1. NASA Design Team January 31, 2003
Revolutionary Aerospace System Concepts Human Outer Planet Exploration FY02 – Concept Catalog
NASA Design Team
January 31, 2003

2. 30MWe Brayton/VASIMR next to the ISS

3. 30MWe Piloted Callisto Transfer Vehicle (PCTV) Artificial Gravity – Two TransHabs
Triangle Shaped Reactor Radiators
SA= 3330m2 Per Panel (13,320m2 Total)
Flat Panel and Cylindrical Radiators
4 Flat Panels SA=445m2 Total
2 Cylindrical SA=455m2
14m
26.4m
49m
34.0m
22.8m
42.7m
198m
“Preliminary” PCTV Mass Properties (Two TransHabs – Total Wet Mass 430MT
Series of 10MWe Brayton Fission Reactors provide 30MWe of electrical power for constant thrust
Variable Isp (3000s to 30,000s) with an varying efficiency Eff = 1X10-5 x Isp  
Total VASIMR Alpha = 0.76kg/kWe (Engine = 0.24kg/kWe, PPU = 0.52kg/kWe)
Dry Mass = 207MT
Propellant Capability = 118MT (NOTE: more tanks can be added)
Payload Masses = 105MT
Provides a constant 1/8g simulated gravity environment

4. Configuration of VASIMR Thrusters (Two TansHab - 30MWe) Callisto Spacecraft
RC Antenna
AFT
7.5 VASIMR Thrusters
(4 operating – 1 spare)
Garbage Containers
Shadow Shields
Adjustable Spin Balance (Help eliminate/reduce wobbling)
Engine Radiators
Reactors
TransHab and Surrounding LH2 Tanks
Reactor Radiators (Two Sided – Area = 13,320m2)
Cryogenic Radiators
FWD
TransHab and Surrounding LH2 Tanks

5. Configuration of 30MWe VASIMR Cargo Spacecraft
Same Configuration as Piloted Ship
IRSU Assembly
SurfaceHab
Tanker Section (189MT LH2)
Cargo Section
Lander
“Preliminary” PCTV Mass Properties (Cargo) – Total Wet Mass = 506MT
Dry Mass = 185 MT
Propellant Capability = 83MT
Payload Masses = 238MT (118 MT is return fuel)

6. Docking Method at Callisto
Cargo/Tanker
Piloted Ship
Fluid Docking Interface
VASIMR Engine
Configuration

7. Common elements between the LARC Cargo and Crewed Vehicles
Piloted Elements
Cargo/Tanker
Elements
Common elements between the
LARC Cargo and Crewed Vehicles
Differences between the LARC
Cargo and Piloted Vehicles
30 MWe Reactors and Radiators
Support Structure
VASIMR Engines

8. 10MWe Brayton/MPD next to the ISS

9. Triangle Shaped Reactor Radiators
Dimensions
5 MPD Thrusters per side
Reactors
Shadow Shield
Triangle Shaped Reactor Radiators
(3725m2 Total)
14m
Brayton Unit
12.5m
Feed Lines:
Propellant
Cooling
Power
16.0m
52.5m
15.0
3.0m
27.5m
“Preliminary” PCTV Mass Properties (Two TransHabs)
Brayton Fission Reactor 8 – 10 MW electrical power
Isp 8000s with efficiency of 64.5% 
Propellant Capability = 118MT
Payload Masses = 105MT
Provides a constant 1/8g simulated gravity environment

10. Configuration of 10MWe MPD Callisto Spacecraft
Aft RCS Thrusters
Brayton Power and Shadow Shield
Adjustable Spin Balance (Help eliminate/reduce wobbling)
Reactor Radiators (Two Sided – Area = 3725m^2)
TransHab and Surrounding LH2 Tanks
Cryogenic Radiators
MPD Thrusters
FWD RCS
Thrusters
FWD
Engine Radiators
Disposable Garbage Containers
TransHab and Surrounding LH2 Tanks

