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Recently I've come across the proposal for the "Scorpion" spacecraft -- I originally ran across it on Project Rho (ctrl-F for it) but it looks like the article was published in the journal of the British Interplanetary Society.

I'm skeptical of the wisdom of the overall design (which is somewhat non-modular and go-everywhere, the author really wants to make a spaceship) and this question isn't about that but the engine is pretty interesting to me.

The engine uses a moderate-performance solid core nuclear reactor to heat propellant and also to drive a heat-engine (it appears that the heating of the cryogenic hydrogen propellant is part of the heat sink for this heat engine), and the heat engine output is then used to inject further energy into the propellant via an arcjet.

(image is fig 10 from the paper) enter image description here

If you believe the author, this gives you a rocket with nuclear-lightbulb-like performance (1200 ISP), the ability to use the reactor for both propulsion and electric power, and a much less radical reactor design than an NTR, while having much greater thrust and less radiators (and less dependence on alpha) than a typical nuclear electric rocket.

The question is whether one should believe the author.

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As with any hypothetical design, one is limited to consider if it's making some "unreasonable" assumptions.

First, one may compare the claimed performance to existing technology. Nuclear rockets were abandoned early, but the completed prototypes give some lower bound for what's possible (NERVA, RD-0410).

  • Thrust: 2000 kN (NERVA 247 kN, RD-0410 35 kN)
  • Isp: 1200s (NERVA 840s, RD-0410 910s)
  • Mass: 40 tons (NERVA 18 tons, RD-0410 2 tons).

This isn't wishfully far from demonstrated capability, and importantly, it doesn't assume the increased thrust and exhaust velocity can be achieved on an equal mass budget, instead listing the system as bulkier.

As for "much greater thrust and less radiators (and less dependence on alpha) than a typical nuclear electric rocket", this is conceptually possible, as waste heat can be dumped into the hydrogen instead of requiring additional radiators. The obvious cost of the increased thrust and reduced cooling requirements is wastly inferior exhaust velocity compared to other electrical propulsion types.

The core idea, however, consists of two parts with wildly different technological readiness. Separating reactor from propulsion.

  1. The reactor, being separate, can use conventional reactor technology, as thus has drastically fewer design constraints. This looks like a massive realism bonus to me.
  2. This makes an "arc heater" necessary.

2.) Is problematic. It's essentially the "magic device" that enables the whole system, and the author spends a single paragraph describing it!

The electrical energy produced by the latter is then used to power arc heaters in the exhaust system. This augmentation heating of the hydrogen raises the effective exhaust velocity well beyond the 8 km/sec that could be expected from a conventional nuclear thermal engine, to above 12.5 km/sec

No details whatsoever, except that it's somehow better than nuclear thermal engines.

As far as I know, nothing even close to this kind of gigawatt scale electrical heater has been demonstrated for rocket propulsion. Not surprising, since the current available power in space is typically 5 to 6 orders of magnitudes lower.

The available literature about this magic space heater doesn't seem to be large:

Scorpion’s main propulsion system is a version of the Serpent engine cycle devised by Alan Bond. The cycle uses electrical augmentation of a nuclear thermodynamic rocket; a basic concept that goes back to at least Goldsmith in 1959 [23]. The third edition of Sutton [24] devotes a paragraph to the idea, citing Goldsmith, and also Berry [25] and Rester and Rott [26]. Later editions of Sutton removed this paragraph, presumably to make room for more detailed discussion of the NERVA development work that had been undertaken between editions. But the concept was not forgotten and in 1972 Bond outlined a detailed, elegant and realisable variant on this basic principle [27]

  1. M. Goldsmith, “Augmentation of Nuclear Rocket Specific Impulse through Mechanical-Electric Means,” American Rocket Society Journal, Vol 29-8, pp 600-601, 1959.
  2. G. P. Sutton, Rocket Propulsion Elements, 3rd Edition, John Wiley, 1963.
  3. E. R. Berry, “Effects of Electrical Augmentation of Nuclear Rocket Flight Performance,” American Rocket Society Journal. Vol 31-1, pp 92-94 1961.
  4. E.L. Resler and N. Rott, “On Rocket Propulsion with Nuclear Power”, American Rocket Society Paper 1201-60.
  5. A. Bond, “A Nuclear Rocket for the Space Tug”, JBIS. Vol 25 pp 625-641, Nov 1972.

A paragraph that got removed in later editions, and small stubs at 2-3 pages is not much to go after. Perhaps Bond's outline contains something? Because there's is nothing of substance this paper about how the engine works, only what kind of spaceship you could build around such an engine.

The question is whether one should believe the author.

About the engine's potential applied use? Perhaps, at least he's made some pages about it.

About the engine's design, workings, theoretical foundation, parameters and performance? Not so much, since there's almost nothing said about it.

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    $\begingroup$ Alan Bond, the engine designer, has worked both for Rolls Royce testing a hydrolox engine, and the UK Atomic Energy Authority on fusion power. This of course in addition to the years of work for SABRE, which uses cooling loop driven turbines, so he's not a complete amateur. Whether any of his non-traditional engines work off the paper remains to be seen. (testing should begin next year) $\endgroup$
    – user20636
    Sep 2 '20 at 11:00
  • $\begingroup$ There can be little doubt that an arc can achieve high temperatures; damage to the electrode points being the limiting factor (maybe these are consumable). Thus separating the power generation (reactor) from propulsion (arc) allowing manageable reactor temperatures seems sound. Perhaps the power could be routed to an ion beam generator for higher Isp (but lower thrust) $\endgroup$ Sep 2 '20 at 15:58
  • $\begingroup$ Following the Project Rho site, the radiation shielding to 1 Rem/hour is a bit sketchy ... the LD50 is about 3 weeks of reactor time. That'll need some improvement. $\endgroup$ Sep 2 '20 at 16:11
  • $\begingroup$ how many hours of thrust is a misson likely to need @BrianDrummond $\endgroup$
    – user20636
    Sep 4 '20 at 9:16

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