Copyright © 2010 United Launch Alliance, LLC. Unpublished Work. All Rights Reserved.
FLV 1A
Propellant Depots
Made Simple
Bernard Kutter
Manager Advanced Programs
10 November 2010
Propellant Depots
Made Simple
Bernard Kutter
Manager Advanced Programs
10 November 2010
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1
Discussion Overview
Brief ULA Background
“Simple Depot” Concept
Depot Operations
Brief Mission Use Examples
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2
United Launch Alliance (ULA)
Two world-class launch systems
–Lockheed Martin’s Atlas program (Atlas V)
–The Boeing Company’s Delta program (Delta II, Delta IV)
–50/50 joint Boeing/Lockheed Martin ownership
Strengthened mission success
ULA’s charter
–Provide launch services on an equal access to all
• No discrimination
–Support commercial launch services through Lockheed Martin
and Boeing Commercial launch services
ULA Can Not Develop/Operate Satellites
ULA Can Not Develop/Operate Satellites
Including Propellant Depots
Including Propellant Depots
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3
A Full Range of Capabilities to All Orbits
A Full Range of Capabilities to All Orbits
Launch Vehicle Products
Medium Class
Intermediate Class
Delta II
Delta IV
Delta IV Heavy
Atlas V
Heavy Class
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4
ULA Cryogenic Upper Stages
ULA has 3 operational LO
2
/LH
2
upper stages
–Represents most of America’s orbital cryogenic experience
Centaur
3m
21 mT
0.90
194
Delta IV stage 2
4m
21 mT
0.87
12
Delta IV stage 2
5m
27 mT
0.87
4
Diameter
Propellant
Mass Fraction
# Flights
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5
100% Mission Success
ULA Launch History
National Security
NASA/Civil
Commercial
NROL-21 - 12/14/06 - Delta II
THEMIS - 2/17/07 - Delta II
STP-1 - 3/8/07 - Atlas V
COSMO-1 - 6/7/07 - Delta II
NROL-30 - 6/15/07 - Atlas V
Phoenix - 8/4/07 - Delta II
Worldview-1 - 9/18/07 - Delta II
Dawn - 9/27/07 - Delta II
WGS-1 - 10/10/07 - Atlas V
GPS IIR-17 - 10/17/07 - Delta II
DSP-23 - 11/10/07 - Delta IV
COSMO-2 - 12/8/07 - Delta II
NROL-24 - 12/10/07 - Atlas V
GPS IIR-18 - 12/20/07 - Delta II
NROL-28 - 3/13/08 - Atlas V
GPS IIR-19 - 3/15/08 - Delta II
ICO G1 - 4/14/08 - Atlas V
GLAST - 6/11/08 - Delta II
OSTM - 6/20/08 - Delta II
GeoEye - 9/6/08 - Delta II
COSMO-3 - 10/24/08 - Delta II
NROL-26 - 1/17/09 - Delta IV
Most Recent Launches
NOAA-N' - 2/6/09 - Delta II
Kepler - 3/6/09 - Delta II
GPS IIR-20 - 3/24/09 - Delta II
WGS-2 - 4/3/09 - Atlas V
STSS ATRR - 5/5/09 - Delta II
LRO/LCROSS - 6/18/09 – Atlas V
GOES-O - 6/27/09 – Delta IV
GPS IIR-21 - 8/17/09 - Delta II
PAN - 9/8/09
-
Atlas V
STSS Demo - 9/25/09 - Delta II
WorldView-2 - 10/8/09
-
Delta II
DMSP F18 - 10/18/09 – Atlas V
Intelsat-14 - 11/23/09 – Atlas V
WGS-3 - 12/5/09 – Delta IV
WISE - 12/14/09 – Delta II
SDO - 2/11/10 – Atlas V
GOES-P - 3/4/10 – Delta IV
OTV-1 - 4/22/10 – Atlas V
GPS IIF SV-1 - 5/27/10 – Delta IV
AEHF-1 – 8/14/10 – Atlas V
NROL-41 – 9/20/10 – Atlas V
COSMO-4 – 11/5/10 – Delta II
Delta II
COSMO-4
11/5/10
Atlas V
NROL-41
9/20/10
Delta IV
GPS IIF SV-1
5/27/10
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6
Why Propellant Depots
Propellant depots ease aggregation of elements
–Beneficial with all launch vehicle performance levels
Propellant
Depot
Cryo Prop Stage Launch
HEFT 1 DRM 4 all cryo option
Propellant Depots Simplify Beyond LEO Exploration
Propellant Depots Simplify Beyond LEO Exploration
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7
Historic Depot Paradigm
Propellant Depot as a Space Station
– Numerous launches
– On orbital assembly
– Zero-boil-off
– Zero-G cryogenic fluid management (CFM)
Assumed Depot Complexity has Effectively
Assumed Depot Complexity has Effectively
Prevented Depot Deployment for 5 Decades
Prevented Depot Deployment for 5 Decades
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8
