Activity LEAG Report
Planetary Sciences Subcommittee
June 23, 2008
Lunar Exploration Roadmap. LEAG Meeting. Lunar Science Conference CxAT-Lunar Interface Commercial Development Summit
Lunar Exploration Roadmap
The Charge from the NAC
The Science Committee recommends that the Lunar Exploration Analysis Group (LEAG) be tasked to prepare a "Lunar Goals Roadmap" that maps science goals to objectives, and to observations and measurements. This roadmap should include an assessment of needed technology developments, areas of potential coordinated activities for commercial and international participation, and potential feed-forward activities for the exploration of Mars and beyond.
LEAG Report to the PSS: June 23, 2008
Exploring the Moon in the 21st Century: Themes, Goals, Objectives, Investigations, and Priorities, 2008 A Community Effort Coordinated by the Lunar Exploration Analysis Group
Themes: Why are we going to the Moon? Theme 1: Pursue scientific activities to address fundamental questions about the solar system, the universe, and our place in them. Theme 2: Use the Moon to prepare for future missions to Mars and other destinations. Theme 3: Extend sustained human presence to the Moon to enable eventual settlement.
LEAG Report to the PSS: June 23, 2008
Exploring the Moon in the 21st Century: Themes, Goals, Objectives, Investigations, and Priorities, 2008 A Community Effort Coordinated by the Lunar Exploration Analysis Group
5 SATs have been formed. SATs to report by June 30th. Web input from the community is being incorporated. Further input at the Lunar Science Conference in July. Review of draft will be requested from SMD, ESMD, and SOMD. Presentation at the LEAG meeting. Presentation at HQ.
LEAG Report to the PSS: June 23, 2008
Lunar Science Conference July 20-23, 2008 NASA-AMES
LEAG has an afternoon session on Tuesday 22 July. Presentations from key SATs. Breakout sessions for community input. Input wrapped into Roadmap development.
LEAG Report to the PSS: June 23, 2008
LEAG Meeting 2008
October 28-31, 2008 (won't coincide with LRO launch!). Joint with ILEWG and SRR. Radisson Resort at the Port, in Cape Canaveral, Florida. Plenary and concurrent sessions - focused on questions pertinent to achieving the "vision" - similar to the last LEAG meeting. 1st announcement is out. 2nd announcement imminent.
LEAG Report to the PSS: June 23, 2008
LEAG Meeting 2008
Themes
LEAG: Sustainable Moon. ILEWG: International Moon. SRR: Productive Moon.
Highlights
Lunar Google X-Prize Team presentations. Special Session: Kaguya, Chang'e-1, Chandrayaan-1, LRO. Sessions focused around key questions relevant to the community and lunar exploration.
LEAG Report to the PSS: June 23, 2008
LEAG Meeting 2008
Day 1: PLENARY What pathways need to be developed/obstacles overcome to enhance the implementation of the GES? Space Agency Reports (status of upcoming missions, priorities for proposed robotic exploration).
LEAG Report to the PSS: June 23, 2008
LEAG Meeting 2008
Day 2 - Morning
LEAG: What is required to reduce dependency and cost of human exploration of the Moon for sustained presence? ILEWG: What is the status of Space Law as it relates to the Moon and what policy and regulation issues need to be addressed for productive international exploration of the Moon? SRR: What are the steps to extensive use of lunar resources?
Day 2 - Afternoon
LEAG: What opportunities are afforded within the current architecture for commercial on ramps and how can these be facilitated? ILEWG: What are the logical architectures, and open implementation to allow effective integration of international elements? SRR: What is the current state of ISRU development?
LEAG Report to the PSS: June 23, 2008
LAT-2 Review - Potential Task
Initial Charge
Further lunar exploration architecture concept developments should be reviewed by the LEAG, which represents a variety of lunar exploration stake holders and partners, including the science community, to assess how well continued developments align with the recommendations of the NAC from the 2007 Tempe workshop.
We have declined this request, but suggested that instead LEAG be involved with the CxAT Lunar effort awaiting NAC response.
LEAG Report to the PSS: June 23, 2008
Commercial Development Summit on NASA's Lunar Activities
Tuesday, May 13, 2008 - NASA-HQ
Who: Programmatic, technical, science, commercial and administrative support authorities regarding the planning of NASA's lunar activities. What: A one-day meeting that provides a comprehensive overview of NASA's many lunar science and technology programs. An output from the meeting will be a narrative document and accompanying set of presentation charts that will provide the basis of any follow-on activities. Why: The information collected will be used to identify opportunities for cooperation and coordination between the programs, and to assess the viability of a commercial development approach to meet the various lunar science and technology needs.
