2) An artificial satellite is launched from 12742 3000" 6000"- point B on the equator by its carrier rocket and inserted into an elliptical orbit with perigee altitude of 3000 km. If the apogee altitude is to be 6000 km, compute a) The necessary perigee velocity vp and the corresponding apogee velocity v4. b) The velocity at point C where the altitude of V satellite is 3500 km. P 3500 c) The period t for a complete orbit.

2) An artificial satellite is launched from 12742 3000" 6000"- point B on the equator by its carrier rocket and inserted into an elliptical orbit with perigee altitude of 3000 km. If the apogee altitude is to be 6000 km, compute a) The necessary perigee velocity vp and the corresponding apogee velocity v4. b) The velocity at point C where the altitude of V satellite is 3500 km. P 3500 c) The period t for a complete orbit.

University Physics Volume 1

18th Edition

ISBN:9781938168277

Author:William Moebs, Samuel J. Ling, Jeff Sanny

Publisher:William Moebs, Samuel J. Ling, Jeff Sanny

Chapter13: Gravitation

Section: Chapter Questions

Problem 79AP: Given the perihelion distance, p , and aphelion distance, q , for an elliptical orbit, show that the...

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