11. Graphite Cylinder Radius = 64cm Thruster and Radiator Configuration
Heat Pipes (26 Total)
Graphite Cylinder Radius = 64cm
Central Cylindrical Cathode
Radius = 2cm Length = 10cm
Annular Anode
Radius = 10cm Thickness = 1.3cm
Thruster and Radiator Configuration
Representative 2.5 MWe MPD Thruster / Radiator
8.0m
Dimensions are
Per Panel
45o
9.0m
30o
15o

12. Typical Radiator Panel From 10MWe System:
SA (Per Side) = 540m2
SA (Two Sided Panel) = 1080m2
Total SA (10MWe Brayton) = 4320M2
16m
2.0m
Typical Radiator Panel From 30MWe System:
SA (Per Side) = 1620m2
SA (Two Sided Panel) = 3240m2
Total SA (30MWe Brayton) = 12960m2
60m
32m
2.0m
90m

13. Brayton Power System 10 MWe (Series of one (1) 10MWe reactors
Aft Shadow Shield
FWD Shadow Shield
Feed Lines:
Propellant
Cooling
Power
Brayton Units
Radiation Shielded Feed Lines
Reactors
10 MWe (Series of one (1) 10MWe reactors
and 2 Brayton Units)
30 MWe (Series of three (3) 10MWe reactors
and 6 Brayton Units)

14. 200MWe Vapor Core Reactor Powered VASIMR
“Preliminary” PCTV Mass Properties (Two TransHabs – Total Wet Mass 623MT
1Vapor Core Reactors provides 200MWe of electrical power (Alpha=0.29kg/kWe)
Variable Isp (3000s to 30,000s) with an varying efficiency Eff = 1X10-5 x Isp  
Total VASIMR Alpha = 0.76kg/kWe (Engine = 0.24kg/kWe, PPU = 0.52kg/kWe)
Dry Mass = 368MT
Propellant Capability = 150MT
Payload Masses = 105MT

15. VCR Radiator Assumptions: VASIMR Radiator Assumptions:
4 (double sided )Flat Panels SA=968m2 Total
Cylindrical SA=612m2
Vapor Core / VASIMR
Two Sided Triangle Radiators
SA = 3279m^2
VAPOR Core Reactor
VCR Radiator Assumptions:
Overall power output efficiency of 20% while allowing operation of the condensing radiator at constant heat rejection temperature of 1500K.
VCR-MHD fuel/working fluid (UF4) could condense at just under 1atm.
Waste heat load is estimated to be about 800 MW yielding an area of 3279 m2 (assuming .85 effective emissivity for the radiator) or 46 MT at 14 kg/m2.
Piping is made of molybdenum alloy (TZM or other similar strength alloys) with composite
The radiator surface is the carbon/graphite composite fins
VASIMR Radiator Assumptions:
Thermal load = 900K using a molten salt coolant. At this temperature two-sided carbon fiber SiC radiator could be used and using the same conservative effective emissivity of .85 yield an area of 1580 m2 or MT at 6-8kg/m2.
estimate is based on using an overall efficiency of 50% for the VASIMR engine

16. HOPE Launch Vehicle Folding Landing Gear
NOTE: The gear is allowed to fold in order to be stowed in the Delta IV Launch Vehicle

17. LH2 Storage for Crew and Cargo Vehicles
Maximum sized tanks for given launch vehicle:
(Total: 22,891 kg/tank)
Tanks Properties:
Volume = 288m^3
Tank Mass = 2725kg
Inner Dia = 4.91m
Outer Dia=5.0m
Total Tank Length = 15.8m
Total Surface Area = 257m^2
Cryogenic system:
Radiator Surface Area = 66m^2
Radiator Mass = 530kg
Fluid Mass = kg (includes ullage and residual)
Cooler Mass = 107.5kg
Cooler Controler Mass = 150.5kg
Insulation Mass = 416kg
Tanks Around TransHab:
(Total: 3,240 kg/tank)
Tanks Properties:
Volume = 35m^3
Tank Mass = 516kg
Inner Dia = 2.4m
Outer Dia=2.5m
Total Tank Length = 8.3m
Total Surface Area = 64.6m^2
Cryogenic system:
Radiator Surface Area = 25.3m^2
Radiator Mass = 202.4kg
Fluid Mass = 2296 kg (includes ullage and residual)
Cooler Mass = 40.7kg
Cooler Controler Mass = 57kg
Insulation Mass = 103kg

