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The earth orbit of a satellite is to be changed from a circle of radius 15 000 km to a collinear ellipse with perigee altitude of 500 km and apogee radius of 22000 km. Calculate the magnitude of the required delta-v and the change in the flight path angle Dg. What is the minimum total delta-v if the orbit change is accomplished instead by a Hohmann transfer?
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- boston614
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