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At time to, the position and velocity of an earth-orbiting satellite at a given instant are r = 9000i + 10000j + 6000k km

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At time to, the position and velocity of an earth-orbiting satellite at a given instant are r = 9000i + 10000j + 6000k km v = 4i + 3j - 3k km/sec where i, j, and k are the orthogonal unit vectors that define the earth-centered inertial (ECI) coordinate system. Find the orbital elements.

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