LEAG Report to the PSS: June 23, 2008
Lunar Capability Concepts Review
LEAG/NAC invite to the LCCR June 18-20, 2008. Johnson Space Center
LEAG Report to the PSS: June 23, 2008
LEAG Report to the PSS: June 23, 2008
Lunar Capability Concept Review (LCCR)
Transportation Systems Only
June 18 20, 2008 Report to the PSS
LCCR Agenda
Date June 18 Time 8:00 8:15 am 8:15 9:00 am 9:00 9:15 am 9:15 10:00 am 10:00 11:00 am 11:00 11:30 am 11:30 am 2:00 pm 2:00 4:30 pm 4:30 5:30 pm June 19 8:00 8:30 pm 8:30 10:30 am 10:30 am 12:30 pm 12:30 1:00 pm 1:00 3:00 pm 3:00 5:00 pm 5:00 5:30 pm June 20 8:00 9:00 am 9:00 10:00 am 10:00 10:30 am 10:30 11:00 am 11:00 11:30 am
June 18 - 20, 2008
Topic Welcome / Introduction 01: LCCR Overview 02: Lunar Requirements Summary 03: CxAT_Lunar Study Process 04: LSS Concepts Lunch 05: Altair System 06: Ares V System 07: Ground Operations 09: Integrated Performance and Mission Design 10: Strategic Analysis Lunch 11: HLR POD Architecture 12: LCCR Product Summary and Forward Plan 13: Architecture Summary and Next Steps 14: MCR Wrap-up Altair 15: MCR Wrap-up Ares V 16: LCCR Success Criteria Review Summary / Conclusions Board Discussion
Section 00: LCCR Agenda
Presenter Hanley / Muirhead Knotts Knotts Joosten Culbert Hansen / Connolly Creech Quinn Martinez Falker Drake Parkinson Muirhead Hansen / Graham Creech Knotts Hanley
Page 15
08: Ares V and Altair Margins Strategies and Basis Muirhead
Components of Program Constellation
Earth Departure Stage
Crew Exploration Vehicle
Heavy Lift Launch Vehicle Crew Launch Vehicle Lunar Lander
June 18 - 20, 2008
Section 05: Altair System
Page 16
Typical Lunar Reference Mission
MOON
Vehicles are not to scale.
100 km Low Lunar Orbit
Lander Performs LOI
Ascent Stage Expended
Earth Departure Stage Expended
Low Earth Orbit
Service Module Expended
EDS, Lander
CEV
Direct Entry Land Landing
EARTH
June 18 - 20, 2008 Section 05: Altair System Page 17
Background
VSE ESAS
Global Exploration Strategy
LAT1 LAT2
CxAT Lunar
June 18 - 20, 2008
Section 03: CxAT_Lunar Study Process
Page 18
LCCR Scope
LCCR will define a Point of Departure (POD)* transportation architecture for the CxP Lunar Capability including capabilities to:
Deliver and return crew to the surface of the moon for short durations, i.e. Human Lunar Return (HLR) Enable establishment of a lunar outpost
This review focuses on the conceptual designs and key driving requirements for Ares V and Altair (crewed and cargo) This review assumes the capabilities of Ares I and Orion for the lunar missions This review will show how the POD transportation architecture, including EVA and Ground Ops, supports a range of mission campaigns and possible surface architecture solutions
Specific Lunar Surface Systems definition is not part of this review
*This is a POD transportation architecture and NOT the final baseline
June 18 - 20, 2008 Section 01: LCCR Overview Page 19
CxP L2 Lunar Design Reference Missions
DRM 1 : Lunar Sortie Crew DRM
- This mission lands anywhere on the Moon, uses only on-board consumables, and leaves within ~1 week. This mission enables exploration of high-interest science sites, scouting of Lunar Outpost locations, technology development objectives, and the capability to perform EVAs.
DRM 2 : Uncrewed Cargo Lander DRM
- Used to support an Outpost, help build one, or merely preposition assets for a subsequent Sortie Lander, this uncrewed mission lands anywhere on the Moon, and has enough resources to sustain itself until a component of the Lunar Surface Systems takes over.
