Consider a spacecraft in an elliptical orbit around the earth.At the low point, or perigee, of its orbit, it is 300km above theearth's surface; at the high point, or apogee, it is 2500km abovethe earth's surface.
A) What is the period of the spacecraft's orbit?
B) Using conservation of angular momentum, find the ratio of thespacecraft's speed at perigee to its speed at apogee.
C) Using conservation of energy, find the speed at perigee andthe speed at apogee.
Enter your answers numerically separated by a comma.
D) It is necessary to have the spacecraft escape from the earthcompletely. If the spacecraft's rockets are fired at perigee, byhow much would the speed have to be increased to achieve this?
E) What if the rockets were fired at apogee?
