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Fission-fragment rocket

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The fission-fragment rocket is a rocket engine design that directly harnesses hot nuclear fission products for thrust, as opposed to using a separate fluid as working mass. The design can, in theory, produce very high specific impulse while still being well within the abilities of current technologies.

Design considerations

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In traditional nuclear thermal rocket and related designs, the nuclear energy is generated in some form of reactor and used to heat a working fluid to generate thrust. This limits the designs to temperatures that allow the reactor to remain whole, although clever design can increase this critical temperature into the tens of thousands of degrees. A rocket engine's efficiency is strongly related to the temperature of the exhausted working fluid, and in the case of the most advanced gas-core engines, it corresponds to a specific impulse of about 7000 s.

The temperature of a conventional reactor design is the average temperature of the fuel, the vast majority of which is not reacting at any given instant. The atoms undergoing fission are at a temperature of millions of degrees, which is then spread out into the surrounding fuel, resulting in an overall temperature of a few thousand.

By physically arranging the fuel into very thin layers or particles, the fragments of a nuclear reaction can escape from the surface. Since they will be ionized due to the high energy of the reaction, they can then be handled magnetically and channeled to produce thrust. Numerous technological challenges still remain, however.

Research

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Rotating fuel reactor

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Fission-fragment propulsion concept
  1. fissionable filaments arranged in disks
  2. revolving shaft
  3. reactor core
  4. fragments exhaust

A design by the Idaho National Engineering Laboratory and Lawrence Livermore National Laboratory[1] uses fuel placed on the surface of a number of very thin carbon fibres, arranged radially in wheels. The wheels are normally sub-critical. Several such wheels were stacked on a common shaft to produce a single large cylinder. The entire cylinder was rotated so that some fibres were always in a reactor core where surrounding moderator made fibres go critical. The fission fragments at the surface of the fibres would break free and be channeled for thrust. The fibre then rotates out of the reaction zone to cool, avoiding melting.

The efficiency of the system is surprising; specific impulses of greater than 100,000 s are possible using existing materials. This is high performance, although the weight of the reactor core and other elements would make the overall performance of the fission-fragment system lower. Nonetheless, the system provides the sort of performance levels that would make an interstellar precursor mission possible.

Dusty plasma

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Dusty plasma bed reactor
  • A. fission fragments ejected for propulsion
  • B. reactor
  • C. fission fragments decelerated for power generation
  • d. moderator (BeO or LiH)
  • e. containment field generator
  • f. RF induction coil

A newer design proposal by Rodney L. Clark and Robert B. Sheldon theoretically increases efficiency and decreases complexity of a fission fragment rocket at the same time over the rotating fibre wheel proposal.[2] Their design uses nanoparticles of fissionable fuel (or even fuel that will naturally radioactively decay) of less than 100 nm diameter. The nanoparticles are kept in a vacuum chamber subject to an axial magnetic field (acting as a magnetic mirror) and an external electric field. As the nanoparticles ionize as fission occurs, the dust becomes suspended within the chamber. The incredibly high surface area of the particles makes radiative cooling simple. The axial magnetic field is too weak to affect the motions of the dust particles but strong enough to channel the fragments into a beam which can be decelerated for power, allowed to be emitted for thrust, or a combination of the two.

With exhaust velocities of 3% - 5% the speed of light and efficiencies up to 90%, the rocket should be able to achieve an Isp of over 1,000,000 seconds. By further injecting the fission fragment exhaust with a neutral gas akin to an afterburner setup, the resulting heating and interaction can result in a higher, tunable thrust and specific impulse. For realistic designs, some calculations estimate thrusts on the range of 4.5 kN at around 32,000 seconds Isp,[3] or even 40 kN at 5,000 seconds Isp.[4]

Am-242m as nuclear fuel

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In 1987, Ronen & Leibson [5][6] published a study on applications of 242mAm (an isotope of americium) as nuclear fuel to space nuclear reactors, noting its extremely high thermal cross section and energy density. Nuclear systems powered by 242mAm require less fuel by a factor of 2 to 100 compared to conventional nuclear fuels.

