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Lecture L16 - Central Force Motion - MIT OpenCourseWare

Example Elliptical Orbits Consider a satellite launched from an altitude d above the earth’s surface, with velocity v c = µ/(R + d). If the direction of the velocity is orthogonal to the position vector, the trajectory will clearly be a circular orbit of radius R + d.

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Transcription of Lecture L16 - Central Force Motion - MIT OpenCourseWare

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