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Nuclear Thermal Propulsion Systems (Last Updated in January 2021) Eric PROUST Eric Proust

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Nuclear Thermal Propulsion Systems (Last Updated in January 2021) Eric PROUST Eric Proust Lecture Series on NUCLEAR SPACE POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems (Last updated in January 2021) Eric PROUST Eric Proust To cite this version: Eric Proust. Lecture Series on NUCLEAR SPACE POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems (Last updated in January 2021) Eric PROUST. Engineering school. France. 2021. hal-03147500 HAL Id: hal-03147500 https://hal.archives-ouvertes.fr/hal-03147500 Submitted on 19 Feb 2021 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. FROM RESEARCH TO INDUSTRY LECTURE SERIES ON NUCLEAR SPACE POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems Eric PROUST Commissariat à l’énergie atomique et aux énergies alternatives - www.cea.fr Last update: January 2021 Lecture Series on SPACE NUCLEAR POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems (last updated in January 2021) Eric PROUST Nuclear Space Power & Propulsion in the last 2 month news Nuclear Thermal Propulsion Nuclear Thermal Propulsion Nuclear Electric Propulsion Space Nuclear Power Reactor Lecture Series on SPACE NUCLEAR POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems (last updated in January 2021) Eric PROUST 2 Space Nuclear Power Systems: Radioisotope or Fission-based? Energy released by the radioactive decay Energy released by the neutron-induced fission (alpha) of a radioisotope of a fissile nuclide U-234 Neutron Neutrons (2,5) 5.5 MeV 190 MeV Pu-238 α (He-4) Fissile Nucleus (U-235) Product Nuclei U-235 (KE: 168 MeV) Applications: Applications: • Thermal management: RHU • Power generation , for supplying • Power generators: RTG , DIPS • A moon/mars base • Electric thrusters ( Nuclear Electric Propulsion : NEP ) • Direct propulsion (by heating a propellant gas) Today’s lecture • Nuclear Thermal Propulsion (NTP) • Both combined Lecture Series on SPACE NUCLEAR POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems (last updated in January 2021) Eric PROUST 3 Lecture Outline (1/2) u Why Nuclear Thermal Propulsion? - In-space propulsion principle; Nuclear Space Propulsion: Thermal or Electric; Space propulsion: some basics; Performances: NTP vs Chemical prop; NTP: enabler of manned missions to Mars? u The US Rover/NERVA Program (1956-1972) - 27 NTP rocket reactors and 3 nuclear engines ground tested; NERVA Rocket Engine Design; NERVA nuclear fuels; Program achievements; The program legacy engine concept: the SNRE u The USSR NTP Program (~1960-1989) - An effort comparable with the US, a full carbide fuel, a quite different design approach u Nuclear Fuels for NTP: Beyond Composite/Carbides Fuels, Cermet Fuels - NTP nuclear fuel design issues; W-UO 2 Cermet fuel developments in the 60’s; Cermet-fuel-based engine concepts: ANL 2000, ANL 200, XNR2000; Cermet vs. carbide fuels for NTP u The CEA-CNES MAPS Study Program (1994-1997) - Study goals; MAPS engine conceptual design; Safety issues for NTP; Development and ground testing approaches; The challenges of nowadays testing nuclear rocket engines u Current Orientations - Why waiting decades?; 2010: new goal of humans orbiting Mars by mid 30’s; NTP engines for manned Mars mission; current NASA project to assess the feasibility of an LEU-based engine; Impacts of switching from HEU to LEU fuel Lecture Series on SPACE NUCLEAR POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems (last updated in January 2021) Eric PROUST 4 Lecture Outline (2/2) And then, for you to choose one among 3 bonus presentations: #1 ‘’Advanced’’ Nuclear Thermal Propulsion Systems #2 Nuclear Pulse Space Propulsion Systems #3 Air-Breathing Nuclear Thermal Propulsion Lecture Series on SPACE NUCLEAR POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems (last updated in January 2021) Eric PROUST 5 In-Space Propulsion: Basic Principle Remember: it’s Newton’s 2 nd Law of Motion Liquid Chemical Rocket %&'()* = + ,+-. !"!#$ / 0 !+1 ! Ejected mass flow rate Velocity of ejected gases !"!#$ Ejected gases pressure at nozzle exit ! Nozzle exit area ! Lecture Series on SPACE NUCLEAR POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems (last updated in January 2021) Eric PROUST 6 Nuclear In-Space Propulsion: Can Be Thermal (NTP), or Electric (NEP) Nuclear Thermal Propulsion Nuclear Electric Propulsion Nuclear Power Subsystem Nozzle Nuclear Reactor Waste Heat Heat Spacecraft (low T) subsystems Electric power Propellant (H 2) Experiments & Spacecraft Subsystems Heat addition Lecture Series on SPACE NUCLEAR POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems (last updated in January 2021) ThrustersEric PROUST 7 In-Space Propulsion: some basics Launch mass (cost) exponentially decreases with HIJIKL 8 8 / FG HIJIKL 78 7, 2$3456$ = +,+ = + .!"