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22.033 Final Design Presentation

22.033 Final Design Presentation. Vasek Dostal Knut Gezelius Jack Horng John Koser Joe Palaia Eugene Shwageraus And Pete Yarsky With the Help of Kalina Galabova Nilchiani Roshanak Dr. Kadak. Our Vision. Use nuclear technology to get people from Earth to Mars and back. Outline.

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22.033 Final Design Presentation

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  1. 22.033 Final Design Presentation

  2. Vasek Dostal Knut Gezelius Jack Horng John Koser Joe Palaia Eugene Shwageraus And Pete Yarsky With the Help of Kalina Galabova Nilchiani Roshanak Dr. Kadak

  3. Our Vision Use nuclear technology to get people from Earth to Mars and back 22.033, Mission to Mars

  4. Outline • Mission plan • Decision methodology • Space power system • Surface power system • Conclusions 22.033, Mission to Mars

  5. Mission Plan Summary • Precursor 1 • Telecommunication nuclear powered satellite in Mars orbit • Precursor 2 • ISRU and surface nuclear reactor demonstration / Sample Return • Manned Missions • Establish the infrastructure • Send the people • Bring them back 22.033, Mission to Mars

  6. Mars Nuclear Telecom Satellite • Primary Objectives • Validate space reactor system • Validate nuclear electric propulsion system • Provide high data rate communications. • Increases science yield. In space, power is knowledge. • Secondary Objectives • Orbital video and hi-res pictures. • High power Mars orbit experiments (active radar, etc.) 22.033, Mission to Mars

  7. ISRU & Surface Reactor Demo / Sample Return • Primary Objectives: • Validate Mars surface reactor technology • Validate Mars surface ISRU • Secondary Objectives • Produce fuel for sample return • Return Martian rocks to Earth 22.033, Mission to Mars

  8. Mars Infrastructure • Launch Window 1 • Launch 2 Nuclear Powered Transfer Systems • Launch first Earth Return Vehicle • Launch first set of surface Infrastructure • ERV waits in Mars Orbit • Reactor deployed, ascent stage fueling begins • Transfer Systems return to Earth for reuse 22.033, Mission to Mars

  9. Manned Exploration • Launch Window 2 • Refuel all 3 Transfer Systems (sitting in LEO) • Launch 2nd ERV & Surface Infrastructure • Launch Transit/Surface Hab • Crew1 meet Hab in HEO • Crew Lands near existing infrastructure • Transfer Systems return to Earth for reuse 22.033, Mission to Mars

  10. Manned Exploration • Launch Window 3 • Crew Meets ERV in Mars Orbit, return. • More infrastructure sent to Mars. • Second Crew Deployed. • This Plan is similar to NASA’s Design Reference Mission, but modified to take advantage of Nuclear Electric Propulsion. 22.033, Mission to Mars

  11. Electric Propulsion Options Precursor cargo missions Array of advanced Ion / Hall thrusters 22.033, Mission to Mars

  12. Variable Specific Impulse Magnetoplasma Rocket – VASIMR - Electric Propulsion (Manned) 10 MW of power 22.033, Mission to Mars

  13. Space Power Goals • Low mass • <3 kg/kWe • Scalable • 200-4000 kWe • Simple and reliable • No moving parts • Multiple round trips 22.033, Mission to Mars

  14. Space Power Unit • High temperature heat rejection • Reduces the radiator size • Thermo Photo Voltaic cells • High efficiency power conversion (up to 40%) • No moving parts • Molten salt coolant • High temperature, low pressure coolant • Good heat transport medium • Ultra-compact high power density reactor 22.033, Mission to Mars

  15. ANDIE Advanced Nuclear Design for Interplanetary Engine • Molten salt transfers the heat from the core to the radiator • All power is radiated towards TPV collector • TEM self powered pumps circulate the molten salt coolant • TPV collectors generate DC from thermal radiation • Residual heat is dissipated into outer space 22.033, Mission to Mars

  16. ANDIE Core Physics Power 11 MWth Dimensions 202020cm Total mass 185 kg Reflector thickness 6 cm (Zr3Si2) Coolant, molten salt (50:50 NaF-ZrF4) Fuel, RG Pu carbide, honeycomb plates keff BOL = 1.1 Core lifetime 570 FPD 22.033, Mission to Mars

  17. Honeycomb Fuel

  18. ANDIE Core Layout

  19. ANDIE Thermal Hydraulics • Fuel centerline temperature 1767K • Core inlet temperature 1550K • Core outlet temperature 1600K • Core mass flow rate 249.81 kg/s • Plate spacing 5.5 mm • Plate thickness 2.05 mm • Pressure drop 123 kPa • Pumping power 11.89 kW (40 kWe) 22.033, Mission to Mars

  20. Internal Radiator • Radiates 10MW towards TPV collectors • TPV collectors generate 4 MWe (η=40%) • Operates at 1575K temperature • Annular U-tube design 39/35mm outer/inner diameter • Made of titanium (w/ high emissivity coating) • U-tube height 15 m • Radiator weight 2967 kg • Molten salt weight 1975 kg 22.033, Mission to Mars

