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ADVANCED CONCEPTS BRANCH
Lander Propulsion Overview and TechnologyLander Propulsion Overview and Technology
Requirements DiscussionRequirements Discussion
Constellation Technology ConferenceConstellation Technology Conference
Galveston, TXGalveston, TX
November 14 November 14 –– 15, 2007 15, 2007
ADVANCED CONCEPTS BRANCH 2
AgendaAgenda
• Lander Project Overview
– Project Evolution/Design Cycles
– Lunar Architecture & Lander Reference Missions
– Lander Concept Configurations
• Descent Module Propulsion Overview
• Ascent Module LOX/CH4 Propulsion Overview
• Initial Technology Requirements Development
ADVANCED CONCEPTS BRANCH 3
Lander Project Overview
ADVANCED CONCEPTS BRANCH 4
Lander Project TimelineLander Project Timeline
• Constellation Level III Lander Project stood up in March
2007 (Laurie Hansen-PM, Dan Schumacher-DPM)
• Lander Team Kickoff in early April 2007
• Lander Design Analysis Cycle 1, (LDAC-1) April, 28 –
July 1, 2007.
• Currently in LDAC-1 Delta – Cargo Optimized Lander –
redirection after discussions with LAT II.
• LDAC-2 to start in Nov/Dec
ADVANCED CONCEPTS BRANCH 5
LDAC-1 Starting PointLDAC-1 Starting Point
• Developed Packaging Concept
– Brainstorming with NASA centers across the country
– Maintain CG along CL (independent of payload mass)
– Single decent engine on CL – present minimum approach
– 8.4 meter shroud (7.5 meter internal)
• 3 DRMs with Timelines and Functional Allocations
– Sortie Mission to South Pole! 4 Crew / 7 Days on Surface / No support from surface assets
! No restrictions on ‘when’ (accommodating eclipse periods)
– Outpost Mission to South Pole
! 4 Crew with Cargo Element (LAT Campaign option 2)
! Outpost provides habitation on surface (down and out)
! 210 Days with surface support (power)
– Cargo Mission to South Pole
! Common descent stage design with kits
• LDAC-1 optimized crewed Lander to deliver LAT payload! How much mass could be delivered in the required volume?
ADVANCED CONCEPTS BRANCH 6
CaLV Launch
CLV Launch
TLI
EDS Disposal
LOI
Descent
Ascent
Ascent Stage
Disposal
Trans - lunar Coast
1
2
3
4
5
6
7
9
10
8
Surface
Mission
CaLV Launch
CLV Launch
TLI
EDS Disposal
LOI
Descent
Ascent
Ascent Stage
Disposal
Trans - lunar Coast
11
22
33
44
55
66
77
99
1010
88
Surface
Mission
Mission ArchitectureMission Architecture
ADVANCED CONCEPTS BRANCH 7
Key Minimum Functional LanderKey Minimum Functional LanderDesign FeaturesDesign Features
• Propulsion – AM is single MMH / NTO engine (sizing for AM mass
resulted in Shuttle / CEV similar OME). DM is single LOX/LH2
expander cycle engine.
• Structures – Composite panel with aluminum or titanium honeycomb
core. Composite and metallic struts. Optimization of DM in work (truss
vs panel).
Key features do not represent “baselines” rather an
initial solution from which to evaluate engineering
trades, etc..
ADVANCED CONCEPTS BRANCH 8
LDAC-1 Sortie ConfigurationLDAC-1 Sortie Configuration
ADVANCED CONCEPTS BRANCH 9
LDAC -1 DeltaLDAC -1 Delta
Task: Design a descent stage (structure and propulsion tanks) that
is optimized for the cargo mission. Must also perform the crewed
Outpost (down and out) and Sortie missions - but not delivering
crew + large payload. Propulsion tanks will be sized for the cargo
mission.
• Unchanged from DAC 1
– Single descent engine on CL (RL-10 A4 CECE)
– Shroud diameter (7.5 meter internal)
– Lander performs LOI burn
– TLI control masses
– DRMs and timelines (minor changes)
Initial results indicate achievable PL mass not enough to support
original LAT II Lunar logistics. Lander configuration and focus re-
directed for LDAC-1 Delta
ADVANCED CONCEPTS BRANCH 10
Descent Module
Propulsion System
ADVANCED CONCEPTS BRANCH 11
Key Propulsion Trades
Results of Descent Main Propulsion Study (3/9/2007)Results of Descent Main Propulsion Study (3/9/2007)
Throttle requirement is based on a minimum stage thrust of 5600 lbf.
Estimated payload losses do not include penalties due to throttling effects on Isp.
