sa08 prop depot panel frank zegler
DESCRIPTION
Frank Zegler's Space Access 08 Propellant Depot Panel presentation on ULA's latest work on propellant depots and related technologies.TRANSCRIPT
![Page 1: Sa08 Prop Depot Panel Frank Zegler](https://reader036.vdocuments.us/reader036/viewer/2022062419/5581774ad8b42ae15f8b5176/html5/thumbnails/1.jpg)
Cryogenic Propellant Depots for the
Real World
March 27 2008United Launch Alliance
Cryogenic Propellant Depots for the
Real World
March 27 2008United Launch Alliance
![Page 2: Sa08 Prop Depot Panel Frank Zegler](https://reader036.vdocuments.us/reader036/viewer/2022062419/5581774ad8b42ae15f8b5176/html5/thumbnails/2.jpg)
File no. | 2
Depots Amplify Performance
EDS Topping from orbital depot amplifies lunar payload– EDS is half full in LEO for ESAS
Accommodates mission delays or high propellant boil-off– Small variations in fabrication have large impacts to tank heating
– Untestable prior to launch
– Centaur experience shows 2:1 variation in heating, same mission
– Likelihood of launch delays is historically very high Opens the door for more capable exploration architectures
Indefinite surface stays, autonomous asset/consumables deliverySimplified vehicle design, increased systems commonality
0
5
10
15
20
25
0 20 40 60 80
Pay
loa
d In
crea
se,
mT
Propellant Transfer Mass(mT)
123126
EDS LSAM
CEV
Pictures Credit: NASA
![Page 3: Sa08 Prop Depot Panel Frank Zegler](https://reader036.vdocuments.us/reader036/viewer/2022062419/5581774ad8b42ae15f8b5176/html5/thumbnails/3.jpg)
File no. | 3
Historic Propellant Depot Paradigm
NASA 9902019
Propellant transfer has been associated with:– Large scale propellant depots
– Zero Boil off fluid transfer
– Zero Boil off Storage
Propellant depots imply:– Large infrastructure
– Zero-G cryo fluid management
•Currently at low TRL
– Huge initial hurdle to cryo fluid transfer implementation
Historic Architectures are an Insurmountable BarrierHistoric Architectures are an Insurmountable Barrier
![Page 4: Sa08 Prop Depot Panel Frank Zegler](https://reader036.vdocuments.us/reader036/viewer/2022062419/5581774ad8b42ae15f8b5176/html5/thumbnails/4.jpg)
File no. | 4
Simple Cryo Depot Concept
Exploration is mostly about moving LO2 around Simple depot sidesteps barriers
– Single propellant (LO2), single unit, single launch
– Based on existing tanks/upper stages
– Simplified thermal management• Geometry isolates cold and hot elements (long conductive paths); • Sun Shield, MLI, vapor cooling
Liquid
Gas
Gas
Solar Array
Sun Shield
Hot
Equ
ip
Dec
k
DockPort
Hot Side
Cold Side
Rotational Settling
SUN
– Settled (rotational) propellant management
– Settled Propellant transfer
– Gas reservoir provides thermal barrier, expulsion gas
![Page 5: Sa08 Prop Depot Panel Frank Zegler](https://reader036.vdocuments.us/reader036/viewer/2022062419/5581774ad8b42ae15f8b5176/html5/thumbnails/5.jpg)
File no. | 5
Two Obvious Options
Depot based on Modified Upper Stage– Least possible Non-recurring investment
– Compromised onboard systems
– Bound to a single launch supplier- minimal competition
• Inevitably leads to higher recurring costs
– Restricted propellant capacity
Depot as a Dedicated Payload– Higher Non-recurring Investment
– Optimized onboard systems
– Much larger propellant capacity, greater utility
• Supplied/replenished by multiple launchers– Enables direct competition for orbital propellant delivery
– Best chance for market-driven lower costs
![Page 6: Sa08 Prop Depot Panel Frank Zegler](https://reader036.vdocuments.us/reader036/viewer/2022062419/5581774ad8b42ae15f8b5176/html5/thumbnails/6.jpg)
File no. | 6
Upper Stage Based Depot
1 or 2 additional burns for phasing
Existing Vehicles deliver 12-16 tons: Lunar cargo increase 3-4t Baseline ACES delivers 17-25 tons Extended tank designs deliver 40-42 t
AC
ES
BA
SELIN
E
200 nm circ orbit
1 or 2 additional burns for phasing
1
200k
12
2
4
4
6
6200k
1
1
Number of RL10 engines
![Page 7: Sa08 Prop Depot Panel Frank Zegler](https://reader036.vdocuments.us/reader036/viewer/2022062419/5581774ad8b42ae15f8b5176/html5/thumbnails/7.jpg)
File no. | 7
Upper Stage Based Depot
Integrated 6 DOF LO2/LH2 Attitude Control
Solar Power System
Baseline ACES Upper Stage, 41t Propellant Load at Launch
Deployable Multiple-Petal Open-Cavity Sunshield (2 petals removed for clarity)
EDS docking interface
Long Duration Avionics with Rendezvous, Docking, Propellant Mgt functions
Vapor Cooled Depot Systems Interface
LO2 Tank
A dedicated ACES on Atlas HLV delivers 25t Propellant to LEO•Equivalent to Altair Cryogenic propellant load (24t)
LH2 Tank
![Page 8: Sa08 Prop Depot Panel Frank Zegler](https://reader036.vdocuments.us/reader036/viewer/2022062419/5581774ad8b42ae15f8b5176/html5/thumbnails/8.jpg)
File no. | 8
Dedicated Depot
Depot shown uses Identical sunshade to ACES upper stage version
•Launched partially filled to maximum launcher capability•Refilled via commercial LO2 delivery to LEO
•Falcon, Delta, Atlas, Ariane, SSTO/RLV•Capacity:
