Consider a spacecraft in an elliptical orbit around the earth.
At the low point, or perigee, of its orbit, it is 300km above the
earth's surface; at the high point, or apogee, it is 2500km above
the earth's surface.
A) What is the period of the spacecraft's orbit?
B) Using conservation of angular momentum, find the ratio of the
spacecraft's speed at perigee to its speed at apogee.
C) Using conservation of energy, find the speed at perigee and
the...