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Lunar Lander Vehicle Design Overview
Wayne LeeLunar Lander Industry Day13 December 2007
2
Vehicle Architecture
DescentModule
AscentModule
Airlock Three Primary Elements
– Descent module
• Provides propulsion for LOI and powered descent
• Provides power during lunar transit, descent, and surface operations
• Serves as platform for lunar landing and liftoff of ascent module
– Ascent module
• Provides propulsion for ascent from lunar surface after surface mission
• Provides habitable volume for four during descent, surface, and ascent operations
• Contains cockpit and majority of avionics
– Airlock
• Accommodates two astronauts per ingress/egress cycle
• Connected to ascent module via short tunnel
• Remains with descent module on lunar surface after ascent module liftoff
3
Key Preliminary Specifications
Number of Crew up to 4
Sortie Mission Duration 14 days LEO (unoccupied)
4 days trans-lunar coast
1 day LLO
7 days surface
7 hours ascent (including disposal)
Total Mass at Lift-off 45,000 to 53,600 kg
Total Propellant Mass 26,652 kg (sortie)
Height of Vehicle Stack 10.52 m, legs uncrushed
Height of DM Deck Above Surface 6.97 m, legs uncrushed
Maximum Diameter of Vehicle 7.5 m, legs stowed
Diameter of Landed Footprint 14.53 m, legs deployed
Descent Propulsion LOX/LH2 Main, MMH/NTO RCS
Ascent Propulsion MMH/NTO Main and RCS
Total V Capability ~2960 m/s
4
Configuration Variants
Vehicle will be configurable as three different variants
– Sortie variant
• Utilized for surface missions up to seven days where crew will use ascent module as living quarters and a base of operations for EVAs
• Employs all major elements -- descent module, ascent module, airlock
– Outpost variant
• Utilized for surface missions up to 210 days where crew will work out of a lunar base
• Configured similar to sortie variant, but without airlock; crew will depressurize ascent module upon landing and head directly for outpost
• Keep-alive power assumed to be provided by outpost
– Cargo variant
• Utilized to deliver large, presumably outpost modules to the surface
• No ascent module or crew; cargo will sit on upper deck of descent module
• Vehicle components normally resident in ascent module will be attached to upper deck of descent module
5
Configuration Variants
Outpost Variant45,000 kg
Descent ModuleAscent Module
Sortie Variant45,000 kg
Descent ModuleAscent Module
Airlock
Cargo Variant53,600 kg
Descent ModuleCargo on Upper Deck
6
Configuration Commonality
Design paradigm is to maximize commonality across variants
– Descent module structure optimized to deliver maximum amount of payload mounted to the deck in cargo mode, but use same structure for all three
– Descent propulsion is identical for all three with exception of propellant load
• Launch mass allocation of 45,000 kg for sortie and outpost variants increased to 53,600 kg for cargo mission due to benefit of Ares V not needing to accelerate Orion vehicle through TLI burn
• Tanks sized for propellant volume needed for 53,600 kg cargo mission, but only filled to level needed to support sortie and outpost variant mass
– Ascent module structure and propulsion is identical for sortie and outpost variants
– Other subsystems are identical in concept for all three variants
• Choice of components and sizing are the same for all three variants
• Minor variations in schematics and physical layout to account for mission-specific details
7
Mass Distribution Comparison of Variants
Dry Mass 9,522.1 kg
Non-Propellants and Other 2,568.7 kg
Propellant 26,651.7 kg
Manager's Reserve 2,856.6 kg
Mass Available for Payload 3,400.9 kg
Total Vehicle 45,000 kg
Thermal Control
Life Support
Other
Propellant
Structures and Mechanisms
Propulsion
Non-Propellant Fluids
Manager's Reserve
Power
Avionics
Mass Available for Payload
Propellant
Propulsion
Structures and Mechanisms
Power
Avionics
Thermal Control
Other
Life Support
Non-Propellant Fluids
Manager's Reserve
Mass Available for Payload
Structures and Mechanisms
