Fission-fragment rocket

Research

Rotating fuel reactor

A design by the Idaho National Engineering Laboratory and Lawrence Livermore National Laboratory 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

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. 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 I_sp 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 I_sp, or even 40 kN at 5,000 seconds I_sp.

Am-242m as nuclear fuel

In 1987, Ronen & Leibson 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 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. 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.

^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. 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.

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. Proliferation resistance of ^242mAm was reported by Karlsruhe Institute of Technology 2008 study.

In 2000, Carlo Rubbia at CERN further extended the work by Ronen and Chapline on fission-fragment rocket using ^242mAm as a fuel. Project 242 based on Rubbia design studied a concept of ^242mAm based Thin-Film Fission Fragment Heated NTR 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. 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.

Aerogel core

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.