Fission-fragment rocket using 242mAm was proposed by George Chapline[7] at Lawrence Livermore National Laboratory in 1988, who suggested propulsion based on the direct heating of a propellant gas by fission fragments generated by a fissile material. Ronen et al.[8] demonstrate that 242mAm can maintain sustained nuclear fission as an extremely thin metallic film, less than a micrometer thick. 242mAm requires only 1% of the mass of 235U or 239Pu to reach its critical state. Ronen's group at Ben-Gurion University of the Negev further showed that nuclear fuel based on 242mAm could speed space vehicles from Earth to Mars in as little as two weeks.[9]

242mAm's potential as a nuclear fuel comes from the fact that it has the highest thermal fission cross section (thousands of barns), about 10x the next highest cross section across all known isotopes. 242mAm is fissile and has a low critical mass, comparable to 239Pu.[10][11] It has a very high cross section for fission, and is destroyed relatively quickly in a nuclear reactor. Another report claims that 242mAm can sustain a chain reaction even as a thin film, and could be used for a novel type of nuclear rocket.[8][12][13][14]

Since the thermal absorption cross section of 242mAm is very high, the best way to obtain 242mAm is by the capture of fast or epithermal neutrons in Americium-241 irradiated in a fast reactor. However, fast neutron reactors are not readily available. Detailed analysis of 242mAm production in existing PWRs was provided in.[15] Proliferation resistance of 242mAm was reported by Karlsruhe Institute of Technology 2008 study.[16]

In 2000, Carlo Rubbia at CERN further extended the work by Ronen[6] and Chapline[7] on fission-fragment rocket using 242mAm as a fuel.[17] Project 242[18] based on Rubbia design studied a concept of 242mAm based Thin-Film Fission Fragment Heated NTR[19] by using direct conversion of the kinetic energy of fission fragments into increasing of enthalpy of a propellant gas. Project 242 studied the application of this propulsion system to a crewed mission to Mars.[20] Preliminary results were very satisfactory and it has been observed that a propulsion system with these characteristics could make the mission feasible. Another study focused on production of 242mAm in conventional thermal nuclear reactors.[21]

Aerogel core

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On 9 January 2023, NASA announced funding the study of an "Aerogel Core Fission Fragment Rocket Engine", where fissile fuel particles will be embedded in an ultra-low density aerogel matrix to achieve a critical mass assembly. The aerogel matrix (and a strong magnetic field) would allow fission fragments to escape the core, while increasing conductive and radiative heat loss from the individual fuel particles.[22]

