Consider a spacecraft in an elliptical orbit around the Earth.At the perigee it is 400 km away from the earth's surface; at theapogee ut us 4000 km above the earth's surface.
a.) What is the period of the spacecraft's orbit?
b.) Using conservation of angular momentum, find the ration ofthe spacecraft's speed at the perigee to its speed at theapogee.
c.) Using conservation of energy, find the speed at theperigee and apogee.
d.) It is necessary to have the spavecraft escape from theearth completely. If the spavefraft's rockets are fired at theperigee, by how much would the speed have to be increased toachieve this? What if the rocketers were fired at the apogee? Whichpoint in the orbit is mroe efficient to use?