mission operations
Operations with reduced logistics capability
Integrated exploration hardware testing
LONG-DURATION HUMAN HEALTH EVALUATION
Evaluate mitigation techniques for crew health and performance in micro-g space
environment
Acclimation from zero-g to low-g
COMMERCIAL CREW TRANSPORTATION
Acquire routine U.S. crew transportation to LEO
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NEAR-TERM OBJECTIVES
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Refueling
Rendezvous sensors
Leak detection
HabitationStructures
Trash compactor
NASA Docking System
Solar arraysLife Support Systems Crew Support Systems
Crew MedicalSystems
EVA Systems
Earth Reliant: Exploration Systems Flight Testing on ISS
Amine Swingbed
CO2 Removal
Optical Comm
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Expanding Research on ISS
GeneLab Rodent Research
Cold Atom Lab
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Hazards of SpaceflightHazards Drive Human Spaceflight Risks
Altered Gravity -Physiological Changes Distance from Earth
Hostile/
Closed EnvironmentSpace Radiation
Isolation & Confinement
Acute In-flight effectsLong term cancer risk
Balance DisordersFluid Shifts
Visual AlterationsCardiovascular Deconditioning
Decreased Immune FunctionMuscle AtrophyBone Loss
Drives the need for additionalautonomous medical care
capacity cannot come home fortreatment
Behavioral aspect of isolationSleep disorders
Vehicle Design
Environmental CO2 Levels,Toxic Exposures, Water, Food
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The Joint US-Russian One-Year Mission
NASA astronaut Scott Kelly and Russian Cosmonaut Mikhail Kornienko
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Commercial Cargo
SpaceX Dragon
Orbital Cygnus
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Commercial Crew Program Overview
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Commercial Crew awards made with initial flights planned for 2017 Phased acquisition using competitive down-selection with full and open competition
Firm fixed-price, performance-based, with fixed-price Indefinite Delivery/IndefiniteQuantity (IDIQ)
Commercial Crew- US Transportation to ISS
Boeing Space-X
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Boeings crew space transportation system is comprised of
its reusable CST-100 spacecraft, the United Launch Alliance
Atlas V launch vehicle, mission operations and groundsystems.
Boeing is continuing to develop its integrated space
transportation system with design reviews and hardware
testing.
FORWARD INNOVATION
Weld-free capsule
Tablet technology
Evaluating lightweight ablator concepts
Wide Area Network
Boeing Sky Interior lighting
Liquid-propelled abort system
Newly developed humidity removal system
Vision-based approach, rendezvous and docking
system
Air bag system for soft land and water landings
REMAINING MILESTONES
All milestones completed
BOEING - CCiCap Initiative
Artist concepts of Boeings CST-100
Artist concept of integrated
CST-100 and Atlas V rocketCST-100 water contingency
landing scenario testing
Launch abort engine hot-fire test in California
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SpaceXs crew transportation system is based on the Dragon
spacecraft and Falcon 9 launch vehicle originally developed for
International Space Station cargo missions. Initially designed to
carry cargo, the Dragons components are being modified for
added safety and crew accommodations.
FORWARD INNOVATION
State-of-the-art avionics
Newly developed spacesuits First stage engine-out to orbit capability
Modern user interfaces for displays and controls
Newly developed humidity removal system
3-D printing of titanium and Inconel steel
Large-scale composite structures
Advanced thermal protection
REMAINING MILESTONES
Pad Abort Test
Dragon Primary Structure Qualification
Crew Vehicle Technical Interchange Meetings
Delta Crew Vehicle Critical Design Review
In-Flight Abort Test
Dragon V2 at SpaceX headquarters
Dragon test article usedfor parachute testing
Astronaut fit-check inthe Dragon
Falcon 9 first stage at SpaceX headquarters
SPACEX CCiCap Initiative
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Earth Reliant: A Commercial Marketplace in LEO
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PROVING GROUND
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NEAR-TERM OBJECTIVES
VALIDATE
SLS and Orion in deep space
Solar Electric Propulsion (SEP) systems
Long duration, deep space habitation systems
Mitigation techniques for crew health and performance in a deep space
environment
Galactic Cosmic Background radiation experience
In-Situ Resource Utilization
Operations with reduced logistics capability
CONDUCT EVAs in deep space, micro-g environments
Human and robotic mission operations
Capability Pathfinder and Strategic Knowledge Gaps (SKG) missions
Investigate staging options for human deep space mission from this region of
space.
