eva systems 101 architecture & ops con eva systems project se&i february 2007 j. davis eva...
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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.
*
*
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