Option 1a 1b 2 3 4 5 ESAS
Engines 1 1 2 3 4 4 4
Engine Thrust (lbf) 28,000 18,600 13,500 13,500 9,000 13,500 15,000
Engine-out No No Partial Yes Yes Yes 1+1 Yes 1+1
Stage Thrust (lbf) 28,000 18,600 27,000 40,500 36,000 54,000 60,000
PDI Thrust (lbf) 28,000 18,600 27,000 27,000 27,000 27,000 30,000
Throttle 5.0 3.3 4.8 7.2 6.4 9.6 10.7
1/Thr 0.20 0.30 0.21 0.14 0.16 0.10 0.09
PDI Throttle 1.00 1.00 1.00 0.67 0.75 0.50 0.50
100% Isp (sec) 450 450 446 446 446 446 455
PDI Isp (sec) 450 450 446 440 441 435 455
LOI Burn Time 394 593 405 270 304 203 186
PDI Burn Time * 594 775 610 602 603 595 560
Total Burn Time 988 1368 1015 872 907 798 746
0.0
200.0
400.0
600.0
800.0
1000.0
1200.0
1400.0
15000 20000 25000 30000 35000 40000
PDI Thrust (lbf)
Re
lati
ve
Pa
ylo
ad
In
eff
icie
nc
y (
lbm
)
4 Engines, 1+1
Engine Out
3 or 4 Engines,
1 Engine Out
Single Engine,
NO Engine Out
Assuming
14 Mt Lander PL
~ 1% PL Loss
~ 2% PL Loss
~ 3% PL Loss0
.25
T/W
0.0
200.0
400.0
600.0
800.0
1000.0
1200.0
1400.0
15000 20000 25000 30000 35000 40000
PDI Thrust (lbf)
Re
lati
ve
Pa
ylo
ad
In
eff
icie
nc
y (
lbm
)
4 Engines, 1+1
Engine Out
3 or 4 Engines,
1 Engine Out
Single Engine,
NO Engine Out
Assuming
14 Mt Lander PL
~ 1% PL Loss
~ 2% PL Loss
~ 3% PL Loss0
.25
T/W
Off-optimal single engine solution
chosen for LDAC-1 due to low
technology risk, and system
complexity benefits
ADVANCED CONCEPTS BRANCH 12
LDAC-1 Delta: Descent Main Propulsion Schematic
Engin
e #
1
LO
X-1
LO
X-2
LO
X-3
LO
X-4
P P P P
GHe
s
TVS TVS TVS TVS
VRVRVRVR
sss
s
s
LOX Vent
LOX Fill/Drain
LH2 Fill/Drain
ss
GH
e F
ill/V
ent
Pneumatics/Purge
Pre
ss/P
re-p
ress
TVS
s
VR
PPneumatic Valve
Pneumatic
Vent/Relief Valve
Relief Valve
Solenoid Valve
Check Valve
Pressure Regulator
Filter
Thermodynamic
Vent System
Diffuser
TIVOx1 TIVOx2 TIVOx3 TIVOx4
TIVOx1-P TIVOx2-P TIVOx3-P TIVOx4-P
GHe
s
GHeGHe
Power System
Interface
PP
LH
2-1
LH
2-2
LH
2-3
LH
2-4
P P P Ps
TVS TVS TVS TVS
VRVRVRVR
sss
TIVF1 TIVF2 TIVF3 TIVF4
TIVF1-P TIVF2-P TIVF3-P TIVF4-P
LH2
Vent
TVCA-1a
TVCA-1b
Simplified Schematic
ADVANCED CONCEPTS BRANCH 13
Ascent Module
Propulsion System
ADVANCED CONCEPTS BRANCH 14
Ascent Module PropulsionAscent Module Propulsion
• Both NTO/MMH and LOX/CH4 under consideration
• Initial LDAC-1 design assumed NTO/MMH integrated RCS/MPS
• After completion of LDAC-1, Ascent Propulsion System re-
designed using LOC/CH4
• LOX/CH4 AM design completed by LAT-II team lead by Eric
Hurlbert (Many CFM Project team members involved)
• Following Charts – from LDAC-1 LOX/CH4 activity, not sized for
LDAC-1 Delta (Cargo Optimized) Lander.
