Transcript Document

Lunar Lander
Vehicle Design
Overview
Wayne Lee
Lunar Lander Industry Day
13 December 2007
Vehicle Architecture
Airlock
 Three Primary Elements
–
Ascent
Module
–
–
Descent
Module
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
2
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
3
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
4
Configuration Variants
Sortie Variant
Outpost Variant
Cargo Variant
45,000 kg
45,000 kg
53,600 kg
Descent Module
Ascent Module
Airlock
Descent Module
Ascent Module
Descent Module
Cargo on Upper Deck
5
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
6
Mass Distribution Comparison of Variants
Sortie Mission Lander
Outpost Mission Lander
Uncrewed Cargo Mission Lander
Avionics
Avionics
Avionics
Power
Power
Power
Mass Available for Payload
Mass Available for Payload
Structures and Mechanisms
Structures and Mechanisms
Structures and Mechanisms
Manager's Reserve
Propulsion
Thermal Control
Propulsion
Manager's Reserve
Life Support
Other
Non-Propellant Fluids
Propulsion
Thermal Control
Mass Available for Payload
Life Support
Thermal Control
Life Support
Other
Other
Non-Propellant Fluids
Non-Propellant Fluids
Manager's Reserve
Propellant
Propellant
Propellant
Dry Mass
9,522.1 kg
Dry Mass
8,971.9 kg
Dry Mass
6,901.2 kg
Non-Propellants and Other
2,568.7 kg
Non-Propellants and Other
2,287.5 kg
Non-Propellants and Other
1,351.0 kg
Propellant
26,651.7 kg
Propellant
26,780.0 kg
Propellant
Manager's Reserve
2,856.6 kg
Manager's Reserve
2,691.6 kg
Manager's Reserve
Mass Available for Payload
3,400.9 kg
Mass Available for Payload
4,269.0 kg
Mass Available for Payload
Total Vehicle
45,000 kg
Total Vehicle
45,000 kg
Total Vehicle
26,319.3 kg
2,070.4 kg
16,958.1 kg
53,600 kg
7
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
Airlock
 Ascent Module Structure
–
Cylindrical-shaped pressure vessel
–
Composite construction
–
Current mass w/o growth 625 kg
Landing Leg
 Airlock Structure
–
Cylindrical-shaped pressure vessel
–
Aluminum construction
–
Current mass w/o growth 312 kg
Launch
Vehicle
Adaptor (EDS)
8
Descent Module Configuration
Cruciform Primary Structure
LH2 Tanks (4)
LOX Tanks (4)
Upper LH2
Support Struts (32)
(tension rods)
Lower LH2
Support Struts (16)
(stabilizers)
Lower LOX Tank
Support Cones (4)
9
Ascent Module Configuration
Docking Window
Frame (2)
LIDS Docking Adaptor
(previous version shown)
Top Flange (4)
Front Window
Frame (2)
MMH Tank (2)
Tank Structure
(24 struts)
NTO Tank (2)
Lower Interface Beam
Separation System
(Marmon Band)
AM/DM Adapter
Engine
10
Airlock Configuration
Pressure Shell Skin
EVA Hatch Frame
AM / Airlock
Tunnel Frame
EVA Hatch Window
EVA Hatch
AM / Airlock Tunnel
Bottom Flange (4)
Truss Structure Strut (8)
11
Propulsion Summary
 Ascent Module Propulsion
Thrusters
(position TBD)
–
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
NTO Tank
–
Current dry mass w/o growth 666 kg
Helium
Tank
 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
MMH Tank
Ascent Main Engine
LH2 Tank
LOX Tank
Descent Main Engine
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DM Main Propulsion Schematic
GHe
GHe
s
Pneumatics/Purge
P
GHe
GHe
GHe Fill/Vent
Press/Pre-press
VR
Power System
Interface
Pneumatic Valve
Pneumatic
Vent/Relief Valve
