(adsbygoogle = window.adsbygoogle || []).push({}); 1. The problem statement, all variables and given/known data

A single-stage rocket is fired from rest from a deep-space platform, where gravity is negligible.

If the rocket burns its fuel in a time of 50.0 s and the relative speed of the exhaust gas is v_ex=2100 m/s, what must the mass ratio m_{0}/m be for a final speed v of 8.00 km/s (about equal to the orbital speed of an earth satellite)?

2. Relevant equations

v-v0= -v_exln(m/m0) = v_exln(m0/m)

3. The attempt at a solution

having a rough time understanding the equation, any tips or hints?

Any help would be greatly appreciated.

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# Mass Ratio Question

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