Propulsion
Thermal Control
Life Support
Other
Propellant
Non-Propellant Fluids
Manager's Reserve
Mass Available for Payload
Avionics Power
Dry Mass 8,971.9 kg
Non-Propellants and Other 2,287.5 kg
Propellant 26,780.0 kg
Manager's Reserve 2,691.6 kg
Mass Available for Payload 4,269.0 kg
Total Vehicle 45,000 kg
Dry Mass 6,901.2 kg
Non-Propellants and Other 1,351.0 kg
Propellant 26,319.3 kg
Manager's Reserve 2,070.4 kg
Mass Available for Payload 16,958.1 kg
Total Vehicle 53,600 kg
Sortie Mission Lander Outpost Mission Lander Uncrewed Cargo Mission Lander
8
Structures Summary
Descent Module Structure
– Cruciform truss configuration, four landing legs (stowed at launch)
– Aluminum construction
– Current mass w/o growth 2110 kg
Ascent Module Structure
– Cylindrical-shaped pressure vessel
– Composite construction
– Current mass w/o growth 625 kg
Airlock Structure
– Cylindrical-shaped pressure vessel
– Aluminum construction
– Current mass w/o growth 312 kg
Launch Vehicle
Adaptor (EDS)
Airlock
AscentModule
Landing Leg
9
Descent Module Configuration
Upper LH2
Support Struts (32)(tension rods)
Lower LH2
Support Struts (16)(stabilizers)
Cruciform Primary Structure
LH2 Tanks (4)
LOX Tanks (4)
Lower LOX Tank Support Cones (4)
10
Ascent Module Configuration
MMH Tank (2)
AM/DM Adapter
Lower Interface Beam
Front WindowFrame (2)
LIDS Docking Adaptor (previous version shown)
NTO Tank (2)
Top Flange (4)
Docking WindowFrame (2)
Tank Structure (24 struts)
Separation System (Marmon Band)
Engine
11
Airlock Configuration
Pressure Shell Skin
Bottom Flange (4)
Truss Structure Strut (8)
EVA Hatch Window
AM / Airlock Tunnel
AM / Airlock Tunnel Frame
EVA Hatch
EVA Hatch Frame
12
Propulsion Summary
Ascent Module Propulsion
– Single MMH/NTO main engine, 24,465 N (5,500 lbf) thrust
– 16 MMH/NTO RCS thrusters
– 2 MMH, 2 NTO tanks shared between main and thrusters
– Current dry mass w/o growth 666 kg
Descent Module Propulsion
– Single LOX/LH2 main, 82787 N (18,627 lbf) thrust, restart capability, 3.3:1 throttle ratio
– 4 LOX, 4 LH2 tanks
– 16 MMH/NTO RCS thrusters
– Current dry mass w/o growth 2510 kg
Ascent Main Engine
Descent Main Engine
LH2 Tank
LOX Tank
MMH Tank
NTO Tank
Helium Tank
Thrusters(position TBD)
13
DM Main Propulsion SchematicL
H2-1
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
TIVOx1
TVS
TIVOx3-P TIVOx4-P
Engine #1
LO
X-1
LO
X-2
LO
X-3
LO
X-4
P P P P
GHe
s
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
TIVOx2 TIVOx3 TIVOx4TIVOx1-P TIVOx2-P
GHe
s
GHeGHe
Power SystemInterface
P
PLH2Vent
TVCA-1a
TVCA-1b
14
Ascent Propulsion Schematic
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, HVHigh Pressure Latching Valve, HPRegulator, RgCheck Valve, CVFilter, FLow Pressure Latching Valve, LVSolenoid Valve SBurst Disk/ Relief Valve RVHeater HtPressure Sensor PTemperature Sensor T
HVHe01
HPHe1
FHe1
RgHe1
CVHe1
FHe5
LVFu1
RVFu1
HVFu01
HVFu2
HVFu3
CVHe2
FHe6
LVOx1
LVFu2
RVOx2
HVOx1
HVOx2
HVOx3FFu1 FOx1
LVOx2
t2
t4t3
Fluids:Helium HeNitrogen Tetroxide (NTO) OxMonomeythhydrazine (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
15
Power Summary
Descent Module
– PEM fuel cell, 5.5 kW peak production
– Provides AM and DM power for LLO, surface operations
• Orion provides 1.5 kW when docked
– Propulsion residuals provide reactants for surface operations
– Current inert mass w/o growth 148 kg (sortie)
Ascent Module and Airlock
– Single primary battery, LiSO2
chemistry, 14.2 kW-hr capacity
– Current mass w/o growth 139 kg
Bus
– 28 V unregulated bus
16
Thermal Summary
Ascent Module and Airlock
– Inner loop with coldplates and sublimator
– Heat transferred to outer loop for rejection during cruise, LLO, surface
– MLI and black Kapton insulation on structure
– Current inert mass w/o growth 208 kg
Descent Module
– Outer loop utilizes radiators for heat rejection
– SOFI insulation on propellant tanks, silverized teflon and MLI on structure
– Current inert mass w/o growth 974 kg (sortie), 990 kg (cargo)
Ascent Module
Airlock
External Volume
subl
imat
or
T
pumpFM
Acc
um.
