Question

Ion-propulsion rockets have been proposed for use in space. They employ atomic ionization techniques and nuclear energy sources to produce extremely high exhaust velocities, perhaps as great as 8.00×10^6m/s. These techniques allow a much more favorable payload-to-fuel ratio. To illustrate this fact: (a) Calculate the increase in velocity of a 20,000-kg space probe that expels only 40.0-kg of its mass at the given exhaust velocity. (b) These engines are usually designed to produce a very small thrust for a very long time the type of engine that might be useful on a trip to the outer planets, for example. Calculate the acceleration of such an engine if it expels4.50×10^-6kg/sat the given velocity, assuming the acceleration due to gravity is negligible.

The problem is asking for us to find the increase in velocity of
the rocket. The exhaust velocity is related to rocket and the mass.
It is also asking us to find the vertical acceleration. The answers
should be completed in m/s and m/s^{2}.

What are the governing principles for this problem? What equations can I use to describe

what is happening here?

Self-Correct. How can I check if the answer is correct? Are there other equations I could have used that should yield the same answer? Do the units work out correctly?

Answer #1

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