On Wed, 2 Jul 2003, Christopher England wrote:

> Ion propulsion is efficient but low in thrust (like ounces of force).
> Chemical propulsion will be needed for high thrust needs like fast
> orbital capture, landing and takeoff.

Chris, has anyone done an analysis to determine whether one could
produce a high-thrust ion engine "complex" using nanotech?  An
analysis of nanotechnology based engines (non-ion) for air-cars [1]
seems to suggest they would be much more efficient than engines
based on current technology.  What do we know about nanotech based
ion-tech?

My guess would be that there would be significant gains in thrust
due to multiple micro-engines but that this might be limited due to
things like voltage and insulator constraints.

I also suspect that your comments regarding radiator limitations
and the need for refractory metals may be somewhat "current
technology" based.  See [2].  We are not close to the limits
of cooling technology at this time.  If one can improve the
cooling technology, one might be able to run the reactor somewhat
hotter without risking a meltdown and as a result increase
thermodynamic energy conversion efficiency.

Interestingly, if one wants a cooling system with the highest
temperature tolerance, the substances one would prefer to make
it out of would seem to be (a) Hafnium carbide; (b) Tantalum carbide;
(c) Tungsten or if one wants something a bit less expensive perhaps
Titanium carbide.  So refractory metals would seem not to be strictly
necessary.

Robert

1. Hall, J. S., "Molecular Manufacturing and the Private Aircar",
   http://discuss.foresight.org/%7Ejosh/aircar/
   See esp. "Engines power-to-weight ratio".

2. Henson, H. K., and K. E. Drexler. (1988) Heterodensity heat
   transfer apparatus and method.  U.S. Patent Office: #4,759,404
   Discussed in some more detail in: Drexler, K. E., "Nanosystems",
   J. Wiley & Sons, New York (1992) esp. Section 11.5, pgs 330-332.

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