EVA Operations, Tools, and Interfaces
• Final Details for Term Projects • EVA Lessons from Apollo (Dean Eppler) • Suit Design for Planetary Exploration (Dean Eppler) • Suit Interfaces to Rovers • Videos of EVA/IVA design for NASA Small Pressurized Rover
© 2009 David L. Akin - All rights reserved U N I V E R S I T Y O F http://spacecraft.ssl.umd.edu EVA Operations, Tools, and Interfaces MARYLAND 1 ENAE 697 -Space Human Factors and Life Support Answers to Questions
• Battery (LiPo) energy storage - 150 W-hr/kg • Thermal control system is 30 kg/kW(thermal) • Habitat attached to (external) CxP power unit - power supply is SEP • Discourage use of fuel cells for rover power, due to concerns about refueling, refrigeration, and system complexity/robustness • Can’t drink the water (bring what you need) 0.9 • Mtanks < kg >=0.1(Mcontents < kg >)
U N I V E R S I T Y O F EVA Operations, Tools, and Interfaces MARYLAND 2 ENAE 697 -Space Human Factors and Life Support Boeing Initial Reference Mission (Based on NASA LSS BAA Industry Day Briefing)
♦ Initial LSS Architecture Elements Include (delivered to lunar surface prior to first crew arrival): • Landers • Two 2-person Pressurized Rovers (with suitlocks) • Four EVA suits • One Mobile Power Generation & Storage Unit • Two Mobility Chassis • One Crew Habitat • One Ascent Stage (used for Earth return) ♦ Crew Lunar Surface Mission • Regular excursions for lunar exploration & science − Deploy instrument packages, gather rock & regolith samples, and evaluate lunar topography − EVA to nearby locations or use pressurized rovers • Mission Duration: 7 – 28 days with 30-day contingency ♦ Initial Functions Set DRAFT• Mission: EVA, Comm, Habitat Health Monitoring, Stowage • Survivability: Waste Management, Life Support, Crew Hygiene, Food Management • Environmental Safety: Radiation Protection ♦ Lunar Surface Systems Assumptions Initial: Full Complement Outpost: • Pressurized rovers (2) • Pressurized rovers (2) • Mobile power unit (1) • Mobile power unit (1) • Habitat (1) • ATHLETE (1) • Landers • Logistics Unit (1) • Ascent Stage (1) • Unpressurized rover (1) • EVA Suits (4) • Airlocks (2) • Habitat(s) (TBD) • Landers • ISRU Plant (1)
Page ECLSS/EVA/Crew System Assumptions DRAFTDRA
Page FT Lunar Communications Terminal (CxAT Lunar Project, SAIF Version 99, 1, 3)
Description
The Lunar Communication Terminal (LCT) provides local communications around its location via a wide area network as well as Earth communications via a relay or Direct-to-Earth (DTE) using Sband and Kband links. Navigation services are provided over Sband.
