1. EVA Systems 101 Architecture & Ops Con EVA Systems Project SE&I February 2007 J. Davis EVA Systems Project SE&I February 2007 J. Davis

2. Slide 2 Outline Missions Functions Architecture EVA System Description EVA Systems Reference Configuration Ops Con Launch Nominal launch ops Emergency Pad Egress Orbit Survival in an unpressurized cabin Unscheduled/Contingency EVA Landing Nominal Off-nominal Backup

3. Slide 3 EVA System Missions Launch / Entry / Abort Nominal launch operations (suit-up, transfer to pad, vehicle ingress, launch through post-insertion, rndz/dock) Launch aborts (on the pad, in-flight) Orbit operations (crew suits up as precaution for dynamic phases of flight) Survival in an unpressurized cabin (up to ~120 hours) Post-landing operations (nominal, off-nominal, water/land) Microgravity EVA Contingency & Unscheduled EVA in LEO, LLO or in-between Surface EVA Outpost Build-up Exploration Science

4. Slide 4 EVA System Functions Sustain the life of the crewmember Protection from the environment Life support (metabolic & cooling) Hydration, nutrition, & medication Waste management Mobility / Dexterity Transition to/from the worksite Stabilize at the worksite Perform necessary tasks (w/gloved hand or tools) Visibility / Communication Ability to get eyes on Communication of voice and data

5. Slide 5 EVA System Description

6. Slide 6 6 Constellation System Hierarchy The EVA System includes more than Spacewalk hardware. Constellation is striving for one suit system to be used for Launch/Entry (crew survival) and EVA. * *

7. Slide 7 7 EVA System Hierarchy – Using Suit as an Example EVA System Element Subsystem Assembly Tools & Equipment Vehicle Interfaces GSE Suit Pressure Garment Life Support Crew Survival Power/CAI Suit Pressure Garment SUT LTA

8. Slide 8 8 EVA System External Interfaces EVA System Mission Systems Ground Systems Ground Systems Orion CEV Orion CEV ARES CLV, CaLV ARES CLV, CaLV Gas, cooling, Voice, data, power structural Flight Crew Equipment LSAM Surface Mobility Habitat Data Gas, cooling, Voice, data, power, structural Robotic Systems Robotic Systems Tools & Equipment Vehicle Interfaces GSE Suit Note: Interface with MS is logical-only. Data is routed via another Cx System.

9. Slide 9 Suit Architecture

10. Slide 10 EVA Systems Reference Architecture Methodology / Approach Stakeholders sequestered in October 2006 to define reference architecture Employ a reconfigurable suit architecture with the following goals A minimum set of hardware required to meet all mission phase requirements Meeting requirements with common components as often as technically practical Results A space suit architecture with two configurations which share many components Configuration 1 – LEA/microgravity EVA (Contingency & Unscheduled) Configuration 2 – Lunar Surface EVA Most components only developed once with a few notable exceptions: Two different soft upper torsos (SUT) because of different mobility requirements between mission phases Different TMGs and visors for contingency and surface EVA Significant possibility that most components will be extensible to long duration Outpost operations with minimal/no additional DDT&E

11. Slide 11 Reference Architecture Details Pressure Garment Subsystem Most components of the pressure garment will require new development to support CEV LEA and Contingency EVA requirements Possible exception is use of Phase VI gloves with updated certification The pressure garment for Sortie will be a combination of new development and carry over from LEA/Contingency EVA Configuration During Sortie and Outpost the Space Suit System will be composed of two Suit configurations with some shared components This architecture does not represent a classic Block delivery structure as had been envisioned Components developed for Configuration 1 (LEA/Cont EVA) will remain in use for the life of the Program Some components will be used in Configuration 2 (the Sortie and potentially Outpost suit configuration) (Lower Torso Assembly (LTA), lower arms, gloves, helmet) Some components will be different in the LEA/Cont EVA Configuration and the Sortie Configuration (Upper Torso)