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2014EFT-1 2017EM-1 2021EM-22018AA22010PA-1
Exploration Mission Timeline
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Core Stage & Avionics
are new developments
In ProductionContract : Boeing
RS-25 Engines
Currently ExistContract: Aerojet Rocketdyne
5 Segment
Solid Rocket Boosters
Currently ExistContract: ATK
Interim Cryogenic PropulsiveStage (ICPS) is a modified
Delta IV upper stage
Contract Being DefinitizedContract: Boeing / United Launch Alliance
Launch Vehicle Spacecraft
Adapter is new developmentContract Awarded Feb 2014Contract : Teledyne Brown
The SLS System- Block 1
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Modern manufacturing is key to lower cost. Existing systems chosen for flat line
budget consideration and lower development cost and risk.
5 Meter Payload Fairings
& LV Adapters
Heritage DesignsContracts: TBD
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Evolving Capability
Orion, Multi-Purpose
Crew Vehicle
(MPCV- LMCO)
Core Stage/Avionics
(Boeing)
Core Stage
Engines (RS-25)
(Aerojet Rocketdyne)
5-Segment Solid
Rocket Booster
(SRB) (ATK)
Interim Cryogenic
Propulsion Stage (ICPS)
(EELV 5m DCSS
Boeing/ULA)
Launch
Abort
System
Commonality of
Payload Interfaces Mechanical
Avionics
Software
Cargo
Fair ing33 ft (10m)
Upper
Stage
Block 1
Initial Capabi lity , 2017-21
70 metr ic ton Payload
Block 2 Capabi l i ty
130 metr ic to n
Payload
Evolutionary Path to Future Capabilities Minimizes unique configurations
Allows incremental development
Advanced
Sol id or
Liquid
(i.e., RP
Engines)
Boosters
Launch
Vehicle/Stage
Adapter (LVSA)
(TBE)
Commonality of Core Stage
Commonality of Engines
Upper Stage &
Core Stage Commonality
Same diameter (27.5 ft.) and basic design
Manufacturing facilities, tooling, materials,
& processes/practices
Workforce
Supply chain/industry base
Transportation logistics
Ground systems/launch infrastructure
Propellants
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Space Launch SystemSolid Progress on Development
Ten barrels have been welded, including the first
four LH2 qualification barrels, for the SLS core stage
NASA has successfully tested the most complex
rocket engine parts ever designed on a test stand at
Marshall Space Flight Center
The 170-foot Vertical Assembly Center at
NASA's Michoud Assembly Facility will weld
parts for the #SLS core stage
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Recent Progress
MPCV-to-Stage Adapter:First flight hardware currently in Florida for
Exploration Flight Test-1 in Fall 2014.
Launch Vehicle Stage Adapter: Contractawarded in February 2014.
Avionics:Avionics first light marked in January
2014; currently testing most powerful flight system
computer processor ever.
Boosters: Forward Skirt test completed May
2014; preparations underway for QM-1.
Core Stage: Initial confidence barrels and domes
completed; Vertical Assembly Center activation
completed in Sept. 2014.
Engines: Preparing for RS-25 testing at at
Stennis Space Center; renovations underway to
B-2 stand.
