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

30MWe Brayton/VASIMR next to the ISS

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 + 0.37  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

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

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)

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

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

10MWe Brayton/MPD next to the ISS

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

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

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

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

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)

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 + 0.37  Total VASIMR Alpha = 0.76kg/kWe (Engine = 0.24kg/kWe, PPU = 0.52kg/kWe) Dry Mass = 368MT Propellant Capability = 150MT Payload Masses = 105MT

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 10-13 MT at 6-8kg/m2. estimate is based on using an overall efficiency of 50% for the VASIMR engine

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

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 = 18962 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

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

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

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

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

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

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

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

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

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