Article View: sci.space
Article #6666Re: SSTO vs 2 stage
From: Bruce Dunn
Date: Thu, 31 Dec 1992 03:35
Date: Thu, 31 Dec 1992 03:35
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> Paul Dietz writes:
>
> The mass ratio on an airliner is much less than in a launcher with
> chemical rocket propulsion, for rather fundamental reasons. It is
> therefore not inconceivable that multistage launchers would be
> appropriate even though multistage aircraft are not.
If the delta V needed to get to orbit were only 5000 meters per
second rather than the 9000+ meters per second which we have to deal with, we
would never be having this discussion. No-one would think of building a two
stage rocket. Clearly, the Earth is no place for a space-faring
civilization. Time to move to Mars :-)
--
Bruce Dunn Vancouver, Canada Bruce_Dunn@mindlink.bc.ca
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Newsgroups: sci.space Path: arc1-ca.pugleaf.net!sparky!uunet!cs.utexas.edu!zaphod.mps.ohio-state.edu!magnus.acs.ohio-state.edu!usenet.ins.cwru.edu!agate!rsoft!mindlink!a752 From: Bruce_Dunn@mindlink.bc.ca (Bruce Dunn) Subject: Re: SSTO vs 2 stage Organization: MIND LINK! - British Columbia, Canada Date: Thu, 31 Dec 1992 03:35:22 GMT Message-ID: <19046@mindlink.bc.ca> Sender: news@deep.rsoft.bc.ca (Usenet) Lines: 18