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Constellation Space Suit System Acquisition Schedule Plan

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Constellation Space Suit System Acquisition Schedule Plan National Aeronautics and Space Administration ConstellationConstellation SpaceSpace Suit Suit SystemSystem ContractContract AwardAward AnnouncementAnnouncement DougDoug CookeCooke DeputyDeputy AssociateAssociate AdministratorAdministrator NASANASA ExplorationExploration SystemsSystems MissionMission DirectorateDirectorate JuneJune 12,12, 20082008 www.nasa.gov ConstellationConstellation SystemsSystems Division Extravehicular Activity – “EVA” • The space-suited astronaut is the ultimate symbol of human exploration • The spacesuit is essentially a self- contained, one-person spacecraft • It protects the crew from and enables them to work in the hostile environments of deep space and the lunar surface • It is the “last line of defense” for astronauts when they leave the relative safety of the crew exploration vehicle, lunar lander, or habitat 2 2 The Challenge for Exploration • Current spacesuits are not suitable for Exploration – Apollo Extravehicular Mobility Unit – Advanced Crew Escape Suit – Space Shuttle/International Space Station Extravehicular Mobility Unit • A new pressurized suit system will be required to support long-term Exploration requirements – Meets all capability requirements – Improves reliability – Improves logistics and maintenance – Reduces life cycle costs 3 3 The EVA System Design Approach Launch and Entry • A single spacesuit system with two configurations which share many components In-space Contingency • Common, evolvable infrastructure • Minimum set of hardware to meet all mission phase requirements • Modular, reconfigurable, component- based open architecture Lunar Surface 4 4 EVA Single Suit System Architecture Launch/Entry/Abort & Microgravity EVA Suit Lunar Surface EVA Suit (Configuration 1) (Configuration 2) Soft rear entry design Two ‘shortie’ cores Rear entry hatch design Portable Life Support System Shoulder bearing Common for mobility helmet Enhanced shoulder mobility Common Waist Bearing lower arms Gloves EVA Gloves Multi-hip Bearing Thermal micrometeroid garment/ Thigh Disconnect Common multi-layer insulation for relevant for modularity legs/boots environment – including boot covers *Overall EVA System architecture approach - modular, reconfigurable, component-based architecture that meets various mission objectives 5 5 Configuration 1 – Launch, Entry, Abort & Microgravity EVA KeyKey FeaturesFeatures Enhanced Helmet Hardware: Open flip visor Inserts for head-impact protection Helmet feed-port (120-hr survival) Analog communication (comm) cap Thermal Micrometeoroid Garment Umbilicals and Secondary Oxygen Pack: (Contingency EVA) Universal umbilical connectors on umbilicals and vehicles Short, closed-loop umbilicals (in vehicle) Pressure Garment Subsystem: Long, closed-loop EVA umbilicals One piece Soft Upper Torso assembly with Secondary Oxygen Pack Emergency 0xygen convolutes at waist and integrated scye Umbilicals: provide breathable gas, cooling shoulder bearings for mobility water, power, comm, and tether function Rear-entry zipper design Convolute joint at elbow and knee Thigh, upper arm, glove and boot disconnects Modular arm and leg components Modular boots Thermal Micrometeoroid Garment /Multilayer insulation similar to Extravehicular Mobility Unit Extraction harness with attached Personal Floatation Device Liquid Cooling Garment and bio-med sensors 6 6 Configuration 2 – Lunar Surface Exploration KeyKey FeaturesFeatures Enhanced Helmet Hardware: Thermal micrometeroid garment and lighting Visor feed-port pass through Heads-up display Suit-integrated audio Enhanced Pressure Garment Subsystem: Umbilicals and Secondary Oxygen Pack: Rear-entry with waist and scye bearings Same hardware from Configuration 1 Wear/abrasion-resistant softgoods Universal umbilical connectors on umbilicals Second generation arm patterned and vehicles convolute joint Short, closed-loop umbilicals (in vehicle) Thermal micrometeroid garment /Multi- Long, closed-loop EVA umbilicals layer Insulation for relevant environment Secondary Oxygen Pack/Emergency Oxygen Umbilicals: provide breathable gas, cooling Power, Communication, and Informatics: water, power, comm, and tether function Lithium ion batteries Command, control, communication processing in Portable Life Support System Expanded set of suit sensors Advanced Caution & Warning On-suit productivity enhancements Portable Life Support Subsystem: High pressure Gaseous Oxygen Spacesuit Water Membrane Evaporator Rapid Cycle Amine Upgrade for recharge Potable water in Portable Life Support System Enhanced Liquid Cooling Garment tank and bio-med sensors * Changes or additions of hardware to Configuration 1 are represented by darker blue 7 7 Where Are We Today? Constellation Space Suit System Acquisition Schedule Plan • Draft Request for Proposal July 17, 2007 • Request for Proposal Release November 1, 2007 • Proposals Received December 20, 2007 • Selection June 11, 2008 • Contract Award June 12, 2008 • Contract Start June 30, 2008 8 8 Constellation Space Suit System Contract Scope & Structure 2008 2009 2010 2011 2012 2013 2014 2015 2016 2017 2018 2019 Basic Period - Configuration 1 (6.3 yrs) Option 2 - Configuration 1 (4 yrs) Option 1 - Configuration 2 (8 yrs.) Delta SRR for Constellation Program IOC Human Lunar Lunar Capabilities Return BasicBasic Period Period OptionOption 2 2 • Configuration 1: DDT&E, initial hardware delivery, and • Configuration 1: • Configuration 1: DDT&E, initial hardware delivery, and • Configuration 1: sustaining engineering until completion of first flight •Production (CPAF/FFP) sustaining engineering until completion of first flight •Production (CPAF/FFP) • Configuration 2: DDT&E as required for commonality of design •Sustaining engineering (CPAF) • Configuration 2: DDT&E as required for commonality of design •Sustaining engineering (CPAF) Milestone driven CPAF Milestone driven CPAF IDIQIDIQ Note: Years are shown as OptionOption 1 1 Government Fiscal Years • Configuration 2: DDT&E, initial hardware delivery, and sustaining engineering • Configuration 2: DDT&E, initial hardware delivery, and sustaining engineering MilestoneMilestone driven driven CPAF CPAF 100 % of the contract is Performance-based CPAF – Cost Plus Award Fee IDIQ – Indefinite Delivery Indefinite Quantity DDT&E – Design, Development, Test, and Evaluation IOC – Initial Operational Capability FFP – Firm Fixed Price SRR – System Requirements Review 9 9 Successful Offeror CONGRATULATIONSCONGRATULATIONS OCEANEERINGOCEANEERINGOCEANEERING INTERNATIONALINTERNATIONALINTERNATIONAL INC.INC.INC 10 10 NASA and Constellation Space Suit System Industry Team Glenn Research Center Worchester, MA Milford, CT Goddard Space Glendale, AZ International Inc. Flight Center Houston,TX Ames Palm Bay, FL Research Center Houston, TX Kennedy Space Center Tucson, AZ Johnson Space Center Houston, TX NASANASANASA andand OceaneeringOceaneeringOceaneering InternationalInternationalInternational Inc.Inc.Inc. areare ““GO“GOGO FORFORFOR EVAEVA”EVA”” 12 12.
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