Tsien, H. S. (1953) Take-Off from Satellite Orbit. Journal of the American Rocket Society, 23 (4). pp. 233-236. ISSN 0095-9073 http://resolver.caltech.edu/CaltechAUTHORS:20091215-133451765
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The mass ratio or the characteristic velocity for the take-off of a space ship from the satellite orbit is computed for two cases: the radial thrust, and the circumferential thrust. The circumferential thrust is much more efficient in that the required mass ratio is much less than for the radial thrust. Both cases show, however, an increase of the required mass ratio and the characteristic velocity with a reduction in acceleration. With circumferential thrust, the characteristic velocity increases by a factor of two, when the acceleration is reduced from 1/2 g to 1/3000 g.
|Additional Information:||(Reprinted from Journal of the American Rocket Society, July-August, 1953) Copyright, 1953, by the American Rocket Society, Inc., and reprinted by permission of the copyright owner. Received November 19, 1952.|
|Group:||Guggenheim Jet Propulsion Center|
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|Usage Policy:||No commercial reproduction, distribution, display or performance rights in this work are provided.|
|Deposited By:||George Porter|
|Deposited On:||15 Dec 2009 23:04|
|Last Modified:||26 Dec 2012 11:39|
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