  21. Pumps • TEM pumps from SP-100 program • Thermoelectric Electromagnetic Pump • Self powered • Self starting • Self regulating • No moving parts • 10 year operating life • Designed to operate at 1310-1350K • Available operating experience 22.033, Mission to Mars

  22. mR/hr Radiation Detector Ĵo = 8.752 x 1013 n/cm2 s W LiH W R a d i a t o r Shielding ANDIE Neutron Moderation and Absorption: LiH Gamma Attenuation: W 22.033, Mission to Mars

  23. How much does ANDIE weigh? 22.033, Mission to Mars

  24. Surface Power Goals • Sufficient power for all surface applications (i.e. ISRU, habitat etc.) • ~200 kWe 22.033, Mission to Mars

  25. Surface Reactor Decision Problem • 192 Possible Combinations • Neutron Spectrum: Thermal, Epithermal, Fast • Coolant: CO2, LBE • Reactor Fuel: UO2, UC, US, UN • Matrix Material: BeO, SiC, ZrO2, MgO • Fuel Geometry: Pin, Block • 4 Decision Options Formulated • Option 1: Epithermal, CO2, UO2, BeO, Block • Option 2: Fast, CO2, US, SiC, Block • Option 3: Fast, LBE, UC, Pin • Option 4: Thermal, CO2, UO2, BeO, Block 22.033, Mission to Mars

  26. Multi-Attribute Utility Theory 22.033, Mission to Mars

  27. Option 1: Epithermal, CO2, UO2, BeO, Block Option 2: Fast, CO2, US, SiC, Block Option 3: Fast, LBE, UC, Pin Option 4: Thermal, CO2, UO2, BeO, Block

  28. Surface Power System • Cooled by Martian atmosphere (CO2) • Insensitive to leaks • Shielded by Martian soil and rocks • Low mass • Hexagonal block type core • Slow thermal transient (large thermal inertia) • Epithermal spectrum • Slow reactivity transient • Low reactivity swing 22.033, Mission to Mars

  29. CADEC CO2 cooled Advanced Design for Epithermal Converter • Pressurized CO2 from atmosphere cools the core • Direct, closed, recuperated Brayton cycle for electricity production (ηnet~20%) 22.033, Mission to Mars

  30. CADEC Core Physics • Power 1 MWth • Dimensions L=160 cm, D=40 cm • 37 hexagonal blocks • Total mass 3800 kg • Reflector thickness 30 cm (BeO) • Coolant Martian atmosphere (CO2) • Fuel 20% enriched UO2 dispersed in BeO • keff BOL = 1.14 • Core lifetime >25 EFPY 22.033, Mission to Mars

  31. What does CADEC look like?

  32. CADEC Thermal Hydraulics • System pressure 480 kPa • Core inlet temperature 486 C • Core outlet temperature 600 C • Core mass flow rate 7.47 kg/s • Channel diameter 30 mm • Block flat-to-flat 63 mm • Film temperature difference 2.5 C • Pressure drop 25 kPa 22.033, Mission to Mars

  33. Shielding CADEC Core Martian soil Place for shutters 22.033, Mission to Mars

  34. Conclusions • Mission plan • Technology demonstration • Reliability assurance before people are committed • Long term, reusability strategy • Reduces recurring costs to future missions 22.033, Mission to Mars

  35. ANDIE: Innovations Molten salt coolant Very high temperature, low pressure Pre-rejection of heat at high temperature Small radiator mass TPV collector High efficiency conversion Ultra compact core Fast spectrum, RG PuC fueled Potentially reduced shield mass Conclusions 22.033, Mission to Mars

  36. Conclusions • CADEC Innovative features • Epithermal spectrum • Slow kinetics (maintains large βeff) • Enhanced conversion • Compromise between advantages of fast and thermal systems • CO2 coolant • Local resource • Resistant to leaks or ingress • Martian soil shield 22.033, Mission to Mars

  37. Conclusions • CADEC Brayton cycle • Acceptable efficiency (25%) • Open cycle - operation is challenging • Closed cycle - heat rejection is the weakest point of the design • Massive pre-cooler required OR • Required fan power is too high (reduces the efficiency to 20%) • The design requires further optimization 22.033, Mission to Mars

  38. Space Reactor Nuclear Design • Goals • Minimize reactor core mass and volume • Provide 11 MW of thermal power for 3  180 days round trips • Flat reactivity throughout lifetime • Controlled by out-of-core mechanisms • Thermal spectrum: Am242m • Small fuel mass • Requires moderator • Challenging to control Options explored Fast spectrum: LWR Grade Pu Ultra-compact and light Controlled by direct leakage Potential for positive reactivity feedback 22.033, Mission to Mars

  39. Space Reactor: Thermal Core Moderator Mass

  40. Space Reactor: Thermal Core kinf BOL

  41. CECR Description 22.033, Mission to Mars

  42. Core Physics: Unit Cell 22.033, Mission to Mars

  43. Core Physics: Whole Core (HOM.) 22.033, Mission to Mars

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