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SLS Milestones Schedule
MCR: Mission Concept Review CDR: Critical Design Review
SRR: System Requirements Review DCR: Design Certification Review
SDR: System Defin ition Review SAR: System Acceptance Review
PDR: Preliminary Design Review FRR: Flight Readiness Review
KDP-C: Key Decision Point
2011 2012 2013 2014 2015 2016 201718
Concept
Studies
Concept & Technology
Development
Preliminary Design &
Technology CompletionFinal Design & Fabrication System Assembly, Integration & Test, Launch & Checkout
Internal
Launch
Readiness
SLS DesignChosen
Orion
Flight
Test
Vehicle Stackingat KSC
Booster
Assembly at
KSC
Core Stage
Test-Firing
Manufacturing
Tooling Installation
Core Stage
Structure
Testing
Booster
Qualification
Tests
STA
Production
Begins
Core Stage
Assembly
Booster
Development
TestWind Tunnel
Testing
EnginesDelivered to
Inventory
Production of
First New
Flight
Hardware
Main
Engine
Test-Firing
CDR
MCR
PDR DCR
Launch AvailabilitySRR/SDR KDP-C
PROGRAM PROGRESSFormulat ion Imp lemen tat ion
ICPS
Production
Begins
www.nasa.gov/sls
SAR
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Launch Abort
System
Crew
Module /
CM AdapterESA
Service
Module
The Orion Spacecraft
O i S ft
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Orion SpacecraftFirst Flight Test in 2014
Orion heads to the Launch Abort System Facility
for the installation of final piece before the
spacecraft is ready to launch
The Orion crew module is complete!
Technicians and engineers at Kennedy Space
Center put the finishing touches on the crew module
Recovery team members work to secure a test
version of Orion in the Pacific Ocean duringUnderway Recovery Tests 3 & 4
Technicians dressed in clean-room suits have
installed a back shell tile panel onto the Orioncrew module
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Service Module
EFT-1 Launch Vehicle
Crew Module
Launch Abort System
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Parachute Drop Tests Astronauts helping design Orion
Mission Control Center Underway Recovery Test
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2014 Exploration Flight Test One
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EFT-1 Test Objectives
Crew Module (CM) Production primary structure Mechanisms: CM/SM, LAS/CM, FBC, SM umb sep. Docking,
DMJS
TPS BEO heat rate capable, BEO heat load capable
Batteries w/4 bus EPS and Power Data Units
Dual redundant primary flight computers
Backup flight control system
Triple Dual redundant TTGbe data bus
Triple Dual redundant OIMUs
C&T system with phased array antennas
OFI and DFI data ECLS ATCS, ARS, Cabin PCS Dual string Hydrazine RCS
Ascent, Abort, Orbit, RPOD, Entry GNC
Human Capable Landing & Recovery Systems & Loads Mgmt
Crew Displays/Crew Systems
Service Module (SM) Production primary structure
Mechanisms: SC sep, SM umb
Solar array power production
Power Data Units
Phased Array Antennas
Hypergolic Main Engine, RCS, storage tanks
ATCS w/radiators
DFI data
Spacecraft
Adapter/Fairings Production primary structure
Mechanisms: Fairing sep
DFI data
Launch Abort System (LAS) Production primary structure
Abort Motor
Attitude Control Motor
Jettison Motor
Boost Protective Cover/Acoustic
Shroud
C&T antennas
DFI data
Legend Text boxes include system description of EFT-
1 configuration based on an EM-2 listing
Strike through text indicates EM2 system not
present on EFT-1 Blue test indicates modified EM2 configuration
present on EFT-1
EFT-1 Mission success criteria:
- Successfully launch and deliver EFT-1 into the planned orbit
- Demonstrate critical separation events during ascent and deorbit
- Demonstrate TPS performance during high energy return- Demonstrate descent, landing, and recovery.