See also

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References

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  1. ^ Chapline, G.; Dickson, P.; Schnitzler, B. (18 September 1988). Fission fragment rockets: A potential breakthrough (PDF). International reactor physics conference. Jackson Hole, Wyoming, USA. OSTI 6868318.
  2. ^ Clark, R.; Sheldon, R. (10–13 July 2005). Dusty Plasma Based Fission Fragment Nuclear Reactor (PDF). 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Tucson, Arizona: American Institute of Aeronautics and Astronautics (published 15 April 2007). AIAA Paper 2005-4460.
  3. ^ Gahl, J.; Gillespie, A. K.; Duncan, R. V.; Lin, C. (2023-10-13). "The fission fragment rocket engine for Mars fast transit". Frontiers in Space Technologies. 4. arXiv:2308.01441. doi:10.3389/frspt.2023.1191300. ISSN 2673-5075.
  4. ^ Clark, Rodney; Sheldon, Robert (2005-07-10). "Dusty Plasma Based Fission Fragment Nuclear Reactor". 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. American Institute of Aeronautics and Astronautics. doi:10.2514/6.2005-4460. ISBN 978-1-62410-063-5.
  5. ^ Ronen, Yigal; Leibson, Melvin J. (1987). "An example for the potential applications of americium-242m as a nuclear fuel". Transactions – the Israel Nuclear Society. 14: V-42.
  6. ^ a b Ronen, Yigal; Leibson, Melvin J. (1988). "Potential applications of 242mAm as a nuclear fuel". Nuclear Science and Engineering. 99 (3): 278–284. Bibcode:1988NSE....99..278R. doi:10.13182/NSE88-A28998.
  7. ^ a b Chapline, George (1988). "Fission fragment rocket concept". Nuclear Instruments and Methods in Physics Research Section A: Accelerators, Spectrometers, Detectors and Associated Equipment. 271 (1): 207–208. Bibcode:1988NIMPA.271..207C. doi:10.1016/0168-9002(88)91148-5.
  8. ^ a b Ronen, Yigal; Shwageraus, E. (2000). "Ultra-thin 241mAm fuel elements in nuclear reactors". Nuclear Instruments and Methods in Physics Research A. 455 (2): 442–451. Bibcode:2000NIMPA.455..442R. doi:10.1016/s0168-9002(00)00506-4.
  9. ^ "Extremely Efficient Nuclear Fuel Could Take Man To Mars In Just Two Weeks". Science Daily (Press release). Ben-Gurion University of the Negev. 3 January 2001.
  10. ^ Dias, Hemanth; Tancock, Nigel; Angela, Clayton. "Critical Mass Calculations for 241Am, 242mAm and 243Am" (PDF). Aldermaston, Reading, Berkshire: Atomic Weapons Establishment plc. Archived from the original (PDF) on 22 July 2011. Retrieved 3 February 2011.
  11. ^ Ludewig, H.; et al. (1996). "Design of particle bed reactors for the space nuclear thermal propulsion program". Progress in Nuclear Energy. 30 (1): 1–65. doi:10.1016/0149-1970(95)00080-4.
  12. ^ Ronen, Y.; Raitses, G. (2004). "Ultra-thin 242mAm fuel elements in nuclear reactors. II". Nuclear Instruments and Methods in Physics Research Section A: Accelerators, Spectrometers, Detectors and Associated Equipment. 522 (3): 558–567. doi:10.1016/j.nima.2003.11.421.
  13. ^ Ronen, Yigal; Aboudy, Menashe; Regev, Dror (2000). "A Novel Method for Energy Production Using 242 m Am as a Nuclear Fuel". Nuclear Technology. 129 (3): 407–417. doi:10.13182/NT00-A3071.
  14. ^ Ronen, Y.; Fridman, E.; Shwageraus, E. (2006). "The smallest thermal nuclear reactor". Nuclear Science and Engineering. 153 (1): 90–92. doi:10.13182/NSE06-A2597.
  15. ^ Golyand, Leonid; Ronen, Yigal; Shwageraus, Eugene (2011). "Detailed Design of 242 m Am Breeding in Pressurized Water Reactors". Nuclear Science and Engineering. 168 (1): 23–36. doi:10.13182/NSE09-43.
  16. ^ Kessler, G. (2008). "Proliferation resistance of americium originating from spent irradiated reactor fuel of pressurized water reactors, fast reactors, and accelerator-driven systems with different fuel cycle options". Nuclear Science and Engineering. 159 (1): 56–82. doi:10.13182/NSE159-56.
  17. ^ Rubbia, Carlo (2000). Fission fragments heating for space propulsion (Report). No. SL-Note-2000-036-EET. CERN-SL-Note-2000-036-EET.
  18. ^ Augelli, M.; Bignami, G. F.; Genta, G. (2013). "Project 242: Fission fragments direct heating for space propulsion—Programme synthesis and applications to space exploration". Acta Astronautica. 82 (2): 153–158. doi:10.1016/j.actaastro.2012.04.007.
  19. ^ Davis, Eric W. (2004). Advanced propulsion study (Report). Warp Drive Metrics.
  20. ^ Cesana, Alessandra; et al. (2004). "Some Considerations on 242 m Am Production in Thermal Reactors". Nuclear Technology. 148 (1): 97–101. doi:10.13182/NT04-A3550.
  21. ^ Benetti, P.; et al. (2006). "Production of 242mAm". Nuclear Instruments and Methods in Physics Research Section A: Accelerators, Spectrometers, Detectors and Associated Equipment. 564 (1): 48–485. doi:10.1016/j.nima.2006.04.029.
  22. ^ Hall, Loura; Weed, Ryan (9 January 2023). "Aerogel Core Fission Fragment Rocket Engine". NASA. Retrieved 21 July 2024.
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