EVA Systems 101 Architecture & Ops Con

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

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. 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. 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. EVA System Description

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. 6

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

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

9. Suit Architecture

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 allmission 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. 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. 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. Reference Architecture Details (cont.)

14. LEA / Microgravity EVA - Configuration 1 • 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 • 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 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 Artwork by Jeannie Corte (ESCG)

15. Lunar Surface EVA - Configuration 2 Enhanced LCG & Bio-Med Sensors Power/CAI: Lithium Ion Batteries - C3I Processing in PLSS - Expanded set of suit sensors - Advanced Caution & Warning - On-suit Productivity Enhancements - 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 - Concept Drawings of the Suit System Reference Configuration Constellation Suit System Team - 26 Oct. 2006 Umbilicals & SOP: Same hardware from LEA Config. Upgrade umbilical for Recharge and Buddy Breathing/Cooling Portable Life Support Subsystem (PLSS): High Pressure GOX - SWME/RCA - Potable Water in PLSS Tank - * Hardware detailed text represents changes or additions of hardware (colored darker blue or purple) to the LEA configuration. Artwork by Jeannie Corte (ESCG)

16. Ops Concepts

17. Mission Description • 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. 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. 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. 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. 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. 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 ID’d by CEV project other than LSAM – CEV transfer

23. Apollo EVA on Service Module Life Support: Umbilical connection to spacecraft ECLSS for breathing gas supply, CO2 scrubbing, thermal control, and bi-directional data/voice Protection: Spacesuit TMG and helmet visor provide protection from the space environment 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

24. EVA External Provision Terminology 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.

25. LSAM and CEV in LRO

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

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. 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