Estimate the asymptotic efficiency of a rocket (or other launch vehicle - Saturn V, Delta, Ariane, Space Shuttle, whatever). A rough estimate would be ok.
As in: what proportion of the total chemical energy in the fuel at launch is ultimately converted into gravitational potential energy + kinetic energy of the launch vehicle/payload?
(To get that PE I expect you integrate Newton's Law of Gravitation, from ground to final altitude, using only the mass of the payload. To get the KE you need to know the final velocity components - is that radial and tangential to the earth orbit?)
For a bonus, what was the single biggest cause of inefficiency, and can you quantify it? (I think it is lifting your own fuel, followed by air resistance)
(I don't just mean the engine efficiency of the engine, I mean the whole deal.)
(Not sure where to put it - this question is a little chemistry, a little physics and a little astronomy)
2007-01-28
03:56:50
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1 answers
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asked by
smci
7