DRM 3 : Visiting Lunar Outpost Expedition DRM
- Analogous to an assembly flight to ISS, this mission lands at the site of a complete Outpost or one under construction, and allows crewmembers to extend their stay by using assets of the Outpost rather than only what is carried onboard their Lander.
DRM 4 : Resident Lunar Outpost Expedition DRM
- Realizing one of the goals of US Space Policy, this mission allows a sustained human presence on the surface of the Moon, since it follows a single crew of four to the surface, transitions them to a habitat at an Outpost, and gets them back to Earth after transitioning over to a replacement crew.
DRM 5 : Outpost Remote DRM
- This mission is separated in function from the other DRMs by focusing only on those Lunar Surface Systems which need to operate without human intervention, either because humans are not present to operate them, or the task is more easily performed in an autonomous or automatic manner.
June 18 - 20, 2008 Section 02: LCCR Requirements Summary Page 20
Building on a Foundation of Proven Technologies
- Launch Vehicle Comparisons 122 m (400 ft)
PPBE Submit (51.0.39) Crew Lunar Lander
Altair
Overall Vehicle Height, m (ft)
91 m (300 ft)
Orion
Earth Departure Stage (EDS) (1 J2X) 234.5 t (517.0k lbm) LOX/LH2
61 m (200 ft)
Upper Stage (1 J2X) 137.1 t (302.2k lbm) LOX/LH2 5-Segment Reusable Solid Rocket Booster (RSRB) Core Stage (5 RS68B Engines) 1,435.5 t (3,164.8k lbm) LOX/LH2 2 5-Segment RSRBs
S-IVB (1 J2 engine) 108.9 t (240.0k lbm) LOX/LH2 S-II (5 J2 engines) 453.6 t (1,000.0k lbm) LOX/LH2 S-IC (5 F1) 1,769.0 t (3,900.0k lbm) LOX/RP-1
30 m (100 ft)
0
Space Shuttle
Height: 56 m (184 ft) Gross Liftoff Mass: 2,041.2 t (4,500.0k lbm) Payload Capability: 25.0 t (55.1k lbm) to Low Earth Orbit (LEO)
DAC 2 TR 5
Ares I
Height: 99 m (325 ft) Gross Liftoff Mass: 927.1 t (2,043.9k lbm) Payload Capability: 25.6 t (56.5k lbm) to LEO
Ares V
Height: 110 m (361 ft) Gross Liftoff Mass: 3,374.9 t (7,440.3k lbm) Payload Capability: 63.6 t (140.2k lbm) to TLI (with Ares I) 55.6 t (122.6k lbm) to Direct TLI 143.4 t (316.1k lbm) to LEO
Saturn V
Height: 111 m (364 ft) Gross Liftoff Mass: 2,948.4 t (6,500.0k lbm) Payload Capability: 44.9 t (99.0k lbm) to TLI 118.8 t (262.0k lbm) to LEO
Page 21
June 18 - 20, 2008
Section 06: Ares V System
Ares V Trade Space
Core Booster 5 Segment PBAN Steel Case Reusable Standard Core W/ 5 RS-68 Opt. Core Length / 6 Core Engines
+5.0 t
Common Design Features
Composite Dry Structures for Core Stage, EDS & Shroud Metallic Cryo Tanks for Core Stage & EDS RS-68B Performance: Isp = 414.2 sec Thrust = 797k lbf @ vac J-2X Performance: Isp = 448.0 sec Thrust = 294k lbf @ vac Shroud Dimensions: Barrel Dia. = 10 m Usable Dia. = 8.8 m Barrel Length = 9.7 m 1.5 Launch TLI Capability
51.0.39
51.0.46
Spacers: 1
63.6 t
+6.1 t
68.6 t
+6.1 t +5.0 t
5 Segment HTPB Composite Case Expendable
51.0.40
51.0.47
Spacers: 1
69.7 t
-2.3 t
74.7 t
-3.6 t +3.7 t
5.5 Segment PBAN Steel Case Reusable
51.0.41
51.0.48
Spacers: 0
67.4 t
LCCR Initial Reference
71.1 t
June 18 - 20, 2008
Section 03: CxAT_Lunar Study Process
Page 22
Recommendations
Approach
Applied Margins/Reserves Methodology to Altair & Ares V (net loss of architecture "performance") Developed higher fidelity mission analysis techniques (net gain of architecture "performance")
Result
Lunar Architecture still requires ~12% additional performance Higher performance Ares V options required Altair prop loading and loiter requirements determined
Post-LOI Loiter Time
June 18 - 20, 2008 Section 03: CxAT_Lunar Study Process Page 23
Altair Wet Mass
Crew Optimized
Delta-V
Altair Wet Mass
Cargo Optimized
Recommended New Point of Departure
- Vehicle 51.0.48 -
Vehicle 51.0.48 recommended
21.7 m 10 m
6 Engine Core, 5.5 Segment PBAN Steel Case Booster Provides Architecture Closure with Margin
