Introduction to theAltair Project

Lauri N. Hansen, Project Manager

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NASA’s Exploration Roadmap

05 06 07 08 09 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25

Orion Development

Ares I Development

Commercial Crew/Cargo for ISS

Initial Orion Capability

Orion Production and Operations

Science Robotic Missions

Mars Expedition Design

Space Shuttle Ops

Altair Development

Ares V Development

Earth Departure Stage Development

Surface Systems Development

Early Design Activity

Lunar Outpost Buildup Lunar Robotic Missions

ISS Sustaining Operations

SSP Transition…

Human LunarReturn

Mars Expedition Design

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Heavy LiftLaunch Vehicle

Crew Launch Vehicle

Earth DepartureStage

Crew Exploration Vehicle

LunarLander

Components of Program Constellation

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Typical Lunar Reference Mission

Ascent Stage Expended

ED

S,

La

nd

er

CE

V

Earth Departure Stage Expended

Lander Performs LOI100 km Low Lunar Orbit

Vehicles are not to scale.

Low Earth Orbit

Service Module Expended

MOONMOON

EARTHEARTH

Direct EntryLand Landing

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Lunar Lander and Ascent Stage

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 15 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

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Configuration Variants

Outpost Variant45,000 kg

Descent ModuleAscent Module

Sortie Variant45,000 kg

Descent ModuleAscent Module

Airlock

Cargo Variant53,600 kg

Descent ModuleCargo on Upper Deck

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Initial Project Structure

Using a Smart Buyer approach Develop a preliminary government design

Coming out of initial design effort, have independent reviews and solicit industry input on initial design

Continue to refine design & requirements based on industry input Using knowledge gained from in-house design effort, create draft

vehicle design requirements In FY10 have a vehicle requirements review, and baseline

requirements Between 2009 – 2011, build hardware/test beds to mature

confidence in path for forward design (lower risk of unknown surprises)

Continue to mature design in-house until PDR timeframe (tentative)

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Detailed Approachfor Design Team

Initial task was developing a preliminary in-house design: 6-9 mth duration Agency wide team

Expert designers from across the agency Minimalist approach – add people on a case-by-case basis, only as needed

Subsystems, not elements Approximately 20 – 25 people on the core team

Co-located initially (approx 2 months) Working from home centers following initial co-location period

Another 20-25 FTE distributed across the Agency (not co-located) Focused on Design (‘D’ in DAC)

Developed detailed Master Equipment List (over 2000 components) Developed detailed Powered Equipment List Produced sub-system schematics NASTRAN analysis using Finite Element Models Performed high-level consumables and resource utilization analysis Sub-system performance analysis by sub-system leads

Keep process overhead to the minimum required Recognizing that a small, dynamic team doesn’t need all of the process overhead that a

much larger one does But…. It still needs the basics

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“Minimum Functionality” Approach

“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)

Altair has taken a Minimum Functionality design 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!

The “Minimum Functional” design approach is informed by: NESC PR-06-108, “Design Development Test and Evaluation (DDT&E)

Considerations for Safe and Reliable Human Rated Spacecraft Systems CEV “Smart Buyer” lessons learned Recent CEV “Buyback” exercises

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Alta

ir P

roje

ct

*ENVISION parametrically sized “polar” lander concept informed by the LDAC-1 Starworks activity with selected additional redundancy and delta-v's that are representative of realistic trajectories, but not optimized for Thrust to Weight.

p711-B Lunar Lander*

Vehicle Concept CharacteristicsAscent ModuleDiameter: 2.35 metersMass (at TLI): 6,128 kgMain Engine Propellants: N2O4/MMHUseable Propellant: 3007 kg# Main Engines/Type: 1/Derived OME/RS18 (Pressure Fed)Main Engine Isp (100%): 320 secMain Engine Thrust (100%): 5,500 lbfRCS Propellants: N2O4/MMHUseable Propellant: Integrated w/main# RCS Engines/Type: 16/100 lbf eachRCS Engine Isp (100%): 300 sec

AirlockPressurized Volume: 7.5 m^3Diameter: 1.75 m Height: 3.58 mCrew Size: 2+

Descent Module (crewed) Mass (at TLI): 38,002 kgMain Engine Propellants: LOX/ LH2Useable Propellant: 25,035 kg# Main Engines/Type: 1/ RL-10 Derived (Pump Fed)Main Engine Isp (100%): 448 secMain Engine Thrust (100%): 18,650 lbfRCS Propellants: N2O4/MMH# RCS Engines/Type: 16/100 lbf each RCS Engine Isp (100%): 300 sec

Descent Module (cargo)Mass (at TLI): 38,970 kgUseable Propellant: 26,611 kg

Lander Performance Crew Size: 4LEO Loiter Duration: 14 daysSurface stay time: 7 days (sortie) 180 days (outpost visit)Launch Shroud Diameter: 8.4mLander Design Diameter: 7.5 mLaunch Loads: 5 g axial, 2 g lateral

Crewed Lander Mass (Launch): 45,586 kgCrewed Lander Mass (@TLI): 45,586 kgCrew Lander Payload to Surface: 500 kgProject Manager’s Reserve: 3009 kg Crew Lander Deck Height: 6.97 m

Cargo Lander Mass (Launch): 53,600 kgCargo Lander Mass (@TLI): Not applicable.Cargo Lander Payload to Surface: 14,631 kg Project Manager’s Reserve: 2227 kgCargo Lander Height: 6.97 m

EDS Adapter Mass: 860 kg (Not included in numbers above, includes growth and Manager’s Reserve)

Crew Lander LOI Delta V Capability: 891 m/sCargo Lander LOI Delta V Capability: 889 m/sCrew/Cargo Plane change and Loiter (Post CEV sep, 1 degree): 28.4 m/sPDI Delta V Capability: 19.4 m/sCrew Descent Propulsion Delta V Capability: 2030 m/sCargo Descent Propulsion Delta V Capability: 2030 m/s

TCM Delta V Capability (performed by RCS): 2 m/sDescent Orbit Insertion Capability (performed by RCS): 19.4 m/sSettling Burn Requirement (performed by RCS): 2.7 m/sDescent and Landing Reaction Control Capability: 11 m/s

Ascent Delta V Capability 1881 m/sAscent RCS Delta V Capability: 30 m/s

Airlock

Ascent Module

Descent Module