Power Volume Mass Breakdown Structure 1.0 Structure 60.375 kg Maximum Generation 0 Energy Storage 0 Pressurized Volume (m3) TBD Capability (W) Capacity (W-hr) 2.0 Protection 0 kg
3 Active Average Day 421 Active Average Eclipse 421 Habitable Volume (m ) TBD 3.0 Propulsion 0 kg Requirement (W) Requirement (W) 4.0 Power 9.8 kg Standby Average Day 33 Standby Average Eclipse 33 Airlock Volume (m3) TBD Requirement (W) Requirement (W) 5.0 Control 0 kg
Comments 6.0 Avionics 182.962 kg DRAFTMass 7.0 Environment 42.751 kg Growth percentages reflect the values used in the current MEL. We have additional information in the MELs that 8.0 Other 0 kg breaks down contingency further, resulting in an average LCT value of 22%. 9.0 Growth 0 kg
Dry Mass 295.89 kg
10.0 Non-Cargo 0 kg
11.0 Cargo 0 Kg
Inert Mass 295.89 kg
12.0 Non-Propellant 0 kg
13.0 Propellant 0 kg
David Israel (Focus Element Member): GSFC, (301) 286-5294, David.J.Israel@nasa.gov Total Mass 295.89 kg
5 TS3 Power Support Unit (CxAT Lunar Project, SAIF Version 98, 1, 5)
Description Batteries This element was formerly known as the Integrated Cargo Pallet. The PSU is an interface structure between the lander and delivered cargos and houses the primary power storage and generation systems for the architecture. The PSU is designed to interface with the Tri-ATHLETE heavy lift mobility system for offloading and transport on the lunar surface. The structure includes adjustable jacklegs for leveling and supporting the PSU on the surface. Power systems on the PSU can be connected together to provide increased capability to the outpost. Note: Two 5.5 m diameter Orion- class solar arrays are not shown
Power Volume Mass Breakdown Structure 1.0 Structure 418 kg Maximum Generation 8.8 Energy Storage 150 Pressurized Volume (m3) 0 Capability (kW) Capacity (kW-hr) 2.0 Protection 0 kg
3 Active Average Day 0 Active Average Eclipse 0 Habitable Volume (m ) 0 3.0 Propulsion 0 kg Requirement (W) Requirement (W) 4.0 Power 1496 kg Standby Average Day 0 Standby Average Eclipse 0 Airlock Volume (m3) 0 Requirement (W) Requirement (W) 5.0 Control 27 kg
Comments 6.0 Avionics 27 kg DRAFTMass 7.0 Environment 30 kg All avionics items listed are developed and provided by the Communications and Navigation Element Team. 8.0 Other 0 kg DDT&E for these elements should not be duplicated. 9.0 Growth 598 kg Power "Maximum Generation Capability" (8.8 kW) assumes losses due to solar array drive assembly power and array Dry Mass 2596 kg regulator unit inefficiency and is beginning of life (BOL). It includes 30% margin. Degradation due to dust accumulation and radiation is assumed to be 2.2% per year. 10.0 Non-Cargo 0 kg
11.0 Cargo 0 Kg
Inert Mass 2596 kg
12.0 Non-Propellant 0 kg
13.0 Propellant 0 kg
Sharon Jefferies (Integration and Design Lead): Langley Research Center, 757-864-4248, [email protected] Total Mass 2596 kg
6 Mobile Power Unit (CxAT Lunar Project, SAIF Version 87, 1, 7)
Description Orion Solar Arrays (5.5m diameter) The MPU is a set of solar arrays and additional batteries that is combined with a Crew Mobility Chassis (CMC) to provide a mobile power source for the architecture. The solar arrays are the same as the ones integrated with the habitation elements carried by the Power Support Units (two 5.5 m diameter Orion class arrays). Additional Battery Pack (10 kW-hr))
Power Volume Mass Breakdown Structure 1.0 Structure 130 kg Maximum Generation 8.8 Energy Storage 10 Pressurized Volume (m3) 0 Capability (kW) Capacity (kW-hr) 2.0 Protection 0 kg
3 Active Average Day 0 Active Average Eclipse 0 Habitable Volume (m ) 0 3.0 Propulsion 0 kg Requirement (W) Requirement (W) 4.0 Power 463 kg Standby Average Day 0 Standby Average Eclipse 0 Airlock Volume (m3) 0 Requirement (W) Requirement (W) 5.0 Control 0 kg
Comments 6.0 Avionics 0 kg DRAFTMass 7.0 Environment 30 kg Mass for the Crew Mobility Chassis is not included in this breakdown. 8.0 Other 0 kg
Power 9.0 Growth 187 kg "Maximum Generation Capability" (8.8 kW) assumes losses due to solar array drive assembly power and array regulator unit inefficiency and is beginning of life (BOL). It includes 30% margin. Degradation due to dust Dry Mass 810 kg accumulation and radiation is assumed to be 2.2% per year. 10.0 Non-Cargo 0 kg
11.0 Cargo 0 Kg
Inert Mass 810 kg
12.0 Non-Propellant 0 kg
13.0 Propellant 0 kg
Josh Freeh (Focus Element Member): Glenn Research Center, 216-433-5014, [email protected] Total Mass 810 kg
7 Crew Mobility Chassis (CxAT Lunar Project, SAIF Version 34, 1, 9)
Description
The Crew Mobility Chassis is a roving vehicle designed to carry up to 4 crewmembers (2 nominally) in an unpressurized environment or in a pressurized cab. The chassis can support up to 3000 kg at nominal speeds and greater payloads at reduced speeds. The chassis has interfaces to connect tools for outpost support operation. The chassis can be controlled directly through the chassis driving kit or the pressurized crew cab, tele-robotically, or autonomously.