23.2 m
Recommend Maintaining Vehicle 51.0.47 with Composite HTPB Booster as Ares V Option
116.2 m
10 m
71.3 m 58.7 m
Final Decision on Ares V Booster at Constellation Lunar SRR (2010) Additional Performance Capability if needed for Margin or requirements Allows for competitive acquisition environment for booster
Near Term Plan to Maintain Booster Options
Fund key technology areas: composite cases, HTPB propellant characterization Competitive Phase 1 Industry Studies
NOTE: These are MEAN numbers
June 18 - 20, 2008
Section 06: Ares V System
Page 24
Summary
Ares V Initial 2008 Capability (51.0.39) exceeds Saturn Capability by ~30% Ares V LCCR analysis focused on meeting lunar requirements and developing margin Ares V is sensitive to Loiter, Attitude, Power, and Altitude requirements in addition to payload performance Recommended new POD Ares V can meet current HLR requirements with ~6 t of Margin
Additional budget required (~$1.7BRY) for the 5.5 Segment PBAN Booster and 6 Engine Core Plan to maintain new composite HTPB booster as an option
Additional analysis required to determine Ares V PLOM and PLOC contributions for CARD recommendations
June 18 - 20, 2008
Section 06: Ares V System
Page 25
Altair Lunar Lander
4 crew to and from the surface
Seven days on the surface Lunar outpost crew rotation
Global access capability Anytime return to Earth Capability to land 14 to 17 metric tons of dedicated cargo Airlock for surface activities Descent stage:
Liquid oxygen / liquid hydrogen propulsion
Ascent stage:
Hypergolic Propellants or Liquid oxygen/methane
June 18 - 20, 2008
Section 05: Altair System
Page 26
Configuration Variants
Sortie Variant
45,000 kg Descent Module Ascent Module Airlock
Outpost Variant
45,000 kg Descent Module Ascent Module
Avionics Mass Available for Payload
Power Structures and Mechanisms
Manager's Reserve Propulsion
Thermal Control Life Support Other Non-Propellant Fluids
Cargo Variant
53,600 kg Descent Module Cargo on Upper Deck
Propellant
Sortie Mission Lander
June 18 - 20, 2008 Section 05: Altair System Page 27
Design Approach
Project examined the multitude of concepts developed in the post-ESAS era, took lessons learned and began to develop a real design. Altair took a true risk informed design approach, starting with a minimum functionality design and adding from there to reduce risk. Lunar Design Analysis Cycle (LDAC) 1 developed a "minimum functional" vehicle.
"Minimum Functionality" is a design philosophy that begins with a vehicle that will perform the mission, and no more than that Does not consider contingencies Does not have added redundancy ("single string" approach) Provides early, critical insight into the overall viability of the end-to-end architecture Provides a starting point to make informed cost/risk trades and consciously buy down risk A "Minimum Functionality" vehicle is NOT a design that would ever be contemplated as a "flyable" design!
LDAC-2 determined the most significant contributors to loss of crew (LOC) and the optimum cost/risk trades to reduce those risks. LDAC-3 (current LDAC) is assessing biggest contributors to loss of mission (LOM) and optimum cost/risk trades to reduce those risks. Goal of the design process is to do enough real design work to understand and develop the requirements for SRR.
June 18 - 20, 2008 Section 05: Altair System Page 28
LDAC-2 Overview
The initial Lander Design and Analysis Cycles (May-November 2007) created a "minimal functionality" lander design that serves as a baseline upon which to add safety, reliability and functionality back into the design with known changes to performance, cost and risk. LDAC-2 completed in May 2008. Goal was to "buy down" Loss of Crew (LOC) risks. "Spent" approximately t 1.3 to buy down loss of crew (LOC) risks. "Spent" an additional 680kg on design maturity.