•230 t LO2 or 167% of EDS capacity•14.3t LH2 or 63% of EDS capacity
Extended Upper Tank (LO2 or LH2)
Truncated Lower Tank (GO2 or GH2)
![Page 9: Sa08 Prop Depot Panel Frank Zegler](https://reader036.vdocuments.us/reader036/viewer/2022062419/5581774ad8b42ae15f8b5176/html5/thumbnails/9.jpg)
File no. | 9
Depot Location
LEO location poses orbital inclination/launch opportunity limitations– Complex mission planning
Depots in Lunar orbit or at Earth-Moon L1/L2 have even greater utility– Easier thermal management (Solar heating dominated)
– Propellants confirmed safely delivered at destination
• Thermal performance is known via daily operation
• Delivery of unmanned Altair to LLO an obvious next step
– Drastically reduces performance demand for ARES, EDS, Altair
• ARES V can be far simpler- 65-80t @ LEO vehicle
• Altair optimized for lunar operations- no LOI function
![Page 10: Sa08 Prop Depot Panel Frank Zegler](https://reader036.vdocuments.us/reader036/viewer/2022062419/5581774ad8b42ae15f8b5176/html5/thumbnails/10.jpg)
File no. | 10
Depot Technologies are In Hand
Autonomous Rendezvous and Docking– XSS-11 and Orbital Express show ARD to be straightforward, cost effective
Cryogenic Propellant Storage, Thermal Management– Settled-Propellant design is critical to eliminating complexity and risk
– Existing designs/data/analyses directly applicable
– LO2-only design decreases thermal storage complexity and risks
– Foundation for LH2-only systems as needs evolve
– Analysis shows 0.01%/day boil-off is possible, supporting long, passive cryo storage
Cryogenic Propellant Gaging, Interconnection, Transfer, Control– Settled operation takes all the risk out
– Transfer identical to engine propellant feed
– High capacity interconnects based on slip-joint ducting
– Mass gaging simple and accurate without exotica
– Vent control based on existing designs, proportional valving
![Page 11: Sa08 Prop Depot Panel Frank Zegler](https://reader036.vdocuments.us/reader036/viewer/2022062419/5581774ad8b42ae15f8b5176/html5/thumbnails/11.jpg)
File no. | 11
ULA Technology Development
Gas Strut Deployable Sunshield– Full scale demo in 2007. Continued 2008
Intermediate Bulkhead Load Bearing Insulation– Compressive load cryostat completed, testing underway
• Insulation selection 2008
– Bulkhead concept definition 2008
Rotational Propellant Settling Flight Demonstration– Using 11kLbm residuals on Centaur spring 2008
H2 Para-Ortho Hardware Demonstration– Completed baseline demo, more work 2008
H2/O2 Catalytic Thruster– >1 hour hotfire time 2007, continued development 2008
Integrated H2/O2 propulsion/fluids system– No Ghe, No Hydrazine, Long Duration capable
– Concept validated 2007, continued work 2008
Cryogenic proportional valving, Cryo-compatible regulator array– Development start 2008
Ullage
Liquid
![Page 12: Sa08 Prop Depot Panel Frank Zegler](https://reader036.vdocuments.us/reader036/viewer/2022062419/5581774ad8b42ae15f8b5176/html5/thumbnails/12.jpg)
File no. | 12
Cryo Transfer Extensibility
Transfer of cryogens is mandatory for exploration– Real exploration implies long stay durations, indeterminate mission design
• Routine handling of tons of LH2 and LO2 for fuel cells, ECLSS• Scavenging of propellants from expended stages and landers• Allows practical sizing for vehicles with wider range of missions
– ISRU has large-scale cryogenic propellant handling at its heart– Mars implies routine and unlimited fill/transfer/refill operations
• Accumulation of Mars-bound assets at L1/L2 is essentially mandatory for even a skeleton exploration crew– Near-continuous pre-departure propellant delivery missions
• Propellant Synthesis, densification and storage on the surface– Orbital and endoatmospheric operations
• Mars is a near-perfect SSTO location– Replenishment of Earth-return assets in Mars orbit
Enhances science missions through orbital replenishment and servicing
This Technology is EssentialThis Technology is Essential
![Page 13: Sa08 Prop Depot Panel Frank Zegler](https://reader036.vdocuments.us/reader036/viewer/2022062419/5581774ad8b42ae15f8b5176/html5/thumbnails/13.jpg)
File no. | 13
Summary
Propellant transfer is a powerful tool– Amplifies existing ESAS capabilities (doubling or tripling of cargo)
• Removes unrealistic demands on proposed vehicle designs– Hardware simplificationlowered risklowered costfaster
schedulehigher ratebetter sciencemore popular support Simple depots can be done NOW
– Single propellant, single launch, single unit– Simple, proven thermal management, propellant xfer techniques
Provides a mission all launch suppliers can participate in– High density, low intrinsic value cargo with simple mission– Ideal cargo for first generation SSTO/reuseable vehicles
• SSTO vehicles have low inherent lift capability but depot demands provide high launch rate for economic operations
– Must support multiple SSTO vehicles for viability• Sets the stage for later LEO lift of propellant for Mars missions