zvoldahl8349 zvoldahl8349

14-10-2022
Physics

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the altitude of a satellite in an elliptical orbit around the earth is 2000 km at apogee and 500 km at perigee. determine a) the eccentricity of the orbit; b) the orbital speeds at perigee and apogee(km/s); and c) the period of the orbit(minutes).

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