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									 National Aeronautics and Space Administration




Constellation Space Suit System
Contract Award Announcement



Doug Cooke
Deputy Associate Administrator
NASA Exploration Systems Mission Directorate
June 12, 2008




 www.nasa.gov                                    Constellation Systems Division
                                                 Constellation Systems 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

 Key Features
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

Key Features
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




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                                                              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



            Basic Period
             Basic Period                                                         Option 22
                                                                                   Option
            • Configuration 1: DDT&E, initial hardware delivery, and              • Configuration 1:
              • Configuration 1: DDT&E, initial hardware delivery, and              • Configuration 1:
              sustaining engineering until completion ofof first flight
                sustaining engineering until completion first flight                   •Production (CPAF/FFP)
                                                                                        •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                                            IDIQ
                                   Milestone driven CPAF                                            IDIQ
Note: Years are shown as             Option 11
                                      Option
      Government Fiscal Years        • Configuration 2: DDT&E, initial hardware delivery, and sustaining engineering
                                       • Configuration 2: DDT&E, initial hardware delivery, and sustaining engineering
                                                                    Milestone driven CPAF
                                                                     Milestone driven 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



      CONGRATULATIONS

  OCEANEERING
 INTERNATIONAL
      INC.
      INC
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NASA and Constellation Space Suit System Industry Team



                                                                     Glenn
                                                                 Research Center          Worchester, MA




                                                                                              Milford, CT



                                                                                        Goddard Space
                  Glendale, AZ                                                           Flight Center
                                        International Inc.
                                          Houston,TX
    Ames                                                                              Palm Bay, FL
Research Center



                                                          Houston, TX              Kennedy Space Center
                    Tucson, AZ



                        Johnson Space Center       Houston, TX
      NASA
        and

    Oceaneering
International Inc.
        are


“GO FOR EVA”
“GO     EVA”
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