Answered: 6.25 An earth satellite has a perigee… | bartleby

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6.25 An earth satellite has a perigee altitude of 1270 km and a perigee speed of 9 km/s. It is required to
change its orbital eccentricity to 0.4, without rotating the apse line, by a delta-v maneuver at
0 = 100°. Calculate the magnitude of the required Av and the change in flight path angle Ay.
(Ans.: ||Av|| = 0.915 km/s; Ay = -8.18°)

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