Power Volume Mass Breakdown Structure 1.0 Structure 571 kg Maximum Generation 0 Energy Storage 20 K Pressurized Volume (m3) 0 Capability (W) Capacity (W-hr) 2.0 Protection 0 kg
3 Active Average Day * Active Average Eclipse * Habitable Volume (m ) 0 3.0 Propulsion 0 kg Requirement (W) Requirement (W) 4.0 Power 104 kg Standby Average Day 100 Standby Average Eclipse 100 Airlock Volume (m3) 0 Requirement (W) Requirement (W) 5.0 Control 17 kg
Comments 6.0 Avionics 53 kg
7.0 Environment 0 kg DRAFT* Active power is a function of vehicle speed, gross weight, and soil condition. 8.0 Other 0 kg
9.0 Growth 223.5 kg
Dry Mass 968.5 kg
10.0 Non-Cargo 0 kg
11.0 Cargo 0 Kg
Inert Mass 968.5 kg
12.0 Non-Propellant 0 kg
Robert Ambrose (Focus Element Lead): Johnson Space Center, 281-244-5561, [email protected] 13.0 Propellant 0 kg Susan Burns (Focus Element Member): Johnson Space Center, 281-483-1541, [email protected] Total Mass 968.5 kg Sharon Jefferies (Integration and Design Lead): Langley Research Center, 757-864-4248, [email protected] 8 Chassis Driving Kit (CxAT Lunar Project, SAIF Version 53, 1, 8)
Description
The Chassis Driving Kit is a pair of upright interfaces that allow suited crew to mount and drive the rover. The kits are easy to remove or install to permit rapid conversion of a mobility system to an unpressurized rover. The ride-along adapter is a structure device that allows 2 crewmembers to ride the CMC (unpressurized environment).
Power Volume Mass Breakdown Structure 1.0 Structure 148 Kg Maximum Generation 0 Energy Storage 0 Pressurized Volume (m3) 0 Capability (W) Capacity (W-hr) 2.0 Protection 0 kg
3 Active Average Day 200 Active Average Eclipse 200 Habitable Volume (m ) 0 3.0 Propulsion 0 kg Requirement (W) Requirement (W) 4.0 Power 2.6 kg Standby Average Day TBD Standby Average Eclipse TBD Airlock Volume (m3) 0 Requirement (W) Requirement (W) 5.0 Control 3.2 kg
Comments 6.0 Avionics 0 kg DRAFTMass 7.0 Environment 0 kg The chassis crew kit is assumed to always ship the crew station as a pair (2 units) and the ride-along adapter (1 8.0 Other 0 kg unit). 9.0 Growth 46.14 kg
Dry Mass 199.94 kg
10.0 Non-Cargo 0 kg
11.0 Cargo 0 Kg
Inert Mass 199.94 kg
12.0 Non-Propellant 0 kg
Robert Ambrose (Focus Element Lead): Johnson Space Center, 281-244-5561, [email protected] 13.0 Propellant 0 kg Sharon Jefferies (Integration and Design Lead): Langley Research Center, 757-864-4248, [email protected] Total Mass 199.94 kg
9 Small Pressurized Rover – Pressurized Crew Cab (CxAT Lunar Project, SAIF Version 55, 1, 7)
Description
The Small Pressurized Rover (SPR) provides a pressurized environment for a crew of two to conduct extended-range exploration of the moon, and can carry four crew members for contingency operations. The SPR consists of a Chariot MC and a pressurized crew cab (PCC). The SPR uses two suitports to facilitate quick egress for EVA activities and includes externally mounted manipulators to allow crew to interact with the surface from within the pressurized environment. The SPR incorporates a common hatch to facilitate docking with a habitat element, and, with its built-in shielding, the SPR fulfills the safe-haven role by providing a radiation shelter for the crew that is accessible from the habitat or while roving on the surface.
