global exploration workshop ben donahue – moon mission ... 2_donahue_final.pdf · propel reserves...
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Copyright © 2011 Boeing. All rights reserved.BOEING is a trademark of Boeing Management Company.Copyright © 2011 Boeing. All rights reserved.
Global Exploration Workshop– Moon Mission Concept with Re-usable Lunar lander
Ben DonahueSr. Principle Engineer, Phantom Works
November 15, 2011
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Global Exploration Roadmap
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Capability Driven Network
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Reference: Bill Gerstenmaier presentation to the 16 June Space Council meeting. 3
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Flexible Path for Exploration
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Re-usable Lunar Lander Based at EML1 / 2
• A Gateway at EML1 or EML2 allows re-usability of the lunar lander which saves money and enhances development of the ultra-reliable systems needed for Mars
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• Our concept lander is much smaller than Altair; Dry mass of 7t, wet mass of 15t (Altair was ~45t wet)
• The propulsion system is designed to be re-fuelable LOX/Methane
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Lunar Lander as a Pathfinder for Mars
Lunar Lander
Mars Lander
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Lunar LanderCommon
Propulsion System
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Delivery of the Lunar Lander to the ISS -EP
• Commissioning crew flies with the lander to the platform
• Flight test program in the vicinity of the ISS-EP is used to prepare the lander for it’s first landing
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Lunar Mission Flight Profile
Descent Stage Performs Trans-lunar Insertion (TLI) and Places Lander into LLO
A Subsequent Burn ProvidesDescent Orbit Insertion (DOI)
Desc Stg Burn Desc Stage Separation
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LLO
Desc Stg Burn Initiates Descent
Desc Stage Continues and Impacts (Notional)
Lunar Lander Performs Terminal Descent and Lands
Desc Stage Separation Point From Lunar Lander
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Lunar Mission Flight Profile
100 km Lunar parking orbit
Separation
Nominal Descent Profile Vehicle Attitude
Thrust direction
DecreasingOrbital velocity
Flight
Nominal mode
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“Abort the Descent” Profile Vehicle Attitude
Thrust direction
IncreasingOrbital velocity
RaisesApoapsis
Altitude
ReturnTo parking
orbit
No Lander rotation required to initiate Abort to or bit burn
Lander is already in position to fire engines to re turn to orbit
Flight direction
Flight direction
Abort mode
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Lunar Lander Departing the ISS-EP
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Initial SLS Capability
� SLS provides the initial launch capability for exploration missions
� Lunar Mission Study Challenge:
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� Fly a complete lunar mission cycle with a single SLS launch
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Third Stage Evolution
Block 1 Block 2a“Moon First”
Delta 5m Upper Stage Block 2b“NEA First”
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• Tank increase from 5m to 5.5m
• 27t to 40t Capacity
• Block 2 NDS• Orbit Kit• Methane Tank
• Block 2 NDS• Orbit Kit• RL-10 Throttle
ARES 5.5m Tooling used to build demonstration tank
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Block 2a Third Stage for SLS
� Block 2a:– “Moon First” Configuration– Adds solar array system– AR&D functionality– Enhanced RCS capability– NDS with fluid transfer capability– Additional tank (toroidal) for
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– Additional tank (toroidal) for lunar lander methane delivery
– Assumes SLS 2 nd stage will be completed
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Lunar Lander Recurring Operations
• The goal for recurring operations should be to delivers the crew and all fuel for the lander in a single SLS launch
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Lunar Site Access
� Operational Considerations– Lunar Orbit Rendezvous (LOR)
� Access to lunar poles would require polar orbit if LOR mission mode utilized
� Lunar polar orbit provides infrequent opportunities for trans-Earth injection (once every 14 days)
– Orbit orientation inertially fixed, aligns with efficient trans-Earth trajectory twice a month
� Total ∆V = 8951 m/s– Libration Point Rendezvous (LPR)
Lunar Orbit
Lunar Polar
Orbit
Correct
Orientation
for Return
Correct
Orientation
for Return
LOR
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– Libration Point Rendezvous (LPR)� Continuous access from L1 to lunar surface and
return– Lunar rotation and libration point motion naturally synchronized
� Continuous access to Earth - landing point partially controllable
� Total ∆V = 10480 m/s
� Unique science opportunities at L 1
� Deep-space human exploration analogs exist at L 1
� Support for deep-space human exploration missions Lunar Orbit
L1
LPR
LOR
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Lunar Lander on the Surface
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Telepresence Precursor
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Dan Lester, Research FellowDepartment of [email protected]
University of Texas at Austin 512-471-3442
On-orbit telerobotic control is a new way of viewing human-robot cooperation.
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Lunar Mission – Summary
• Re-usable Lander – Pathfinder for Mars
• “Global Access” from EML1/2
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• “Global Access” from EML1/2
• Telerobotics Precursor Potential
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Backup Charts
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Lunar SurfaceReusable Surface Hab and Crew Lander
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Crew Lander – 15 mt Total Mass
Total Systems MassSurface Payloads
Total Lander MassCrew Cabin and Systems
Dry MassPropellant total
mass14.98 mt0.50 mt
14.48 mt3.15 mt2.72 mt8.61 mt
delta-V
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Propellant MassesPropel Reserves
L1 to LLO Prop MainL1 to LLO RCS
Terminal Desc Propel MainTerminal Desc RCSAscent Propel Main
Ascent RCSLLO to L1 Prop Main
L1 RCS Prop
8.61 mt0.17 mt
n / a0.02 mt1.92 mt0.04 mt5.20 mt0.04 mt1.18 mt0.04 mt
3,133 m/s
5 m/s500 m/s
10 m/s1950 m/s
10 m/s640 m/s
18 m/s
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Lunar Mission Mass Estimates
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LO2 / Methane CH4 Engines for Descent and AscentISRU derived Methane may be used for Mars ascent de scentDevelopmental programs underway at Aerojet and ATK/ CORLO2 residuals left in desc stg tanks available Crew on surfacePump-fed Methane engine provides significant Isp (3 72 sec)
over press-fed storable engine (320-328)Shared propel tank O2/CH4 main / RCS system in test
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Lander Close Up View
Legs in stowedposition
Legs
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Legs deployed