12. Slide 12 Reference Architecture Details (cont.) Life Support Subsystem Configuration 1 is umbilical supported Short umbilicals for IVA operations (closed loop) Long umbilicals with Secondary O2 supply for Cont EVA (open loop) Secondary O2 also used for Configuration 2 Sortie EVA Umbilical connectors planned to be common between configurations though some upgrade may be needed for Outpost Configuration 2 Removable backpack PLSS with modular design and a moderate level of technology development in an effort to develop a PLSS that could meet Outpost requirements Rapid Cycle Amine (RCA) CO2 removal – eliminates LiOH upmass/volume Spacesuit Water Membrane Evaporator (SWME) heat rejection SWME is more robust and reliable than existing sublimator technology On-going Trade – SWME water use is twice that of other options being pursued which have much higher technology risk Lightweight Composite O2 Tanks New more robust TMG with dust mitigation

13. Slide 13 Reference Architecture Details (cont.)

14. Slide 14 LEA / Microgravity EVA - Configuration 1 Umbilicals & SOP Universal Umbilical connectors on Umbilicals & vehicles Long Umbilical (2 for EVA) – Closed Loop Short Umbilical (per crewmember) – Closed Loop Secondary Oxygen Supply (SOP/Emergency O2) Umbilicals provide, breathable gas, cooling water, power & comm, and safety tether function Enhanced Helmet hardware TMG (Cont. EVA) Helmet feed-port (120 hr survival) Analog Comm cap Flip visor Neck wedge for cant if needed Inserts for head-impact protection LCG & Bio-Med Sensors Artwork by Jeannie Corte (ESCG) Concept Drawings of the Suit System Reference Configuration Constellation Suit System Team - 26 Oct. 2006 Pressure Garment / Crew Survival 2 Umbilical connections (make before break) provide, breathable gas, cooling water, power & comm TMG/MLI similar to EMU Waist-entry SUT (patterned convolute, BSC w/multiple sizes) Phase VI gloves (updated cert.) Common LTA (integrated waist/Hip/Leg - bearing hip w/convolute joint) Walking boot (w/ disconnect) Devise (PFD) Waist containment w/Maximum Absorbency Garment (MAG) Extraction harness w/attached Personal Floatation Orthostatic intolerance mitigation

15. Slide 15 Lunar Surface EVA - Configuration 2 Enhanced Helmet hardware: TMG & lighting - Heads-Up-Display - SUT-integrated Audio - Enhanced Pressure Garment / Softgoods: TMG/MLI for relevant environment - Rear Entry Lunar SUT w/Waist & Scye Bearings - Wear/abrasion resistant softgoods - Enhanced LCG & Bio-Med Sensors Portable Life Support Subsystem (PLSS): High Pressure GOX - SWME/RCA - Potable Water in PLSS Tank - Power/CAI: Lithium Ion Batteries - C3I Processing in PLSS - Expanded set of suit sensors - Advanced Caution & Warning - On-suit Productivity Enhancements - Umbilicals & SOP: Same hardware from LEA Config. Upgrade umbilical for Recharge and Buddy Breathing/Cooling Concept Drawings of the Suit System Reference Configuration Constellation Suit System Team - 26 Oct. 2006 Artwork by Jeannie Corte (ESCG) * Hardware detailed text represents changes or additions of hardware (colored darker blue or purple) to the LEA configuration.

