Calculate magnitude of required dv and change in flight path

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Reference no: EM131013455

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 q ¼ 1000. Calculate the magnitude of the required Dv and the change in flight path angle Dg.

Reference no: EM131013455

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