Simple Depot Concept
Existing Lines
New Lines
LH2 Module
L=16.3m
Mission
Module
Centaur
LO2 Module
L= 9.6m
H
e
&
G
O
2
L
H
2
S
to
ra
g
e
(1
1
0
m
3
;
7
.6
m
T
)
L
O
2
S
to
ra
g
e
(4
8
m
3
;
5
3
m
T
)
Simple depot side steps historic barriers
– Single unit, single launch, no orbital assembly
– Settled CFM (Transverse spin)
– Simplified thermal management
– H2 boil-off for station keeping
Key cryo storage principles
– Minimize penetrations
– Minimize surface area
– Segregate cold-hot elements
NASA Should Lead Propellant Depot Development
NASA Should Lead Propellant Depot Development
Atlas 551 Launch
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9
Historic Cryogenic Storage
2.0%
Hours
20 & 100
20,900
ULA
Liquid hydrogen &
oxygen
Centaur
19.6% SOFI
5.1
20
426
BATC
Liquid hydrogen
HALE
0.0085 %
38.4
90-211
354
BATC
ScO2
PRSA Enhanced
0.22 % s
14.8
90-211
354
BATC
ScO2
PRSA2
~7%
w/ heaters
0.5
0.5
20-83
90-211
42
354
BATC
ScH2
ScO2
Power Reactant Storage
Assy (PRSA)1
0.022%
150
90
7186
Beech
BATC
Liquid Oxygen
OTTA
0.022%
150
20
446
Beech
BATC
Liquid hydrogen
HTTA
0.05%
66
1.3
45
BATC
SfHe
Spitzer
0.07%
49
1.5
83
BATC
SfHe
COBE
0.32%
10
1.7
70
BATC
SfHe
IRAS
0.07%
0.08%
44.9
40.4
65
145
91
42
LMC
Solid methane
Solid ammonia
Long-life cooler
(LLC) (2-stage)
0.04%
0.07%
66
64.9
65
145
150
73
LMC
Solid methane
Solid ammonia
Extended life cooler
(ELC)
0.16%
0.13%
19.8
25
14
125
449
340
LMC
Solid Neon
Solid CO2
CLAES (2-stage) (Post
Challenger)
0.15%
21.4
10.4
85
LMC
Solid hydrogen
CLAES
0.264%
10
9.5
85
LMC
Solid hydrogen
SPIRIT III
0.49%
5.4
12
4
LMC
Solid hydrogen
WIRE
0.09%
30
1.8
29
LMC
SFHe
SHED
0.17%
1.34%
16
2
1.8
1.8
334
29
LMC
Superfluid
helium (SFHe)
Gravity probe-B
•
SMD/EDD
Flow-rates
per day (%)
Life-
time (mo)
Operating
temp (K)
Tank
capacity (kg)
Company
Cryogen
Program
Efficient Cryogenic Storage Already Demonstrated
Efficient Cryogenic Storage Already Demonstrated
Need to Develop Large Scale, Mass Efficient Storage
Need to Develop Large Scale, Mass Efficient Storage
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10
LH2 Module
L
H
2
S
to
ra
g
e
(1
1
0
m
3
;
7
.6
mT
)
C
e
n
tr
if
u
g
a
l
F
o
rc
e
Counter weight
Integrated MLI blanket
-Minimal penetrations
-GH2 vapor cooled shield
-Broad area cooling
-MMOD
Sun Shield
LH2 tank (launched empty)
0.013” CRES monocoque
No foam
GH2 vapor cool tank
Composite strut adapter
LH2 transfer line/valves
GH2 pressurization/vent line
Wiring
GH2 vapor cool penetrations
LH2
Module
H2
Ullage
Built using existing
Centaur tooling
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11
LO2 Module
C
e
n
tr
if
u
g
a
l
F
o
rc
e
H
e
&
G
O
2
L
O
2
S
to
ra
g
e
(4
7
mt
3
;
5
4
mT
)
Composite Adapter
Wiring
GO2 pres/vent line
LO2 transfer line
GH2 vapor cool wall
Integrated MLI blanket
-Minimum penetrations
-GH2 vapor cooled shield
-Broad area cooling
-MMOD
GH2 vapor cooling cooling
to condition LO2
GH2 vapor cooled tank
Purge shut-off valves
GH2 cool engine beam
Cylindrical sun shield
Warm GH2 RCS
LO2
Module
(Centaur)
Cg
Existing Lines
New Lines
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Depot Demonstration
ESPA structure
Avionics
Propellant control
Transfer pumps
Solar power
Grapple arm
Transfer Port
Cryocooler
Radiator
Mission
Module
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Technology Readiness
3
3
Fluid Coupling
5
4
Tank fill operation
9 (5*)
9 (5*)
Propellant Subcooling P>1atm (P<1atm*)
9
4
Pressure Control
5
4
Transfer System Operation
7
5
9
9
9
9
3
4
9 (4)
3
9
5
9
Settled
7
4
3
4
4
3
3
4
9 (4)
3
9
5
Na
0-G
Current TRL
MLI Integrated Micro Meteorite Protection
AR&D
System Chilldown
Propellant Expulsion Efficiency
Mass Gauging
Propellant acquisition
Ullage & Liquid Stratification
Active cooling (LH2)*
Broad Area Cooling
Vapor Cooling (para ortho conversion)
Multi-layer insulation (MLI)
Thermodynamic Vent System
Low Acceleration Settling
Cryo Transfer Technology
