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Rocket Propulsion

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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 2100 m/s, what must the mass ratio mo/m be for a final speed v of 8.00 km/s (about equal to the orbital speed of an earth satellite)?

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Following is the text part of the solution. Please see the attached file for complete solution. Equations, diagrams, graphs and special characters may not appear correctly here.

Let q be the rate at which the exhaust gas is emitted.

After a time t, the mass of the rocket is reduced by M - qt where M is the initial rocket mass.

At time t + dt, let the velocity of ...

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