consider a spacecraft in an elliptical orbit around the earth. At the low point, or perigee,...

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Physics

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

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

(Vperigee / Vapogee) = .....

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 & Explanation Solved by verified expert
3.9 Ratings (425 Votes)
Part A The ratio of spacecrafts speed at perigee to its speedat apogee which will be given by Vperigee Vapogee Ra RE Rp REVperigee Vapogee 2500 km    See Answer
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