2.20 An unmanned satellite orbits the earth with a perigee radius of 10,000 km and an apogee radius of 100,000 km. Calculate: (a) the eccentricity of the orbit; (b) the semimajor axis of the orbit (km); (c) the period of the orbit (h); (d) the specific energy of the orbit (km2/s); (e) the true anomaly (degrees) at which the altitude is 10,000 km; (f) v, and vi (km/s) at the points found in part (e); (g) the speed at perigee and apogee (km/s). {Partial Ans.: (c) 35.66 h; (e) 82.26°; (g) 8.513 km/s, 0.8513 km/s}

2.20 An unmanned satellite orbits the earth with a perigee radius of 10,000 km and an apogee radius of 100,000 km. Calculate: (a) the eccentricity of the orbit; (b) the semimajor axis of the orbit (km); (c) the period of the orbit (h); (d) the specific energy of the orbit (km2/s); (e) the true anomaly (degrees) at which the altitude is 10,000 km; (f) v, and vi (km/s) at the points found in part (e); (g) the speed at perigee and apogee (km/s). {Partial Ans.: (c) 35.66 h; (e) 82.26°; (g) 8.513 km/s, 0.8513 km/s}

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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