Nuclear salt-water rocket

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A nuclear salt-water rocket (NSWR) is a theoretical type of nuclear thermal rocket which was designed by Robert Zubrin.[1] In place of traditional chemical propellant, such as that in a chemical rocket, the rocket would be fueled by salts of plutonium or 20 percent enriched uranium. The solution would be contained in a bundle of pipes coated in boron carbide (for its properties of neutron absorption). Through a combination of the coating and space between the pipes, the contents would not reach critical mass until the solution is pumped into a reaction chamber, thus reaching a critical mass, and being expelled through a nozzle to generate thrust.[1]

Proposed design[edit]

Orthodox chemical rockets use heat energy produced by chemical reactions in a reaction chamber to heat the gas products. The products are then expelled through a propulsion nozzle at a very high speed, creating thrust.[2] In a nuclear thermal rocket (NTR), thrust is created by heating a fluid by using a nuclear fission reactor. The lower the molecular weight of the exhaust, hydrogen having the lowest possible, the more efficient the motor can be. However, in this engine the propellant can be anything with suitable properties as there will be no reaction on the part of the propellant.[3] In an NSWR the nuclear salt-water would be made to flow through a reaction chamber and out an exhaust nozzle in such a way and at such speeds that critical mass will begin once at the chamber is filled to a certain point, however, the peak neutron flux in the fission reaction would occur outside the vehicle.[1]

Advantages of the design[edit]

There are several advantages relative to conventional NTR designs. As the peak neutron flux and fission reaction rates would occur outside the vehicle, these activities could be much more vigorous than they could be if it was necessary to house them in a vessel (which would have temperature limits due to materials constraints).[1] Additionally, a contained reactor can only allow a small percentage of its fuel to undergo fission at any given time, otherwise it would overheat and meltdown (or explode in a runaway fission chain reaction).[4] The fission reaction in an NSWR is dynamic and because the reaction products are exhausted into space it doesn't have a limit on the proportion of fission fuel that reacts. In many ways this makes NSWRs like a hybrid between fission reactors and fission bombs.[1]

Due to their ability to harness the power of what is essentially a continuous nuclear fission explosion, NSWRs would have both very high thrust and very high exhaust velocity, meaning that the rocket would be able to accelerate quickly as well as be extremely efficient in terms of propellant usage. Such an engine being able to produce both high thrust and high ISP is a very rare trait in the rocket world, owing to the possibility to use a low density propellant such as hydrogen.[5] One design would generate 13 meganewtons of thrust at 66 km/s exhaust velocity (compared to ~4.5 km/s exhaust velocity for the best chemical rockets of today).

The design and calculations discussed above are using 20 percent enriched Uranium salts, however, it would be plausible to use another design which would be capable of achieving much higher exhaust velocities (4,700 km/s) and use 2,700 tonnes of highly enriched uranium salts in water to propel a 300 tonne spacecraft up to 3.6% of the speed of light.[1]

"NSWRs share many of the features of Orion propulsion systems, except that NSWRs would generate continuous rather than pulsed thrust and may be workable on much smaller scales than the smallest feasible Orion designs (which are generally large, due to the requirements of the shock-absorber system and the minimum size of efficient nuclear explosives)."[6]

Limitations[edit]

The propellant used in the initial design would contain a rather large amount of the relatively expensive isotope 235U, which would not be very cost effective. However, if the use of NSWR began to rise, it would be possible to replace this with the cheaper isotopes 233U or 239Pu in either fission breeder reactors or (much better) fusion/fission hybrid reactors. These fissiles would have the right characteristics to serve nearly equally as well, while having the boon of coming at a relatively low cost.[1][7]

Another major limitation of the nuclear salt water rocket design by Robert Zubrin included the lack of a material to be used in the reaction chamber that could actually sustain such a reaction within a spacecraft. Zubrin claimed in his design that the apparatus was created so that the liquid flow rate or velocity was what mattered most in the process, not the material. Therefore, he argued that if the proper velocity was chosen for the liquid traveling through the reaction chamber, the site of maximum fission release could then be located at the end of the chamber, thus allowing the system to remain intact and safe to operate. These claims have still not been proven due to no test of such a device having ever been conducted.[8]

For example, Robert Zubrin argues that if diluted nuclear fuel flows into the chamber at speed similar to diffusion speed of thermal neutrons, then nuclear reaction is confined in the chamber and does not damage the rest of the system (It is a nuclear analog of gas burner). Possible problem in that line of thinking could be the fact that neutrons do not all diffuse at the same (average) velocity, but has rather broad distribution over several orders of magnitude. It is quite possible that tails of this velocity distribution would be sufficient to generate enough heat in fuel feeding system (by scattering and fission) to destroy the system.[citation needed] This question can be perhaps answered by detailed Monte-Carlo simulations of neutron transport.

The vessel's exhaust would contain radioactive isotopes, but in space these would be rapidly dispersed after travelling only a short distance; the exhaust would also be travelling at high speed (in Zubrin's scenario, faster than Solar escape velocity, allowing it to eventually leave the Solar System). This is however of little use on the surface of a planet, where a NSWR would eject massive quantities of superheated steam, still containing fissioning nuclear salts. Terrestrial testing might be subject to reasonable objections; as one physicist wrote, "Writing the environmental impact statement for such tests [...] might present an interesting problem ..."[9] It is also not certain that fission in a NSWR could be controlled: "Whether fast criticality can be controlled in a rocket engine remains an open question".[10]

See also[edit]

References[edit]

  1. ^ a b c d e f g R. Zubrin (1991). "Nuclear Salt Water Rockets: High Thrust at 10,000 sec ISP" (PDF). Journal of the British Interplanetary Society. 44: 371–376. 
  2. ^ Angelin, Marcus; Rahm, Martin; Gabrielson, Erik; Gumaelius, Lena (Aug 17, 2012). "Rocket Scientist for a Day: Investigating Alternatives for Chemical Propulsion". Journal of Chemical Education. 89: 1301–1304. Bibcode:2012JChEd..89.1301A. doi:10.1021/ed200848r. 
  3. ^ Babula, Mariah. "Nuclear Thermal Rocket Propulsion". NASA.gov. NASA Space Propulsion and mission analysis office. Retrieved May 1, 2016. 
  4. ^ Hasegawa, Koichi (March 2012). "Facing Nuclear Risks: Lessons from the Fukushima Nuclear Disaster". International Journal of Japanese Sociology. 21 (1): 84–91. doi:10.1111/j.1475-6781.2012.01164.x. 
  5. ^ Braeunig, Robert. "Rocket Propulsion". braeunig.us. Retrieved May 1, 2016. 
  6. ^ Dr. David P. Stern (19 November 2003). "Far-out Pathways to Space: Nuclear Power". From Stargazers to Starships. Retrieved 14 November 2012. 
  7. ^ Kang, Jungmin; von Hippel, Frank N. (2001). "U-232 and the ProliferationResistance of U-233 in Spent Fuel". Science and Global Security. 9: 1–32. doi:10.1080/08929880108426485. 
  8. ^ "Alternate View Column AV-56". www.npl.washington.edu. Retrieved 2017-04-18. 
  9. ^ John G. Cramer (December 1992). "Nuke Your Way to the Stars (Alternate View Column AV-56)". Analog Science Fiction and Fact. Retrieved 2012-03-07. 
  10. ^ Dr. Ralph L. McNutt Jr. (31 May 1999). "A Realistic Interstellar Explorer" (PDF). Phase I Final Report NASA Institute for Advanced Concepts. Retrieved 14 November 2012.