Power Volume Mass Breakdown Structure 1.0 Structure 846 kg Maximum Generation 0 Energy Storage 100 Pressurized Volume (m3) TBD Capability (W) Capacity (W-hr) K 2.0 Protection 2.3 kg
3 Active Average Day 1000 Active Average Eclipse 1000 Habitable Volume (m ) TBD 3.0 Propulsion 0 kg Requirement (W) Requirement (W) 4.0 Power 568 kg Standby Average Day 300 Standby Average Eclipse 300 Airlock Volume (m3) 0 Requirement (W) Requirement (W) 5.0 Control 0 kg
Comments 6.0 Avionics 103.33 kg DRAFT7.0 Environment 265.1 kg 8.0 Other 196.8 kg
9.0 Growth 294.3 kg
Dry Mass 2575.9 kg
10.0 Non-Cargo 0 kg
11.0 Cargo 0 Kg
Inert Mass 2575.9 kg
12.0 Non-Propellant 0 kg
Michael Gernhardt (Focus Element Lead): Johnson Space Center, 281-244-8977, [email protected] 13.0 Propellant 0 kg Andrew Abercromby (Focus Element Member): Johnson Space Center, 281-483-8603, [email protected] Total Mass 2575.9 kg Robert Ambrose (Focus Element Lead): Johnson Space Center, 281-244-5561, [email protected] Sharon Jefferies (Integration and Design Lead): Langley Research Center, 757-864-4248, [email protected] 10 Unpressurized Rover Interfaces
• Tests performed in 2000 by NASA JSC (CTSD) in parabolic flight – A7L-B – H-suit (Mark III) – I-suit (first generation) – D-suit • NASA Report JSC-39922
U N I V E R S I T Y O F EVA Operations, Tools, and Interfaces MARYLAND 11 ENAE 697 -Space Human Factors and Life Support D-Suit Sitting
U N I V E R S I T Y O F EVA Operations, Tools, and Interfaces MARYLAND 12 ENAE 697 -Space Human Factors and Life Support A7L-B Sitting
U N I V E R S I T Y O F EVA Operations, Tools, and Interfaces MARYLAND 13 ENAE 697 -Space Human Factors and Life Support H-Suit Sitting
U N I V E R S I T Y O F EVA Operations, Tools, and Interfaces MARYLAND 14 ENAE 697 -Space Human Factors and Life Support I-Suit Sitting
U N I V E R S I T Y O F EVA Operations, Tools, and Interfaces MARYLAND 15 ENAE 697 -Space Human Factors and Life Support Step Heights
D-Suit H-Suit I-Suit U N I V E R S I T Y O F EVA Operations, Tools, and Interfaces MARYLAND 16 ENAE 697 -Space Human Factors and Life Support Videos Shown in Class
• 090118.NASA-SPR.M04.mov - description of suitport • 090118.NASA-SPR.M011.mov - guided tour of rover by Mike Gernhardt and Rob Ambrose • 090118.NASA-SPR.M012.mov - suit ingress • 090118.NASA-SPR.M013.mov - suitport egress • 090118.NASA-SPR.M14.mov - interior tour with Rob Ambrose • 090118.NASA-SPR.M15.mov - interior tour
U N I V E R S I T Y O F EVA Operations, Tools, and Interfaces MARYLAND 17 ENAE 697 -Space Human Factors and Life Support