Sa08 Prop Depot Panel Dallas Bienhoff

LEO Propellant Depot Technology and Impact Space Access ‘08 Grace Inn Phoenix, Arizona March 27-29, 2008 Dallas Bienhoff The Boeing Company 703-414-6139 571-232-4554 Boeing Proprietary Data

LEO Propellant Depot Technology and Impact
Long Term Cryo Storage
Zero-G Cryo Transfer
Depot Impact to ESAS Architecture
Depot System Overview
Depot Impact to other Missions

Advanced Cryogenic Upper Stage AIAA 2006-7454

Passive and Active Thermal Control AIAA 2006-7454 Passive Active Passive Active

Cryogenic Transfer Experiments
SHOOT – Superfluid Helium On-Orbit Transfer
GSFC STS 57 experiment
Fixed couplings
Porous plug/heater
Hitchhiker payload
COLDSAT – Cryogenic Liquid Orbiting Depot Storage Acquisition and Transfer
Designed for Shuttle flight
NASA GRC
CONE – Cryogenic On-orbit Nitrogen Experiment
Designed for Shuttle Flight
NASA GRC

Orbital Express Can Provide Basis for Cryo Transfer Interface

ESAS Final Report Architecture
LSAM DS performs LOI with CEV and lunar descent and landing
Lunar orbit rendezvous: LSAM AS to CEV
LOx/LH in EDS and LSAM DS
Lox/Methane in LSAM AS and CEV
1.5 Launch architecture: Ares I & V
Earth orbit rendezvous: CEV to LSAM/EDS
EDS performs Earth orbit insertion & circularization and TLI burns

ESAS Recommended Architecture Baseline Mission Mass Profile Calculated
ESAS FR Figures 6-41 & 43 used as study reference
Orion mass held constant throughout profile
Calculated EDS propellant use matches reference
8.8 t EDS margin payload
ESAS LSAM propellant fractions and delta Vs used to calculate stage masses
DS: 9.6 inert; 27.2 prop
AS: 4.8 inert; 3.3 prop
17.7 t landed on Moon
ESAS Architecture assessment provides trade study datum

The Exploration Architecture with a LEO Propellant Depot
LSAM DS performs only lunar descent and landing
Lunar orbit rendezvous: LSAM AS to CEV
LOx/LH in EDS and LSAM DS
Lox/Methane in LSAM AS and CEV
7500 $/kg propellant price from depot
1.5 Launch or Single Launch architecture: Ares I & V or Ares V
EDS & LSAM receive propellant in LEO
Eliminates EDS & LSAM boil-off concerns
Earth orbit rendezvous: EDS/LSAM to Depot; CEV to LSAM/EDS
EDS performs Earth orbit insertion & circularization, TLI, and LOI burns

51 t to Lunar Surface or Two Sorties if Depot Incorporated into ESAS Arch
EDS and LSAM same as for ESAS Architecture
51 t vs 18 t for crew missions
51 t vs ~30 t for cargo
2 Sorties per mission with excess EDS propellant in LLO
Crew missions could be conducted with Ares V only
EDS could become basis for lunar vicinity depot
150 mt Lox/LH transferred from depot to EDS and LSAM DS

A LEO Propellant Depot System Concept with Reusable Propellant Carrier Low-cost launch provider Space X Falcon 9 shown 2 Modular Propellant Depots 150-175 t capacity LOx/LH Reusable Propellant Carrier 9400 kg total mass LOx/LH Reusable Transfer Stage GTO and/or GEO delivery LOx/LH

Refueling the EDS/Lander Vehicle from a Depot
LPD RMS berths EDS & LPD
Single mating interface
Transfer prior to Orion mate
Lox and LH to EDS & Lander
~25 t transferred to Lander
~125 t transferred to EDS
2 depots for redundancy
12-month depot refill cycle

A LEO Propellant Depot Operational Concept: A Hub for Exploration and HEO Missions Low-cost launch provider Space X Falcon 9 shown Ares V Earth Orbit Lunar Orbit Interplanetary Trajectories Reenter & Reuse RGTV RGTV RPC EDS/LSAM

EML1 Depot Could be Added with Lunar Propellant Production and Reusable Lander
Enables reusable all-propulsive EDS and reusable lander
EML1 depot supplied from any Earth space port or lunar outpost
Reusable lander can be based at depot or lunar surface
Earth launch reduced to Orion and mission payload

Architecture With LEO Depot Can Deliver 18-75 t to Lunar Surface
ESAS Recommended Architecture provides 18-20 t landed mass
Same capability with Depot and LSAM and EDS downsized; EDS does TLI
30 t capability if LOI allocated to EDS; same LSAM initial mass but different propellant load; and EDS downsized
48 t capability if LOI allocated to EDS; EDS characteristics unchanged; and LSAM upsized
50 t capability if LOI allocated to EDS and ESAS systems unchanged
75 t capability if EDS unchanged; LSAM upsized to full EDS to TLI capability
5 distinct capabilities to lunar surface when LEO Propellant Depot added to Exploration Architecture

Ares V Core Stage Payload Can Be As Low As 85 t With LEO Depot in Architecture
ESAS Architecture Ares V Core Stage Payload is 300 t
With a LEO propellant depot . . .
22 different heavy lift launch vehicle configurations possible
Orion can be launched on Ares V
Reduced Core Stage Payload options between 80 t and 265 t
Ares V Core Stage Payload can be reduced by 72% when LEO Propellant Depot added to Exploration Architecture

LEO Propellant Depot Increases Landed Mass and/or Reduces Ares V Lift Requirement 187% increase in lunar surface delivery capability using ESAS Architecture Systems with LEO Propellant Depot

Capabilities for Missions Without Depot

Capabilities for Missions With Depot

In Summary…
Boil-off can be significantly reduced or eliminated for cryo systems
ESAS lunar landed mass with Depot increases to 51 t for crew or cargo
LEO Depot enables dual sorties on a single lunar mission
Depot provides 2-3 times more capability to high energy missions

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Sa08 Prop Depot Panel Dallas Bienhoff

by jongoff on Mar 31, 2008

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Sa08 Prop Depot Panel Dallas Bienhoff — Presentation Transcript