Sum of System Contributions to LOC/ Mass Available for Payload
1.8E-01 1.6E-01 1.4E-01 1.2E-01 1.0E-01 2000 8.0E-02 6.0E-02 4.0E-02 1000
1 in 6 3652 kg
4000 3500 3000 2500
1671 kg
1500
Individual Subsystem Contribution to LOC: Events\Hazards Life Support Thermal Propulsion Structures and Mechanisms Power Avionics Mass Available for Payload
500 kg minimum payload
2.0E-02
500 0
1 in 206
0.0E+00
LDAC-1
June 18 - 20, 2008
LDAC-2
Section 05: Altair System Page 29
mass (kg)
P(LOC)
Launch Shroud
Packaging the lander within the Ares V launch shroud is akin to building a "ship in a bottle" Ares V descent stage structure and landing gear designed to package within a 10 meter launch shroud (8.8 meter diameter dynamic envelope)
Migration of Structural Configuration to 10m Shroud
Key features
Assumed 8.8m Dynamic Envelope (but not a hard number) Scaled LDAC1 -Delta w/No Major Configuration Changes Incorporated Updates for 10m Shroud & For Increased V Single CAD Update, Two Analysis Cases (10m & 10m + V) AL and AM Global Geometry Unchanged Items that Did Change (or that were matured) Include
resized propellant tanks, engine mounts modified tank support scheme added realistic clearances for plumbing, radiators, insulation, struts Refined AM/DM separation and AM/AL separation/tunnel Details Some hatch details Descent stage is now "Clocked " 45 o with respect to AM Deck Height = 5.9m (upgrade to 10m shroud) , 6.2m (shroud +
LDAC1-Delta & LDAC2 Configurations
AM Tanks with RCS Placeholder Structure Airlock Modified Hatch
V)
Mass impact
10m Shroud Migration Adds +46 kg (DS Truss -44.3 kg, EDSA +90.6 kg) Increased V Adds +217 kg (+164.4 kg DS Truss, EDSA +52.67 kg) +47 kg Due to Combination of both 10m Shroud & Increased TOTAL MASS INCREASE: 310 kg
7-Apr -2008 NASA Internal Only
9.5m 9.5m Modified Cone Supports
V
Your Initials Here /
2
LDAC1-
NASA Internal Only
LDAC2
Your Initials Here / 3 Page 30
June 18 - 20, 2008
7-Apr -2008 Section 05: Altair System
Payload Shroud Current Design Concept
Point of Departure (Biconic) Leading Candidate (Ogive) Mass: 9.1 t (20.0k lbm) POD Geometry: Biconic Design: Quad sector Barrel Diameter: 10 m (33 ft) Barrel Length: 9.7 m (32 ft) Total Length: 22 m (72ft) Quad Sector Design
Frangible Joint Horizontal Separation
Composite sandwich construction (CarbonEpoxy face sheets, Al honeycomb core) Painted cork TPS bonded to outer face sheet with RTV Payload access ports for maintenance, payload consumables and environmental control (while on ground)
June 18 - 20, 2008
Thrust Rail Vertical Separation System Payload umbilical separation
Section 06: Ares V System Page 31
Ares V Shroud Encapsulation Issues
Shroud quad sector configuration will likely preclude partial encapsulation in SSPF Shroud Encapsulation risks are the same for all 51 Series Ares V variants GO and Ares V teams will continue to study shroud ground processing alternatives.
