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

(I only have 1 try left in mastering please help me thanks)

Answer 1

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