Relief Valve
s
Solenoid Valve
Check Valve
s
s
s
s
Pressure Regulator
Filter
TVS
LOX Vent
Thermodynamic
Vent System
Diffuser
LH2
P
s
s
s
s
Vent
LOX Fill/Drain
LH2-2
LH2-3
LH2-4
LOX-4
TIVOx4-P
TIVOx4
TVCA-1a
TVCA-1b
Engine #1
TIVF4-P
TIVF4
TVS
TIVOx3-P
TIVOx3
P
TIVF3
TVS
TIVOx2-P
TIVOx2
P
TIVF2
TVS
TIVF3-P
P
TIVF1
TVS
TIVF2-P
P
TVS
TIVF1-P
P
P
TVS
P
P
TVS
TIVOx1-P
TIVOx1
LOX-3
s
LOX-2
s
LOX-1
s
LH2-1
P
s
TVS
LH2 Fill/Drain
13
Ascent Propulsion Schematic
Function:
Service Hand Valve,
High Pressure Latching Valve,
Regulator,
Check Valve,
Filter,
Low Pressure Latching Valve,
Solenoid Valve
Burst Disk/ Relief Valve
Heater
Pressure Sensor
Temperature Sensor
tHe1
Fluids:
Helium
Nitrogen Tetroxide (NTO)
Monomeythhydrazine (MMH)
HV
HP
Rg
CV
F
LV
S
RV
Ht
P
T
He
Ox
Fu
tHe1
GHe
GHe
tHe2
tHe2
GHe
GHe
pHe1
HVHe01
HPHe1
FHe1
RgHe1
FHe5
FHe6
HVOx1
HVFu01
Thruster 5,6,7,8
Thruster 1,2,3,4
CVHe2
CVHe1
LVFu1
LVOx1
RVFu1
S
S
S
S
t13
t12
S
t11
t14
pp1
S
S
S
t10
t9
pp2
t16
t15
t5
p3
t6
p4
HVFu4
HVOx4
RVOx2
tp1
tp5
tp3
MMH
tp2
t3
MMH
tp7
NTO
NTO
tp6
tp4
tp8
t4
HVFu2
RCS Thruster Quads
HVOx2
LVFu2
LVOx2
FFu1
p5
t7
HVOx5
FOx1
p1
t1
p2
t2
HVFu5
t8
t18
t17
S
S
S
p6
t20
t19
S
t21
S
S
t24
t23
t22
S
S
HVOx3
HVFu3
S
S
S
S
S
S
S
S
Ascent Engine
Thruster 9,10,11,12
Thruster 13, 14, 15, 16
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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
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Thermal Summary
 Ascent Module and Airlock
Sublimator
(attached to AM)
Inner loop with coldplates and
sublimator
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
p
T
sublimator
–
External Volume
coldplate
(1 ext.)
dedicated
radiator (2)
coldplate
(9 int.)
LCG
H/X
Suitloop
H/X
Cabin
H/X
20% PG
80% water
p
reg
T
FC
gas feed
pump
HX
coldplate
(8 ext.)
p
T
Ascent Module
FM
T
pump
T
Current inert mass w/o growth 974 kg
(sortie), 990 kg (cargo)
fuel cell
p
HFC-245fa
T
T
pyro
Airlock
Accum.
–
FM
MLI and black Kapton insulation on
structure
Regen.
H/X
–
coldplate
(1 int.)
heaters
Inter-Loop
H/X
Heat transferred to outer loop for
rejection during cruise, LLO, surface
Accum.
–
Radiator
(another on other side)
FW tank
–
radiator
radiator
T
16
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
Ascent Module
Components
Airlock
Components
 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)
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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-NASAcenter 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
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GN&C Summary
Lidar and Camera
 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
(top front of AM)
MIMU
(inside AM)
Star Tracker
DM RCS
Thruster Pod
 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
Radar Electronics
(inside DM)
Radar Antennas
(not shown, mounted
on lower edge of DM)
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Telecom Summary
 Primary Radio
SSPA
(top face of AM)
–
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.)
Low-Gain
Primary
Antennas
 EVA Radio
–
802.16 transceiver currently in
development
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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
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