June 18 - 20, 2008
Section 07: Ground Operations
Page 32
Temporal Availability Contour Plots
Temporal availability contour plots show the availability of lunar landing sites over the lunar nodal cycle. The following plots reflect both global sortie mission availability for the Altair alone as well as for the integrated Orion/Altair mission. The following proposed ESAS landing sites are indicated in the contours:
Landing Site Latitude Longitude Notes ------------------------------------------------------------------------------------------------------------------------------------------A. South Pole 89.9 S 180 W (LAC 144) rim of Shackleton B. Far side SPA floor 54 S 162 W (LAC 133) near Bose C. Orientale basin floor 19 S 88 W (LAC 91) near Kopff D. Oceanus Procellarum 3S 43 W (LAC 75) inside Flamsteed P E. Mare Smythii 2.5 N 86.5 E (LAC 63) near Peek F. W/NW Tranquilitatis 8N 21 E (LAC 60) north of Arago G. Rima Bode 13 N 3.9 W (LAC 59) near Bode vent system H. Aristarchus plateau 26 N 49 W (LAC 39) north of Cobra Head I. Central far side highlands 26 N 178 E (LAC 50) near Dante J. North Pole 89.5 N 91 E (LAC 1) rim of Peary B
June 18 - 20, 2008
Section 09: Integrated Performance and Mission Design
Page 33
Global Access/LOI -V/LLO loiter
Access to all lunar landing sites ("global access") requires a combination of additional LOI -V, pre-descent LLO loiter, and post-ascent LLO loiter
Minimum energy LLO maneuvers are sufficient for polar outpost missions
Altair to size tanks for 1000 m/sec LOI maneuver, load consumables for 4 additional days of LLO loiter
June 18 - 20, 2008
Section 05: Altair System
Page 34
Global Sortie Mission Sequence
IC: PostAscent LEO Epoch Specified DE-ORBIT TLI LOI-1 PDI Landing Site LOI-3 Earth-Moon Specified Transfer 3-Burn LOI 1-day Loiter ASCENT TO DOCK Pre-TEI Extended Loiter 1-day Loiter 3-Burn TEI EI
Moon-Earth Transfer
3-7 Day Surface Stay
TCM's
RENDEZVOUS IN LEO GIVEN:
Epoch Landing Site LAT/LONG TLI Window Duration Trans-Lunar Time of Flight Post-LOI Extended Loiter Pre-TEI Extended Loiter Trans-Earth Time of Flight Entry Interface Conditions
Post- LOI Extended Loiter
TCM's
ASCENT PLANE CHANGE
TEI-1 TEI-3
LLO ORBIT MAINTENANCE
DETERMINE:
Required Propellant Mass for EDS, Altair, and Orion Vehicles.
June 18 - 20, 2008 Section 09: Integrated Performance and Mission Design
ACTIVE VEHICLES: 1. ORION ACTIVE 2. ALTAIR ACTIVE 3. EDS ACTIVE
Page 35
Greater Than Zero Temporal Coverage
1000 m/s LOI V Capability
In order to ensure global lunar surface access, the following minimum mission architecture conditions were determined to be sufficient for providing access to all lunar landing sites at some epoch during the lunar nodal cycle*: 48 HR LOI and TEI flight times 5 days of extended LOI loiter 3 days of extended TEI loiter For these conditions the Altair can provide access to the worst case landing sites ~8% of the time. For the integrated capability, this provides for access to the worst case integrated landing sites ~5% of the time.
Altair Only
Integrated Altair and Orion
* To the resolution of the MAPP data and given the assumptions in the MAPP analysis (e.g., no Earth perturbations assumed in LOI and TEI 3-burn maneuvers).
June 18 - 20, 2008 Section 09: Integrated Performance and Mission Design Page 36
LDAC-2 Configuration
June 18 - 20, 2008
Section 05: Altair System
Page 37
Vehicle Architecture
Three Primary Elements
Airlock Descent Module
- Provides propulsion for TCMs, LOI, and powered descent - Provides power during lunar transit, descent, and surface operations - Serves as platform for lunar landing and liftoff of ascent module
Ascent Module
Ascent Module
- Provides propulsion for ascent from lunar surface after surface mission - Provides habitable volume for four during descent, surface, and ascent operations - Contains cockpit and majority of avionics
Airlock Descent Module
- Accommodates two crew per ingress / egress cycle - Connected to ascent module via short tunnel - Remains with descent module on lunar surface after ascent module liftoff
Section 05: Altair System Page 38
June 18 - 20, 2008
Altair LDAC-2 Sortie Vehicle Configuration
LIDS AM RCS Thruster Pod (x4) Star Tracker and Comm. Antenna (x2)
Docking Window (x2) Forward Facing Window (x2) Avionics Platforms (x2)
AM Fuel Tank (x2) AM Oxidizer Tank (x2) Pressurant Tank (x2) AM Main Engine Thermal Insulation DM LH2 Fuel Tank (x4) Pressurant Tank (x2)
AM-Airlock Connecting Structure
AM Connecting Structure (Remains on DM)
Airlock
Airlock Egress Hatch
Avionics boxes (x2) Life Support Oxygen Tank Landing Leg (x4)
DM RCS Thruster Pod (x4) Radiator (x2)
LOX Tank Support Cone (x4) DM Main Engine
RCS Tanks
Problem: central location of capsule = bad visibility.