ADVANCED CONCEPTS BRANCH 15
LDAC-1b: Ascent Main/RCS Propulsion SchematicUnchanged from LDAC-1a
S
t1
MMH
tp2
pp1
RCS Thruster Quads
GHe
p5
GHetHe2
pHe1
S S
S S
S S
S
p1
p2
Function:
Service Hand Valve, HV
High Pressure Latching Valve, HP
Regulator, Rg
Check Valve, CV
Filter, F
Low Pressure Latching Valve, LV
Solenoid Valve (dual coil), SV
Burst Disk/ Relief Valve RV
Heater Ht
Pressure Sensor P
Temperature Sensor T
HVHe01
HPHe1
FHe1
RgHe1
CVHe1
FHe5
LVFu1
RVFu1
HVFu01
HVFu2
HVFu3
CVHe2
FHe6
LVOx1
LVFu2
RVOx2
HVOx1
HVOx2
HVOx3
FFu1FOx1
LVOx2
t2
t4t3
Fluids:
Helium He
Nitrogen Tetroxide (NTO) Ox
Monomeythhydrazine (MMH) Fu
Thruster 1,2,3,4 Thruster 5,6,7,8
Thruster 9,10,11,12 Thruster 13, 14, 15, 16
p4
HVFu4
HVOx4t6
t5
S S S S
t12t11t10t9
S S S S
t7
t8
S S S S S S S St24t23t22t21
p6
p3
HVFu5
HVOx5
MMH NTO NTO
Ascent Engine
t16t15t14t13
t20t19t18t17
tp1
tp4
tp3
tp6
tp5
tp8
tp7
pp2
tHe1
GHe GHetHe2tHe1
Simplified Schematic
ADVANCED CONCEPTS BRANCH
Ascent Stage
LO2/LCH4 Integrated Propulsion System
Notional Schematic (Minimalist)
S
t1
LCH4
tp2
pp1
RCS Thruster Quads
GHe
p5
GHetHe2
pHe1
S S
S S
S S
S
p1
p2
Function:
Service Hand Valve, HV
High Pressure Latching Valve, HP
Regulator, Rg
Check Valve, CV
Filter, F
Low Pressure Latching Valve, LV
Solenoid Valve (dual coil), SV
Burst Disk/ Relief Valve RV
Heater Ht
Pressure Sensor P
Temperature Sensor T
HVHe01
HPHe1
FHe1
RgHe1
CVHe1
FHe5
LVFu1
RVFu1
HVFu01
HVFu2
HVFu3
CVHe2
FHe6
LVOx1
LVFu2
RVOx2
HVOx1
HVOx2
HVOx3
FFu1FOx1
LVOx2
t2
t4t3
Fluids:
Helium He
Liquid oxygen (LO2) Ox
Liquid Methane (LCH4) Fu
Thruster 1,2,3,4 Thruster 5,6,7,8
Thruster 9,10,11,12 Thruster 13, 14, 15, 16
p4
HVFu4
HVOx4t6
t5
S S S S
t12t11t10t9
S S S S
t7
t8
S S S S S S S St24t23t22t21
p6
p3
HVFu5
HVOx5
LCH4 LO2 LO2
Ascent Engine
t16t15t14t13
t20t19t18t17
tp1
tp4
tp3
tp6
tp5
tp8
tp7
pp2
tHe1
TVS / Vent valve
Bleed valvesBleed valves
Eric Hurlbert/JSC
Simplified Schematic
ADVANCED CONCEPTS BRANCH 17
CFM - Storage of LO2 and LCH4CFM - Storage of LO2 and LCH4for the Outpostfor the Outpost
• Design
– LO2 and Methane are loaded subcooled and allowed to
absorb heat leak and warm over the LEO loiter, transit, and
210 day surface stay
• Thermal Modeling Has been performed by GRC and
MSFC to validate this approach
– Both models show heat leaks that result in zero boil-off for
the outpost mission
– Sortie Mission capability for zero boil-off also exists
Steve Sutherlin, MSFC
Bob Christie, GRC
Dave Plachta, GRC
Solar/Surface-Shields under concept
investigation for application to LOX/CH4
surface Storage
ADVANCED CONCEPTS BRANCH 18
Technology Requirements Development
ADVANCED CONCEPTS BRANCH 19
• LOX/LH2 Deep Throttling Pump Feed Engine(s)
• LOX/CH4 Pressure Feed Main Engine
• LOX/CH4 RCS Thrusters
• Cryogenic Propellant Storage and management
– LOX/LH2
– LOX/CH4
• Cryo Mass Gauging
– LOX, LH2, LCH4
• Low Heat Transfer Tank Mountings, and interfaces
• Variable area valve and actuation technology
Technology Needs
ADVANCED CONCEPTS BRANCH 20
• LOX/LH2 Ascent Propulsion
– 1 – 4 engines
– 28 – 30 klbf optimal stage thrust
– 35 – 40 klbs optimal stage thrust (engine out configurations)
– Throttle range (3.3 to 1) – (8 to 1)
– LOX/LH2 Main Engine (Expander Cycle)
! 4500 lbf – 6500 lbf
! 448 sec Isp (maximize @ 100% RPL)
! 2 – 4 starts per mission
– LOX/LH2 Storage & Fluid Management
! 14 – 28 days LEO
! 3 days Transit
! 2 days LLO
Descent Propulsion Technology Assumptions
ADVANCED CONCEPTS BRANCH 21
• LOX/CH4 Ascent Propulsion
– LOX/CH4 Main Engine (Pressure Feed)
! 4500 lbf – 6500 lbf
! 355 sec Isp
! 1 – 3 starts per mission
– LOX/CH4 RCS Thrusters
! 100 lbf
! 80 ms pulse length (40 ms growth risk)
! 300 + sec Isp
– LOX/CH4 Storage & Fluid Management
! 14 – 28 days LEO
! 3 days Transit
! 2 days LLO
! 210 days Lunar surface
Ascent Propulsion Technology Assumptions
ADVANCED CONCEPTS BRANCH 22
Additional Questions and Answers