An artificial satellite is launched from point \(B\) on the equator by its carrier rocket and inserted into an elliptical orbit with a perigee altitude of \(2000 \mathrm{~km}\). If the apogee altitude is to be \(4000 \mathrm{~km}\), compute

(a) the necessary perigee velocity \(v_{P}\) and the corresponding apogee velocity \(v_{A}\),

(b) the velocity at point \(C\) where the altitude of the satellite is \(2500 \mathrm{~km}\), and \((c)\) the period \(\tau\) for a complete orbit.

Transcribed Image Text:

A. R VAY B 2500 km P 4000 -2000 km 12 742 km km 2a