18. HOPE Landers Various Configuration Supported by common base pallet
3 Person Element:
Dry Mass = 10,918kg
Wet Mass = 25,009kg
Fuel Needed to Descend = 8,721kg
Fuel Needed to Ascend = 5,370kg
SurfaceHab Element:
Dry Mass = 23,277kg
Wet Mass = 36,616kg
Fuel Needed to Descend = 13,339kg
IRSU Assembly Element:
Dry Mass = 24,719kg
Wet Mass = 37,909kg
Fuel Needed to Descend = 13,792kg
Common Base Pallet between all three:
LOX/LH2 Tanks will support the Lander Ascent and
Decent as well as the SurfaceHab and IRSU Ascent
Engine Layout
Landing Gear

19. configuration and specifics
ISRU Plant
configuration and specifics
2 Rovers
Reactors
IRSU Plant
Common Base Pallet
Stowed Landing Gear
Packaged in Delta IV – Font ramps not shown
IRSU and Reactor being reconfigured when landed
Fully extending Ramp – The rovers can now pull the Reactors off the ramps

20. Internal LH2 Properties (One Cylindrical Tank) Internal Lox Properties
3 Person Lander
3 person Crew Pod:
Volume = 19.3m3
MAX D5.0m
Base Section
9.6m
1.28m
4 ASE Engines
Internal LH2 Properties
(One Cylindrical Tank)
Internal Lox Properties
(One Torus Tank)
8.25m
NOTE:
The Lander’s base section is the same for the 30-Day Surface Hab, and IRSU plant

21. configuration specifics
(30-Day) Surface Facility Habitat
configuration specifics
Stowed Position
13.25m
Common Base Section of the Lander, IRSU and 30-Day Surface Hab
Inflated Surface Hab (Assumes the same technology as the Mars Trans Hab):
Total Inflated Volume: = 127m3
Head Room (Floor to Ceiling) = 2.5m
Max Inner Dia = 7.6m
Max Outer Dia = 8.0m
Stowed Dia = Same as Trans Hab

22. HOPE TransHab D8.0m Pressurized Empty Volume = 333m3 12.2m
Work Environment
Figure 3 – TransHab wrapped
with LH2 tanks
30.5cm shell thickness (average)
Figure 1 - Basic dimensions of the TransHab
Sleeping Quarters
Common/Entrainment Areas
Figure 2 - Concept for the
interior of the TransHab

23. Table 1 – List of storable and Habitual Volume per mission length
Table 2 – The left charts shows the mass breakdown for a 1 year mission and the Left chart shows
Space allotted to each system if all supplies were stored in the TransHab

24. Table 3 – The left charts shows the mass breakdown for a 2 year mission and the Left chart shows
Space allotted to each system if all supplies were stored in the TransHab
Table 4 – The left charts shows the mass breakdown for a 3 year mission and the Left chart shows
Space allotted to each system if all supplies were stored in the TransHab

25. Table 5 – The left charts shows the mass breakdown for a 4 year mission and the Left chart shows
Space allotted to each system if all supplies were stored in the TransHab
Table 6 – The left charts shows the mass breakdown for a 5 year mission and the Left chart shows
Space allotted to each system if all supplies were stored in the TransHab

26. A quick look at Mass Savings by grown food during the mission –
Please note this is only a first cut based off data from JSC 38672
Assumptions:
1) 1 year mission ECLSS mass is held constant for all missions (0% food grown on site). If all food is brought from Earth, missions longer than 1 year, require an additional storage area within or outside the current Trans Hab design. This extra storage space can be used for a BRLSS system that would also reduce the ECLSS recycling mass.
2) FAR Term Technology - Plant Chambers would provide a 25% ECLSS mass reduction for missions over one year. The 25% mass reduction also represents 50% in plant productivity in the 50 year time frame; the mass reduction can go a high as a 50% in ECLSS mass reduction if a 200% increase in plant productivity is assumed.
3) BRLSS Numbers are for 55% food grown in transit