Question

consider a spacecraft in an elliptical orbit around the earth. At the low point, or perigee, of its orbit, it is 300 km above the earth's surface; at the high point or apogee, it is 2500 km above the earth's surface.

Part A: find ratio of the spacecraft's speed at perigee to its speed at apogee?

(V_perigee / V_{apogee) = .....}

Part B: find the speed at the apogee?

V apogee = ........ m/s

Part C: find speed at perigee?

V perigee = ..... m/s

(lots of people wrong this question so please help me this question because I only have 1 left of mastering, thanks)

Answer 1

To calculate the speed from at Perigee,

Similarly, to calculate the speed at apogee,

Where,

G is the gravitational field strength and M, is the mass of the Earth.

On substituting the value, we can get the value of and are the speed at perigee and apogee.

Once, these values are obtained, we can get to know the ratio.