2017 E l ti Mi i (EM) 1 SLS/O i
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2017: Exploration Mission (EM) -1 SLS/Orion
Uncrewed Flight Test
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Mission Objectives/Operations: SLS heavy lift capability Autonomous Orion operations in the Distant
Retrograde Orbit environment
Deploy secondary payloads Demonstrate Critical Mission Events
Separation Events - Booster/Core, ServiceModule fairings, Crew Module/Launch
Abort System, Orion to SLS
Maneuvers Interim Cryo PropulsionStage TLI, Service Module Orbit and Entryburns
Beyond Earth Orbit re-entry (11 km/s) Validate Thermal Protection System
performance
Chute deploy, Crew Module uprighting and
recovery Demonstrate integrated vehicle systems in flight Deep space communication and tracking Integrated power and thermal Attitude control and in-space maneuvering
Validate environments Aerodynamic, Aerothermal, Acoustics,
(shock and vibration), Structural Loads,Thermal, Radiation
OrionSLS Block 1 ICPS Upper Stage
SLS Block I Vehicle Core Stage with 4 RS-25 engines Two 5 segment boosters Non-human rated ICPS Upper Stage
Orion Vehicle Cis-Lunar configuration (no ECLSS)
DRO Mission Profile 3U/6U Secondary Payloads on SLS
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Exploration Mission 1 Demonstrates ARM Trajectory
1
3
2
4
5
6
7
8
9
1011
12
Trans Lunar
Injection
ICPS
Outbound Lunar
Gravity Assist
Return Lunar
Gravity Assist
Distant
RetrogradeOrbit
70,000 KM
(Not strictly
circular)
DRO
Arrival
Burn
DRO
Departure
Burn
Perigee Raise
Maneuver
ICPS
100x975 nmi
CM/SM
Separation
El-20 min
Entry &Landing
LAUNCHTrajectory
Correction
Maneuvers
Orion
Inbound: ~9 days
Outbound: ~10 days
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SLS Block 1B Vehicle Core Stage with 4 RS-25 engines Two 5 segment boosters Exploration Upper Stage EUS Cargo area
Orion Vehicle Block 0 Orion (cis-lunar configuration) 2-4 Crew
Hybrid Mission Profile (High Earth Orbit/Cis-Lunar Flyby)
2021: EM-2 SLS/Orion Crewed Flight
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Mission Objectives/Operations: First flight of SLS Exploration Upper Stage
(EUS) Demonstrate Orion crewed operations in
Beyond Earth Orbit (BEO) environment Deep space rendezvous and docking
Primary Utilization Activities: Check-out and test of Orion Systems in
beyond LEO environment
Test and validate life support and crewedoperations in deep space
Demonstrate Critical Mission Events inBlock 1B vehicle Separation Events Service Module (SM)
fairings, EUS/SM Maneuvers EUS Trans Lunar Injection
Demonstrate integrated vehicle systems t Environmental Control and Life Support
System, Flight Crew Equipment,Habitability
Validate Block 1B environments Aerodynamic, Aerothermal, Acoustics,
(shock and vibration), Structural Loads,
Thermal, Radiation
Orion
Not Shown: SLS Block 1B with Exploration Upper Stage (EUS)
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Exploration Upper Stage (EUS) - Payload Capacity
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Orion
w/extra
ServiceModule
Standard
MSA2Cone
17.8
EUS Enhances Multi-Capability Missions
8m Fairing
w/AdvancedTechnology
Large Aperture
Space Telescope
(ATLAST)
30 tall x 27.6 dia
5m Fairing
w/European Space
Agency (ESA)
Service Module
& Exploration
Augmentation
Module (EAM)
60 tall x 27.6 dia
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EUS DRM for Co-Manifested Payloads
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1
2
3 4 5a
5b
Orion separates
and Spacecraft
Adapter jettisoned
USA Panels deployed
and Orion performs
transposition maneuver
Orion docks with
co-manifested payload
EUS performs injection
burn sending Orion and
co-manifested
payload to destination
Secondary
payloads
deployed
Completion
of EUS
ascent burn
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Objectives of Asteroid Redirect Mission
Conduct a human exploration mission to an asteroid in
the mid-2020s, providing systems and operational
experience required for human exploration of Mars.
Demonstrate an advanced solar electric propulsion
system, enabling future deep-space human and
robotic exploration with applicability to the nations
public and private sector space needs.
Enhance detection, tracking and characterization ofNear Earth Asteroids, enabling an overall strategy to
defend our home planet.
Demonstrate basic planetary defense techniques that
will inform impact threat mitigation strategies to defend
our home planet.
Pursue a target of opportunity that benefits scientific
and partnership interests, expanding our knowledge of
small celestial bodies and enabling the mining of
asteroid resources for commercial and exploration
needs.
