Ryan Gosse, a bunch of Floridians, and Tony Colozza of NASA offered "Nuclear Wave Rotor Bi-Modal Cycle for In-Space Propulsion" in, I think, 2024 (pdf). They fill out "wave rotor" with "enhanced nuclear" to make the catchy 'cronym WREN. h/t ToughSF on Twitter 30 August who summarises: A wave rotor uses shockwaves to compress the exhaust of a nuclear thermal rocket to 4765 K, achieving 1430s Isp at 2.27 kW/kg, or turn a generator to feed 3000s Isp thrusters at 0.47 kW/kg
. The target is Mars(/Deimos).
Isp is, recall, really a measure of exhaust velocity, so just x9.8. NERVA-mode 14 km/s just like it says on Table 1 (page 15, relayed at ToughSF).
As we've learnt from ramjets, usually this much temperature melts ... everything. We again want liquid-scale results from a still-solid core. They're saying the WREN can use the shockwaves to keep the hydrogen plasma off the chassis, heat it even more (Boyle's Law, bitchez) and ram it out to that bespoke velocity. So an afterburner except not burning.
The NΘP mode instead offers 34.7 kN of thrust, twice the beryllium option of fusion pinch (also skiffy). Which does indeed put Mars into the frame.
The NΘP propulsion cycles
run a total irradiation time of only two days for a 45-day mission and less than 10 hours for a 65-day mission
. To follow that - I suppose - they... don't run. The assumption is a one-way mission, perhaps short enough they don't need to spin the wheel nor, one assumes, build to a wheel. At Mars, the areonauts find their own gravity until return.
The paper notes that pre-VASIMR, Isp had been chemical and rather unconstrained. The high impulse allowed by electric propulsion permitted variable propulsion, for mass savings over the trajectory burn
. Mass of propellant, that is; which means more for the mission, albeit likely to be taken by the NEP mode's own subsystems.
The paper must admit to wasting heat, defined as heat not going to propulsion. They hope to recover some of that as electricity: life support for the crew, or just filling up batteries (thus relieving strain on the radiators if nothing else). Once at Mars solar-cells get only, what, 43% flux and on Mars that's at high noon with no dust. That's for a later day.
Also deferred is the propulsion cycle, dependent on thrust/weight of the NΘP. The authors had touted the 10-48 hours as short
. Classical NERVA, for its 900s, aimed for 30m-2h of burn. WREN must settle on NΘP 8-15 hours. That's not so short; it's comparable to the issues identified with NTR to our own moon (that paper recommended LOX for a true afterburner, so "LANTR"). The WREN authors suggest they drop the NEP components to focus on thrust; this would jack up the time of the mission and maybe require that spinwheel after all.