Section 05: Altair System Page 39
June 18 - 20, 2008
Altair Key Messages
Current design demonstrates a lander design that closes within the Constellation transportation architecture Altair has investigated a wide breadth of lander concepts, using lessons learned to influence the current design concept Altair has undertaken a process that begins with minimum functionality and buys back safety, reliability and additional capabilities with known performance, cost and risk impacts The Altair team is using this design process to help develop good requirements Design process (particularly risk based design approach) is resulting in a smart government design team Altair has used its bottoms-up design work to inform sizing of landers for transportation architecture trades Altair has developed a detailed bottoms-up cost estimate
June 18 - 20, 2008
Section 05: Altair System
Page 40
Sample Return Mass Considerations
Nominal return mass: 100 kg. Note that Apollo 17 returned 110.5 kg of sample. "The PSS views the sample mass allocation in the current exploration architecture for geological sample return as too low to support the top science objectives. We are asking that CAPTEM undertake a study of this issue with specific recommendations for sample return specifications." Tempe Workshop, 2007. CAPTEM: Minimum of 230 kg total return mass, but noted that on the basis of simple extrapolation of the Apollo 17 mission, sample return mass could be as much as 800 kg. The recent Lunar Surface Scenarios workshop estimated that a 7-day sortie mission with 4 crew and 8 EVAs could collect 306 kg of samples.
June 18 - 20, 2008
100 kg IS NOT ENOUGH
Section 05: Altair System
Page 41
Sample Return Mass Considerations
LCCR Action Items: Stochastic modeling of sample return mass on the Altair ascent stage; Study of Orion volume capacity for increasing return sample mass. At the moment there is 1.6 metric tons of reserve mass on Altair, not including PMR.
June 18 - 20, 2008
Section 05: Altair System
Page 42
LCCR & The Surface Architecture
(not part of this LCCR)
Can the Constellation transportation system (Ares, Orion & Altair) support the deployment and operations of a lunar outpost?
Is the POD cargo capacity to the lunar surface Can enough?
Element
LCT (Lunar Communications Terminal) 2 - Crew Mobility Chassis 2 - Pressurized Crew Cab Mobile Power Unit OTSE - Davit OPS - ISRU system - H2 Reduction (0.5t) - TS3 Excavation - H2 Reduction (0.5t) - TS3 Mass (t) 0.32 2.13 6.13 0.85 0.16 0.24 0.05 Capabilitiy 14.60
Do the surface systems fit in the Ares-5 shroud and on the Altair deck?
Lander
Baseline Capability Mass (t) 14.60
Have solutions for unloading cargo to the surface been identified?
Logistics
Category Pressurized Science Logistics 0.69 3.97 Unpressurized Oxygen Nitrogen Water Logistics
Carried 0.420 1.911 0.000 0.000 0.000 2.331 Packaging 0.080 1.560 0.000 0.000 0.000 1.640 Total 0.500 3.471 0.000 0.000 0.000 3.971
Total Capability Difference
14.55 14.60 0.05
June 18 - 20, 2008
Yes
Yes
Yes
Page 43
Section 04: LSS Concepts
ISRU
Functional Description:
Perform lunar regolith excavation and handling, oxygen extraction from regolith, and oxygen storage and delivery, and support lander propellant scavenging and water production. For flexibility, two 1/2scale plants will be delivered and 2 sets of excavation tools. Total O2 Produced = 1000 kg/yr Mass per O2 plant = 219 kg Power per plant = 3.93 kW Total Regolith = 415 kg/day Excavation Tools = 42.7 kg (each) Excavation Time = <1 hr/day
June 18 - 20, 2008
Oxygen Extraction from Regolith
Large hoppers hold 1 day's regolith Hoppers raised to allow dumping of spent regolith into CMC Radiator panels fold down for launch
RESOLVE Subscale O2 Extraction and Volatile release reactor
Regolith H2 Processing
TS 2/3 O2 Production System with Storage and Thermal Control
H2 O Processing O2 Storage
1st Gen O2 Production System (660 kg/yr ) for Field Demo, Nov. 08
Regolith Excavation and Movement
Scoop lifts 11 kg regolith/scoop (38 scoops to fill hoppers for day) Cratos Excavator
Area Clear Blade on CMC
Excavation and O2 Plant mounted on mobile chassis
Bucketwheel Excavator
