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Physics, 22.04.2020 23:24 charlesgtro7066

An earth satellite is in an elliptical orbit of eccentricity 0.3 and angular momentum 60,000 km2 /s. Find the delta-v required for a 90o change in inclination at apogee (no change in speed)

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An earth satellite is in an elliptical orbit of eccentricity 0.3 and angular momentum 60,000 km2 /s....
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