sa08 prop depot panel dallas bienhoff

LEO Propellant Depot

Technology and Impact

LEO Propellant Depot

Technology and Impact

Space Access ‘08Grace InnPhoenix, ArizonaMarch 27-29, 2008

Space Access ‘08Grace InnPhoenix, ArizonaMarch 27-29, 2008

Dallas BienhoffThe Boeing Company

703-414-6139571-232-4554Boeing Proprietary Data

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LEO Propellant DepotTechnology and ImpactLEO Propellant DepotTechnology and Impact

Long Term Cryo Storage

Zero-G Cryo Transfer

Depot Impact to ESAS Architecture

Depot System Overview

Depot Impact to other Missions

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Advanced Cryogenic Upper Stage AIAA 2006-7454Advanced Cryogenic Upper Stage AIAA 2006-7454

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Passive and Active Thermal ControlAIAA 2006-7454Passive and Active Thermal ControlAIAA 2006-7454

Passive Active

Passive Active

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Cryogenic Transfer ExperimentsCryogenic 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

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Orbital Express Can Provide Basis for Cryo Transfer InterfaceOrbital Express Can Provide Basis for Cryo Transfer Interface

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ESAS Final Report ArchitectureESAS 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

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ESAS Recommended Architecture Baseline Mission Mass Profile CalculatedESAS Recommended Architecture Baseline Mission Mass Profile Calculated

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Mission Event ID

Mis

sio

n S

tack

Mas

s (m

t)

EDS Ignition

Shroud Sep

MECO

LEOCirc

Orion & LSAMMate

InitiateLOI

End LOI

Orion Sep;D&L Start

LandingEDS Sep

Initiate TLI

End TLI

• 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

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The Exploration Architecture with a LEO Propellant DepotThe 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

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51 t to Lunar Surface or Two Sorties if Depot Incorporated into ESAS Arch51 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

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Mission Event ID

Mis

sio

n S

tack

Mas

s (m

t)

ESAS 1.5 ESAS 1.5 + Depot ESAS 1.0 + Depot ESAS 1.5 + Depot; No Extra Pyld Cargo Only

EDS Ignition

Shroud Sep

MECO

LEOCirc

EDS/LSAM & Depot Mate

EDS/LSAM Depot Sep

Orion & LSAMMate

Initiate TLI

End TLI

EDS Sep

InitiateLOI

End LOI

Orion Sep;D&L Start

Landing

Orion SepShroud Sep

EDS Sep

Initiate TLI

End TLI

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A LEO Propellant Depot System Concept with Reusable Propellant CarrierA LEO Propellant Depot System Concept with Reusable Propellant Carrier

Low-cost launch providerSpace X Falcon 9 shown

2 Modular Propellant Depots150-175 t capacity

LOx/LH

Reusable Propellant Carrier9400 kg total mass

LOx/LH

Reusable Transfer StageGTO and/or GEO delivery

LOx/LH

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Refueling the EDS/Lander Vehicle from a DepotRefueling 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

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A LEO Propellant Depot Operational Concept:A Hub for Exploration and HEO MissionsA LEO Propellant Depot Operational Concept:A Hub for Exploration and HEO Missions

Low-cost launch provider

Space X Falcon 9shownAres V

Earth Orbit Lunar

Orbit

InterplanetaryTrajectories

Reenter & Reuse

RGTV

RGTV

RPC

EDS/LSAM

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EML1 Depot Could be Added with Lunar Propellant Production and Reusable LanderEML1 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

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Architecture With LEO Depot Can Deliver 18-75 t to Lunar SurfaceArchitecture 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

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Case ID

Lan

ded

Mas

s (k

lbm

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Lan

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AS DS inert/pyld

5 distinct capabilities to lunar surface whenLEO Propellant Depot added to Exploration Architecture

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Ares V Core Stage Payload Can Be As Low As 85 t With LEO Depot in ArchitectureAres 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

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Case ID

Co

re S

tag

e P

yld

(kl

bm

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Co

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e P

yld

(t)

Shroud Margin Payload LSAM Stack EDS Inert EDS Propellant CEV

Ares V Core Stage Payload can be reduced by 72%when LEO Propellant Depot added to Exploration Architecture

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187% increase in lunar surface delivery capability using ESAS Architecture Systems with LEO Propellant Depot

LEO Propellant Depot Increases Landed Mass and/or Reduces Ares V Lift RequirementLEO Propellant Depot Increases Landed Mass and/or Reduces Ares V Lift Requirement

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Core Stage Payload (klbm)

Lan

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lbm

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1, 3, 9

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2416

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26 23

44% CSP Reduction72%

165 klbm

106 klbm

65 klbm

39 klbm

+65%

+170%

+323%

27, 28

112 klbm

+187%

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6

59

137

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Lunar Missions GTO GSO InterplanetaryC3 = 0

Mission Type

Cap

abili

ty (

t)Capabilities for Missions Without DepotCapabilities for Missions Without Depot

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Cre

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Lunar Missions GTO GSO InterplanetaryC3 = 0

Mission Type

Cap

abili

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t)Capabilities for Missions With DepotCapabilities for Missions With Depot

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In Summary…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

sa08 prop depot panel dallas bienhoff

Technology

depot incorporated

cargo leo depot

ares v eds lsam

lunar vicinity depot

excess eds propellant

eds lander

t capability

eds unchanged lsam