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The orbit for an earth-orbiting satellite has an eccentricity of 0.15 and a semi-major axis of 9000 km. Assume a mean value of 6371 km

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The orbit for an earth-orbiting satellite has an eccentricity of 0.15 and a semi-major axis of 9000 km. Assume a mean value of 6371 km for the earth's radius. At a given observation time during a south to north transit, the height above ground is measured as 2000 km. Find the corresponding true anomaly. Hint:Use the equation below r = a(1 e) 1 + ecos(v)

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