Power for an Orbital Maneuver

Question

A satellite of mass $$m$$ is in a stable circular orbit of radius $$r$$ around a planet of mass $$M$$. The orbital radius is slowly increased at a rate of $$dr/dt$$, such that the orbit remains nearly circular. Which of the following expressions represents the power required to sustain this change in orbital radius?

Accepted Answer

$$P = \frac{GMm}{2r^2} \frac{dr}{dt}$$

Answer

$$P = -\frac{GMm}{2r^2} \frac{dr}{dt}$$

Answer

$$P = \frac{GMm}{4r^2} \frac{dr}{dt}$$

Power for an Orbital Maneuver

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