FW
tank
reg
p
pyro
fuel cellFC
gas feedHX
coldplate(1 ext.)
dedicatedradiator (2)
p
coldplate(9 int.)
Inte
r-Lo
opH
/X
pump
p
Acc
um.
coldplate(8 ext.)
FM
T
T
Reg
en.
H/X
T
20% PG80% water
HFC-245fa
radiator
radiator
T
T
T
p
heaters
T
coldplate(1 int.)
LCGH/X
CabinH/X
SuitloopH/X
Radiator(another on other side)
Sublimator(attached to AM)
17
Life Support Summary
Atmosphere
– Between 57 and 83 kPa
– Cabin loop provides for heat removal
– Suit loop provides for CO2, moisture, heat removal from suit umbilicals
– Suit loop also removes CO2 from cabin air via amine swing beds
Water
– Internal tank holds one day of potable water with silver ion biocide
– External tank accumulates water from fuel cells for internal tank, EVA recharge, and thermal
Waste
– Collection and disposal provided
Current mass w/o growth 212 kg (sortie)
Ascent ModuleComponents
AirlockComponents
18
C&DH Design Status
Project strategy regarding C&DH has been not to instantiate a baseline design using available components
– Over 10+ years to go until first flight
– Relatively rapid progress in evolution of electronics may render today’s design obsolete
Baseline C&DH architecture is currently under study by a multi-NASA-center team with the following objectives
– Determine functional properties of architectures that have favorable characteristics relative to Lander performance requirements
– Develop candidate architectural concepts that satisfy the desired characteristics, but are expandable and extensible
– Identify technology and/or component families suitable for use in populating the architecture
– Develop a functional/mass equivalent design placeholder using existing parts, if available
19
GN&C Summary
Sensor Suite
– Star tracker and MIMU data for propagation of attitude and position for all phases of flight
– Pulsed Doppler radar provides altitude and velocity during landing
– Lidar provides range and bearing to Orion during rendezvous
– Rendezvous camera used during terminal approach prior to docking
Control Suite
– 16 thrusters on DM allows for attitude control during cruise, LLO, descent
– DM main engine gimbals by 6° to keep thrust aligned with c.g.
– 16 thrusters on AM allows for attitude control and main engine thrust vector pointing during ascent
MIMU(inside AM)
Lidar and Camera(top front of AM)
Star Tracker
DM RCS Thruster Pod
Radar Electronics(inside DM)
Radar Antennas(not shown, mountedon lower edge of DM)
20
Telecom Summary
Primary Radio
– S-band transponder for link with Orion and Earth
– SSPA with 40 W output power
– 2 ISS-heritage low-gain antennas with 120° field of view
Link Performance
– 80 kbps to 18-m Earth network, 190 kbps to 34-m network
– 2.3 Mbps to Orion at 100 km range
– Significant fraction of data volume in minimal functional design occupied by overhead (headers, IP, etc.)
EVA Radio
– 802.16 transceiver currently in development
Low-Gain Primary
Antennas
SSPA(top face of AM)
21
Summary
Vehicle design shown today is from the first design cycle (LDAC-1)
– Minimum functional design; not intended for flight
– Design basis was the design reference mission as opposed to a detailed requirements set
Implementation choices should not be considered frozen with the exception of a few key architectural features
– 4 crew, descent propellant, inclusion of an airlock, use of LIDS docking adaptor for Orion
Forward work for FY08
– Evaluate upgrades for safety and reliability
– Evaluate upgrades for lunar global access and enhanced functionality
– Mature preliminary design and develop requirement sets and specifications
– Evaluate technologies for mass reduction