nasa human exploration and operations update (october 23, 2014)

8/10/2019 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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4

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

4


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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

5

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

16

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

18

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

2727


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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

29

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

31

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

32

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

33

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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35

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

35

Asteroid Redirect Mission: Three Main Segments

Robotic Mission Spacecraft Reference Configuration


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Robotic Mission Spacecraft Reference Configuration

Key Features

36

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

37

Solar electric propulsion (SEP) based system

redirects asteroid to cis-lunar space (two capture options)

A B

37


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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

38 38


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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)

41

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


Best demonstration of suit

capability, attributed to good suit

fit that allowed the subject easier

access to standard work envelope.


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

45

Asteroid Redirect Mission Provides Capabilities For Deep


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46

Space/Mars Missions

46

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

47

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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49

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

nasa human exploration and operations update (october 23, 2014)

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