!#$ + 7* 7* DE FG <>?@AB ; 9 78 = :+ .!"!#$ 9 +7, + For ‘’thermal’’ rocket engines (chemical, nuclear thermal) D <?@?C , : chamber temperature (K) c\]\$ V T+ aG = .!"!#$ +ln+ NO ST : molecular weight c^\]_` HIJIKL M+ U+ ef PO : QR U d = + g eD aG bHIJIKL \]\$ ^\]_` Specific Impulse: HIJIKL (Tsiolkowsky’s ‘’rocket equation’’) WXY+ PXR = + Z[ Lecture Series on SPACE NUCLEAR POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems (last updated in January 2021) Eric PROUST 8 Nuclear Thermal Propulsion: a ~Twice Higher Isp than Chemical Propulsion V NO ST WXY M + PO : QR U ð ð Chemical (LH 2 /LO 2) : M~13.8 g/mol, T ~3420 K ~480 s Nuclear Thermal (LH 2 propellant): M~2 g/mol, T ~2700 K ~900 s WXY+ WXY+ Thrust ~ 2 000 kN; burn time ~500 s; thrust/weight ~150 Thrust ~50 - 1 000 kN; burn time ~1 000 s; thrust/weight ~10 - 30 ‘’Energy-limited’’ performances (energy stored in chemical Performances limited by fuel resistance to high temperature H 2 bounds) Lecture Series on SPACE NUCLEAR POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems (last updated in January 2021) Eric PROUST 9 Space Propulsion: an example of the benefits of a twice higher Isp Example of Earth-Mars round trip : a twice higher XY+ ð reduces mass to put in LEO (cost) by a factor ~2 Mars Earth or ð enables to shorten manned round trip time (space radiation dose!) Sun = 480 s WXY+ Round trip low Earth orbit ó low Mars orbit: = 900 s minimum ΔV ~6 km/s WXY+ Chemical (Thermal) propulsion: ~480 s ð ΔV/ ~13 ð / ~3.7 WXY+ WXY+ UhihL Ujhikm Nuclear Thermal Propulsion: ~900 s ð ΔV/ ~6.7 ð / ~1.9 WXY + WXY + UhihL Ujhikm Lecture Series on SPACE NUCLEAR POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems (last updated in January 2021) Eric PROUST 10 Space Propulsion: another example of the benefits of a twice higher Isp (1/2) Manned Mission To Mars: ΔV budget vs. Transit Time / Radiation Dose * Annual Ambient Radiation Levels for the Earth, Mars and Space * Earth Mars Moon Space Annual Total 3 mSv 245 mSv 438 mSv 657 mSv Daily Average 8.2 10 -3 mSv 0.67 mSv 1.2 mSv 1.8 mSv Source: L. Joseph Parker, Human radiation exposure tolerance and expected exposure during colonization of the moon and Mars, 2016 2033 ''Fast conjunction'' Long Stay Mars Mission 30 Mission Total 25 Outbound 20 Inbound 15 (Poor) Shielding effectiveness against galactic cosmic radiation at solar minimum 10 Delta V budget (km/s) budget V Delta 5 0 60 90 120 150 180 210 ''one-way'' transit time to or from Mars (days) * See back-up slide Source: based on Borowski et al., Space 2013, AIAA-2013-5354 Lecture Series on SPACE NUCLEAR POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems (last updated in January 2021) Eric PROUST 11 Space Propulsion: another example of the benefits of a twice higher Isp (2/2) Mission mass ratios vs. transit time to Mars Mini : initial total mass of spacecraft in LEO (= Spacecraft mass + Payload mass + propellant mass ) aDbopq6r : \]\$ ^\]_` \]\$ 2033 ''Fast conjunction'' Long Stay Mars Mission 40 30 Chemical Propulsion Isp = 455 s 25 30 20 final Nuclear Thermal 20 15 / M / Propulsion init Isp = 910 s Mission M Total Delta V 10 10 5 Mission Total Delta V V (km/s) Delta Total Mission 0 Source (Delta V): Borowski et al., Space 2013, AIAA-2013-5354 0 60 90 120 150 180 210 "One-Way" Transit Time to and from Mars (days) Reminder: average space radiation level ~1.85 mSv/day Lecture Series on SPACE NUCLEAR POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems (last updated in January 2021) Eric PROUST 12 Nuclear Thermal Propulsion (NTP): enabler of manned missions to Mars? 2033 – 2045 opportunities For an detailed explanation of why, although EP has a much higher Isp, NTP outperforms NEP (and SEP), wait for my next lecture on Space Fission Power and Electric Propulsion The short explanation: electric thrusters have a very (very) low thrust * and they need Electric Propulsion: SEP : Solar a power supply NEP : Nuclear Source: B. G. Drake “Human Mars Mission Definition: Requirements & Issues”, Human 2 Mars Summit, 2013 * See back-up slide Lecture Series on SPACE NUCLEAR POWER & PROPULSION SYSTEMS -2- Nuclear Thermal Propulsion Systems (last updated in January 2021) Eric PROUST 13 The US Rover/NERVA program (1956-1972): 20 NTP rocket reactors designed, built and ground tested
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