EVA Systems 101Architecture & Ops Con

EVA Systems 101Architecture & Ops Con

EVA Systems Project SE&IFebruary 2007J. Davis

EVA Systems Project SE&IFebruary 2007J. Davis

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

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

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

Slide 5

EVA System Description

Slide 66

Constellation Architecture

CEV

LSAM

EVA Systems

Flight Crew Equipment

MTV

DAV

CLV

CaLV

Ground Systems

Mission Systems

Resource Utilization

Robotic Systems

Power Systems

Surface Mobility

Habitat

C&T Networks

ISS

Architecture Level

System Level

Future

External

Constellation System Hierarchy

The EVA System includes more than ‘Spacewalk’ hardware.Constellation is striving for one suit system to be used forLaunch/Entry (crew survival) and EVA.

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Slide 77

Constellation Architecture

CEV

LSAM

EVA Systems

Flight Crew Equipment

MTV

DAV

CLV

CaLV

Ground Systems

Mission Systems

Resource Utilization

Robotic Systems

Power Systems

Surface Mobility

Habitat

C&T Networks

ISS

Architecture Level

System Level

Future

External

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

Slide 88

EVA System External Interfaces

EVA SystemMission Systems

Mission Systems

GroundSystems

GroundSystems

OrionCEV

OrionCEV

ARESCLV, CaLV

ARESCLV, CaLV

Gas, cooling,Voice, data,

powerstructural

Flight Crew EquipmentFlight Crew Equipment

LSAMLSAMSurface Mobility

Surface Mobility

HabitatHabitat

Data

Gas, cooling,Voice, data,

power,structural

RoboticSystems

RoboticSystems

Tools & Equipment

Vehicle Interfaces GSE

Suit

Note: Interface with MS is logical-only. Data is routed via another Cx System.

Slide 9

Suit Architecture

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

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)

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

Slide 13

LEA Contingency EVA Sortie OutpostPressure Suit Assembly

Attachment rings and bearings Common, scalable, dust resistent Cycle life in dust environmentHelmet Helmet with visor up/down,

conformal capability, feedportVisors (eye protection) ORU-able Protective Visor / Shade-

TBRVisor / Shade assy

Upper Torso (including upper arms) Soft Upper Torso (SUT) 1, waist entry

SUT 2, rear entry (w/ waist bearing)

Lower ArmGloves Restraint Ph 6 (update cert for 8 psi -TBR)Glove thermal / durability IV Outerlayer Current Ph 6 TMG New TMGLower Torso Assemby (LTA) Waist / Hip /Leg integrated Upgrade with ORU DisconnectsOrtho-static intolerance garment New - mechanical counterpressure N/A N/A N/A

Boots Walking boot Installable over-bootWaste Management MAG MAG MAG Regenerable Diaper

Life Support SystemUmbilical Connectors Cycle life in dust environmentLong Umbilical na Yes, 2 onboardShort Umbilical Yes, up to 6 per mission plus spare Update for recharge

Insulation (TMG) na SOA ORU TMG Over-garment, 2 onboard

New, more robust SOA ORU TMG plus new layer for dust mitigation

PLSS Core Tech. na - If RCA for Sortie is common w/ CEV RCA need to start now

na SWME/RCA/GOX w/lightweight composite tanks/separate "chicken

soup" pumpEmergency O2 Systems ACES -like EOS for Egress SOP for EVA (3000psi (refillable)),

buddy Umbilical for IVA/EVA backup

umbilical length delta

Emergency Thermal Systems Buddy / umbilical for cooling length delta Cycle life in dust environment

Power / CAIAudio (Front End) New Comm caps Integrated comm - built into SUT 2Batteries Power thru umbilical Lithium IonAudio Processing / Data transmission

all analog all analog Analog in helmet and C3I processing in PLSS

Cx Radio none none Digital Radio and AntennaBiomed Sensors none planned, scar for via umbilical none planned, scar for via umbilical Heart rate and rhythm sensors

integrated into vest or LCVGCaution/ Warning System Analog signal thru comm cap Analog signal thru comm cap New CWS with automated advisory

capabilityDisplay none except gauge none except gauge Non-graphic text display (external).

Paper cuff checklistHUD

Video Capable none umbilical scar only Yes

Legend: No development required Development Activity No change from Previous config. Significant risk of new development

Reference Architecture Details (cont.)

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

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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

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

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* Hardware detailed text represents changes or additions of hardware (colored

darker blue or purple) to the LEA configuration.

* Hardware detailed text represents changes or additions of hardware (colored

darker blue or purple) to the LEA configuration.

Slide 16

Ops Concepts

Slide 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

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

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

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

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

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 ID’d by

CEV project other than LSAM – CEV transfer

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

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

Slide 25

LSAM and CEV in LRO

Slide 26

LSAM to CEV External Transfer

EVA Translation Path – 43 inch corridor centered on handrails. Free of sharp edges and other hazards.

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)

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