* Upgrade option for enhanced long duration operation
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Demonstration to Orion Mission
Atlas 551 launch of depot
– Transfer 12 mT Centaur residuals for long term storage
Demonstrate DCSS operations
– Docking, propellant transfer, Earth departure
Refuel depot
Orion Lagrange/Lunar fly by mission
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15
Large Scale Plum Brook Cryo Test
Allows near term full scale technology
demonstration
Thermal vacuum test of flight cryo tank
(Centaur) at Plum Brook
– ULA loans Centaur tank (2011)
– NASA outfits tank to NASA requirements
– NASA performs testing (2012)
Test Objectives
– Enhance CFM confidence enabling
use for exploration missions
– Demonstrate low boil-off storage
• ~2%/day current flight demonstrated
• ~0.25%/day with existing Centaur
• Guide future vehicle design
to support <0.1%/day boil-off
Integrated MLI
Vapor cool
Clean bulkhead
- Min penetrations
Vapor cool
Enhanced
Thermal
Protection
Vapor cool
engine mount
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16
CRYOTE
Small Scale
Demonstrations
2012-2014
Leading to
Large Scale
Cryo-Sat Flagship
Tech Demo
2015
2010 Ground test
2012 Orbital flight
(Geoeye) in work
CRYOTE (CRYogenic Orbital TEstbed)
– In-space laboratory for cryo fluid
management (CFM) technologies
– Uses residual Centaur LH2 after
primary payload separation
Quickly Demonstrates Critical CFM Capabilities
Quickly Demonstrates Critical CFM Capabilities
Centaur
LH2
acquisition
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17
Technology Readiness
3
3
3
3
Fluid Coupling
6
4
5
4
Tank fill operation
9 (5*)
9 (5*)
9 (5*)
9 (5*)
Propellant Subcooling P>1atm (P<1atm*)
9
6
9
4
Pressure Control
6
4
5
4
Transfer System Operation
7
5
9
9
9
9
3
4
9 (4)
3
9
5
9
Settled
7
4
3
4
4
3
3
4
9 (4)
3
9
5
Na
0-G
Current TRL
5
5
MLI Integrated Micro Meteorite Protection
7
7
AR&D
6
4
System Chilldown
9
6
Propellant Expulsion Efficiency
9
4
Mass Gauging
9
6
Propellant acquisition
9
6
Ullage & Liquid Stratification
3
3
Active cooling (LH2)*
4
4
Broad Area Cooling
9 (6)
9 (6)
Vapor Cooling (para ortho conversion)
9
9
Multi-layer insulation (MLI)
6
6
Thermodynamic Vent System
9
na
Low Acceleration Settling
Settled
0-G
Post-CRYOTE Lite TRL
Cryo Transfer Technology
* Upgrade option for enhanced long duration operation
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Depot Capacity Options
LH2
LO2
Mission
Module
30 mT
Capacity
70 mT
120 mT
200 mT
Launch Using Existing or Future Rockets
Launch Using Existing or Future Rockets
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Lagrange Mission or Lunar Fly By
Example
Propellant Launch
Propellant Depot
Delta IV
Atlas V 552
Falcon 9
Atlas V 552
38 mT propellant launched
Earth Departure
(C3=0)
Orion
DIV HLV RS68A
Orion
Requires:
– Propellant depot
– Earth departure stage
– Propellant delivery
Transfer Prop EDS
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Lunar Surface Mission Example
Altair
TLI
Orion
Altair
Orion
Propellant Launch
Propellant Depot
Alternative Options
HLV
>70 mT Propellant
Delta IV
Atlas V
Falcon 9
Taurus II
Transfer Prop EDS
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NEO Mission Example
HLV
SM, Hab
Upper Stage (EDS)
Earth Depart
(C3 ~8)
Orion
SM
Hab
SM
Hab
Propellant Launch
Propellant Depot
Alternative Options
Transfer Prop EDS
HLV
>70 mT per launch
Orion
Delta IV
Atlas V
Falcon 9
Taurus II
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Mars Mission Example
SM
Hab
Propellant Launch
LEO Depot
Transfer Prop EDS
L2 Depot
Transfer Prop
EDS, SM, Lander
Earth Depart
(C3=20)
Orion
SM
Hab
Lander
Lander
HLV
SM, Hab, Lander
Upper Stage (EDS)
Orion
Alternative Options
Delta IV
Atlas V
Falcon 9
Taurus II
HLV
>70 mT per launch
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23
Early launch of
Orion from LC-39
can enable
crewed missions
beyond Earth
orbit as early as
2016