A satellite is launched from the Kennedy Space Center in Florida, USA. The satellite is designed to go into an elliptical orbit around the Earth where the perigee of the orbit is at an altitude of 375 km and the apogee is at an altitude of 2000 km. a) What are the semiminor and semimajor axes of the orbit? b) What is the eccentricity of the orbit? c) What is the period of the orbit? d) What is the altitude of the satellite when the true anomaly angle is175o​​?

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