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Infrared Telescope FacilityGoldstone Arecibo
NEOWISE
IDENTIFY
REDIRECT
EXPLORE
Ground and space
based assets detect andcharacterize potential
target asteroids
Solar electric propulsion
(SEP) based system
redirects asteroid to cis-
lunar space (two capture
options)
Crews launches aboard SLS
rocket, travels to redirected
asteroid in Orion spacecraft
to rendezvous with redirected
asteroid, studies and returnssamples to Earth
Pan-STARRS
A B
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Asteroid Redirect Mission: Three Main Segments
Robotic Mission Spacecraft Reference Configuration
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Robotic Mission Spacecraft Reference Configuration
Key Features
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Solar Electric Propulsion
Module (SEPM)
Compatible with SpaceTechnology Mission
Directorate (STMD) solar
array technology at 50 kW
Electric propulsion derived
from STMD thruster/power
processing technology
Xenon tanks seamlesscomposite overwrapped
pressure vessel with at least
10 t capacity
Launch Vehicle Interface Compatible with 5m fairings
Unique adapter depending on
launch vehicle selected
Capture Mechanism
Flight heritage instrumentation Two mass capture options
Mission Module Flight heritage avionics
Simple Interface with SEPM
Orion docking I/F
Crew access path
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Asteroid Redirect Robotic Mission Options
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Solar electric propulsion (SEP) based system
redirects asteroid to cis-lunar space (two capture options)
A B
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Asteroid Redirect Crewed Mission Overview
Deliver Crew on
SLS and Orion
Perform extra-vehicular activity to retrieve asteroid samples
Return crew safely to Earth
with asteroid samples in Orion
Orion Travels To and Docks with Robotic Spacecraft
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Trajectory, Rendezvous, and Proximity Operations
STORRM Camera Image STORRM LIDAR Images
Common Rendezvous/prox-ops sensors
leveraging Space Shuttle Detailed Tests
Rendezvous /proximity operationsmaneuvers result largely in rectilinear
motion
Trajectory, launch window, rendezvous,
and navigation techniques enable Mars
EARTH Outbound Flight Time
9 days
Moon
Lunar Gravity Assists
Return Time
11 days
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Docking System
International Docking Adapter will create a docking port on ISSto provide power and data utility connections to visiting vehicles
Beginning FY14 study with ISS Program to evaluate Block I to
Block II: Voltage and avionics
Deep space environment
Mass reduction opportunities
Overall system design efficiency
Orion ActiveDocking
Mechanism
Robotic Spacecraft
Passive Docking
Mechanism
Docking System for Orion and Robotic
Spacecraft leverages development of
International Docking System Block 1 All Mars/Deep Space Architectures will require
some form of autonomous docking
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EVA Suit and Primary Life Support System (PLSS)
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Exploration PLSS- capable withsmall modifications of ISS EMU,Exploration Suit, or M-CES witharchitecture that is Mars capable
PLSS 2.0 prototype completed in FY13
Variable Oxygen Regulator flammabilitytesting completed at White Sands TestFacility
FY14 work includes integrated metabolicand functional testing and fabrication of a
PLSS/MACES integration kit
MACES with PLSS
and EVA Suit KitVariable Oxygen Regulator
Testing at WSTF
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NBL Test Results Worksite Stabilization
Adjustable Portable FootRestraint operationswere tested and
execution is very similarto the ISS ExtravehicularMobility Unit.
Body RestraintTether allowed thecrew to performtwo handed tasks
Crew was able toperform severalsampling tasksincluding worksiteimaging, float samplecollection, hammerchiseling andpneumatic chiseling.
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Modified ACES Testing Summary
Hardware and
Procedure
Improvements
May June July August September
May 5th Test #1 (2hr)
Established baselineweigh out and ECS
interface (both to be
improved)
Winter 2012
MACES EVAs are
demonstrated as feasible
and neutrally buoyant
testing is warranted
June 7th Test #2 (2hr)
Established need for
robust EVA gloves (ISS
EMU PhaseVI)
June 28th Test #3 (2hr)
Improvements in suit fit
procedures needed
July 12th Test #4 (2hr)
Two-handed task difficulties
established need for suit
shoulder biasing and better
worksite stabilization
July 22nd Test #5 (2hr)
Great capability improvements
observed in subsequent runs
indicating that training on the
suit is vital.