1 t of oxygen per year requires a regolith excavation rate of <1/2 cup per minute! (1% efficiency - 70% light)
Section 04: LSS Concepts
Page 44
Surface Architectures Assessed
Three surface architectures were developed in support of LCCR:
Rapid Outpost Buildup (TS-1)
- Deliver as much outpost capability as soon as transportation system permits - Full-up outpost based on the recommendations from LAT-2. - Substantial robustness through element duplication
Initial Mobility Emphasis (TS-2)
- Temper outpost build-up based on affordability with initial emphasis on mobility capabilities - Full-up outpost has less volume and limited eclipse operating capability than TS1 - Robustness achieved through functional reallocation - Assumed water scavenging
Initial Habitation Emphasis (TS-3)
- Temper outpost build-up based on affordability with initial emphasis on core habitation & exploration capabilities - Full-up outpost has less volume and limited eclipse operating capability than TS1 - Robustness achieved through functional reallocation - Assumed water scavenging
Surface Systems Review in 2010
June 18 - 20, 2008 Section 04: LSS Concepts Page 45
Lunar Transportation Architecture Recommendations
Ares-V
- - -
Maximize commonality between Lunar and Initial Capabilities: Ares-V 51.0.48
6 engine core, 5.5 segment PBAN steel case booster Provides architecture closure with additional margin High commonality with Ares I
Continue to study the benefits/risk of improved performance: Ares-V 51.0.47
- - - - Final decision on Ares V booster at Program SRR (6/2010) Additional performance capability if needed for margin or requirements Allows for competitive acquisition environment for booster Requires further study and technology investment funding
Altair
Provide a robust capability to support Lunar Outpost Missions:
- - Optimize for crew missions (500 kg + airlock with crew) Lander cargo delivery: ~ 14,500 kg in cargo only mode
Size the system for global access while allowing future mission and system flexibility
- - - - Size Altair tanks for 1,000 m/s LOI delta-v Size for an additional 4 days of Low-Lunar Orbit loiter (site specific) ~1,000 kg Program reserve at TLI Minimum of 40% total Altair margin/reserve
Retain adequate margins:
Orion
Continue to mature Orion vehicle concept Maintain strong emphasis on mass control
- Continue to hold Orion control mass to 20,185 kg at TLI
Increase emphasis on evolution of Orion Block 2 to support lunar Outpost missions
June 18 - 20, 2008 Section 13: Architecture Summary and Next Steps Page 46
DRMs/Mission Key Driving Requirements Mapping
Lunar Sortie Design Reference Mission
Altair Crew of 2-4 + 500 kg (1,102 lbm) cargo Global Access Landing accuracy 100 m (328 ft) with 95% accuracy ( ) 373 ( ) hrs crew support Airlock functionality LOC 1 in 250 ( ) LOM 1 in 75 ( ) Descent V 2,030 m/s (6,660 ft/s) LH2/LO2 descent engine restartable/throttleable
MOON
7d Ascent 1,881 m/s (6,171 ft/s) 100 kg (220 lbm) pressurized return payload TBD hrs post lunar ascent
A TBD or TBR is associated with this requirement
Multi-Mission Phase Requirements Anytime Abort LOC 1 in 100 LOM 1 in 20 LLO 100 km (54nm) Altair Performs LOI 1,000 m/s (3,281 ft/s) (Propellant load for 950 m/s)
Altair V for LOI 1,000 m/s (3,281 ft/s)
3-burn LOI 1-4 days Altair LLO loiter
TEI 1,492 m/s (4,895 ft/s) (Tanks sized for 1, 560 m/s (5,118 m/s)
Altair TLI Injected Control Mass 45 t (99,200 lbm) EVA Mass Allocation 171.5 kg (378.0 lbm) FCE Mass Allocation 133.8 kg (295.0 lbm) EDS TLI Injection Capability 66.1 t (145,726 lbm) + 5 t reserve EDS Performs TLI 3,175 m/s (10,417 ft/s)
Orion Orion TLI Control Mass 20,185 kg (44,500 lbm) FCE & EVA Mass Allocation 675 kg (1,488 lbs) Orion 382 kg (842) unpressurized cargo 21.1 days crew support LOC 1 in 200 LOM 1 in 50 ERO 241km (130nm) -20x185 km (-11x100 nm), 29
Ares-I Delivered Mass 23.6 t (52,070 lbm) 4 days LEO loiter
Direct or Skip Entry
905 t (2M lbm)
3,698 t (8.2 Mlbm)
EARTH
June 18 - 20, 2008
90 min. 1-5d
Ares V 4 launches per year (6 launches per year) Weather exclusive launch availability TBD 2 5.5 sebment SRBs; 6 RS-68B LOC 1 in 37,000 LOM (vehicle) 1 in 125 ~4d 1-5d 7d 1d <5.8d
Water Landing
Section 13: Architecture Summary and Next Steps
Page 47