16. Slide 16 Ops Concepts

17. Slide 17 Mission Description ISS/CEV – Provide LEA, limited duration pressurized survival, and contingency EVA (zero-G) capability for missions to ISS for up to 6 crewmembers Lunar Outpost Buildup (former Sortie) – Provide LEA, extended duration pressurized survival (up to 120 hours), microgravity EVA capability, and surface (1/6-G) EVA capability for a lunar mission (~ 2 weeks, 1 week on surface) for up to 4 crewmembers Lunar Outpost – In addition to above, provide surface EVA capability for a lunar mission duration of up to 6 months Mars – Surface operation EVA capability on Mars for extended duration

18. Slide 18 Operational Scenarios Launch Nominal launch ops Emergency Pad Egress Orbit Survival in an unpressurized cabin Unscheduled/Contingency EVA Landing Nominal & Off-nominal Note: Photos borrowed from all legacy and current programs

19. Slide 19 Nominal Launch Ops Crew dons their suits in the O&C Building Suit-up room Some checkout of the suit will be performed using GSE Crew transfers (with closeout crew) to the pad in the Astrovan Provisions for cooling will be available Crew rides elevator to the access level (~ 280 level) Crew finishes suit-up process and ingresses CEV with assistance

20. Slide 20 Emergency Pad Egress System must allow for unassisted emergency egress Closeout crew and rescue crews assist if situation warrants Emergency escape system under review by Ground Systems Rail system being pursued as the leading design concept Bunker at base of current slidewire system will provide services Use of emergency escape vehicle (M-113) needs to be assessed

21. Slide 21 Survival in an Unpressurized Cabin Requirement at the Constellation Architecture level Allocated to CEV, LSAM, & EVA Systems Reference concept is that CEV feeds leak while crew dons suits Cabin eventually bleeds down and crew survives in their suits for the trip home Suit pressure under evaluation but may limit mobility at least during the prebreathe timeframe. Worst case (for a single vehicle) involves survival for ~120 hours Details for hydration, nutrition, and mobility need to be worked

22. Slide 22 Unscheduled / Contingency EVA Unscheduled / Contingency EVA requirement levied on the Constellation Architecture (Microgravity) Currently allocated to CEV, LSAM, and EVA Unscheduled – Mission Success Contingency – Crew Safety 2 EVAs of 4 hours (TBR) Independent of other vehicles EV1 performs task EV2 SEVA, ready to assist Currently no tasks IDd by CEV project other than LSAM – CEV transfer

23. Slide 23 Life Support: Umbilical connection to spacecraft ECLSS for breathing gas supply, CO2 scrubbing, thermal control, and bi-directional data/voice Stabilization: Handrails give EVA crewmember the means to stabilize himself at the worksite Translation Path: Handrails leading from the hatch allow EVA crewmember safely reach worksites Protection: Spacesuit TMG and helmet visor provide protection from the space environment Apollo EVA on Service Module

24. Slide 24 EVA Translation Path – 43 inch corridor centered on handrails. Free of sharp edges and other hazards. EVA Worksite – Designated area where EVA task is performed. Analyzed for compatibility with EVA work envelope, fov, body positioning, and loads. EVA External Provision Terminology

25. Slide 25 LSAM and CEV in LRO

26. Slide 26 LSAM to CEV External Transfer EVA Translation Path – 43 inch corridor centered on handrails. Free of sharp edges and other hazards.

27. Slide 27 Nominal & Off-Nominal Landing Nominal landing scenario is on land with full assistance by ground ops recovery forces Crew would likely stay suited through transport (cooling services provided) Off-nominal scenarios: Land-landing not at the designated site Water-landing In either case, the crew has the option of staying with or leaving the vehicle (appropriate survival gear will be provided by EVA & FCE)

28. Slide 28 Conclusion EVA Systems reference configuration will serve as the basis for continued ops concept and requirements generation between now and the EVA SRR Changes will be considered on a case-by-case basis as further trades and analyses are performed in the first DAC cycle between now and EVA SRR Reference architecture will be documented in the EVA Systems Architecture Description Document (Riddable at EVA SRR) EVA Systems Ops Concepts will be refined prior to the EVA SRR EVA Ops Concepts will be captured in the EVA System Ops Concept Document (Riddable at EVA SRR) Changes to the EVA Systems reference architecture and/or the Ops Concept require approval by the EVA Systems Project Control Board