Sept. 6th Test #6 (3hr)
Suit fit specific to EVA
operations continues to
be a significant
performance factor
Sept. 25th Test #8 (4hr)
Best demonstration of suit
capability, attributed to good suit
fit that allowed the subject easier
access to standard work envelope.
Sept. 16th Test #7 (4hr)
Suit system demonstrated
feasibility of 4 hour EVAs.
Improved weights Phase IV GlovesDrink bag
included
Improved
Poolside
Procedure
Cooling System
modificationsNew liquid
cooling garment
Added tool
harness
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Each wing sized for nominally 20kW BOL
STMD Solar Array Technology Work in FY 2014
Cut away of NASA 300V PPU
JPLH6withmagneticshielding
GRC30
0Mwithmagneticshielding
EARTH INDEPENDENT
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EARTH INDEPENDENT
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Asteroid Redirect Mission Provides Capabilities For Deep
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Space/Mars Missions
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High Efficiency
Large Solar Arrays
Solar
Electric
Propulsion
(SEP)
In-space Power and Propulsion :
High Efficiency Solar Arrays and SEP
advance state of art toward capability
required for Mars
Robotic ARM mission 40kW vehiclecomponents prepare for Mars cargo
delivery architectures
Power enhancements feed forward to
Deep Space Habitats and Transit Vehicles
Exploration
EVACapabilities
EVA:
Build capability for future exploration
through Primary Life Support System Design
which accommodates Mars
Test sample collection and containment
techniques including planetary protection
Follow-on missions in DRO can provide more
capable exploration suit and tools
Deep Space
Rendezvous
Sensors & DockingCapabilities
Crew Transportation and Operations:
Rendezvous Sensors and Docking Systems provide a
multi-mission capability needed for Deep Space and Mars
Asteroid Initiative in cis-lunar space is a proving ground
for Deep Space operations, trajectory, and navigation.
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Large/Long Gap
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ISS and ARM Provides First Steps to Mars
Sequence
Mission
N ti l Ph b Mi i
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Notional Phobos Mission
Mars Orbit Deimos
Pre-Deploy Cargo
Mars Orbit
InsertionTrans-Earth
Injection
Direct Earth
Entry
High-Earth
Assembly Orbit
~16 Months in Mars System
High Mars Orbit
Lunar Gravity
Assist
4Yea
rstoMars
Cargo via Solar
Electric PropulsionCrew via Chemical
Propulsion
3Yea
rstoMars
7-9MonthstoM
ars
7-9Mo
nthstoEarth
Crew Mission
Phobos
Habitat
Earth Return Stage
and Phobos Transfer Stage
Orion: Mars ops and Earth Entry
EUS for
Earth
Departure
Transit Habitat
Mars Insertion Stage
Solar Electric Propulsion
(100 -200 kW )
(40 t class payloads)
Phobos
Mars habitat and return stage
will confirmed to be in place
before crew departure.
Reference: Center workin rou March 14 201448
Mars Split Mission Concept
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Mars Split Mission Concept
Returning from Mars, the crew will return to Earth in Orion and the Mars Transit
Habitat will return to the staging point in cis-lunar space for refurbishment for futuremissions
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LEO
7,800 lb
BEO
18,965 lb
PROPELLANT
BEO
210 Liters
LEO
40 Liters
DRINKINGWATER
OXYGEN
BEO
190 L
LEO
36 L
BEO
14.8 FT3
LEO
2.8 FT3
FOOD
BEO 11.2 KM / SEC
REENTRY SPEED
LEO 7.8 KM / SEC
RADIATION
DOS
E
SHIELDING
BEO
ISS
Orion is built for going Beyond Earth Orbit
ADVANCED CARBONDIOXIDE REMOVAL
SYSTEM
CARBON DIOXIDEFILTER
BEO
42
LEO
8