Rotational Dynamics
Earth
Perigee
Example 15:
An artificial satellite is placed into an elliptical orbit about
the Earth. Telemetry data indicate that its point of closest
approach (called the perigee) is rp= 8.37.10° m Apogee --
from the center of the Earth, and its point of
greatest distance (called the apogee) is ra= 25.1. 10m A
from the center of the Earth.
The speed of the satellite at the perigee is vp = 8450 m/s.
Find its speed va at the apogee.
Reasoning: