A satellite in elliptical orbit has maximum speed v_max at perigee (closest) and minimum v_min at apogee. The ratio v_max/v_min equals (r_apogee/r_perigee):
A√(r_apogee/r_perigee)
Br_perigee/r_apogee
C1
Dr_apogee/r_perigee
Answer & Solution
Correct answer: D. r_apogee/r_perigee
Angular momentum conservation: m v_max r_perigee = m v_min r_apogee. So v_max/v_min = r_apogee/r_perigee. The satellite moves faster when closer to Earth.
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