Final answer:
The perigee and apogee radii of a satellite in Earth orbit can be calculated by subtracting the radius of the Earth from the given altitudes of perigee and apogee.
Step-by-step explanation:
The perigee and apogee radii of a satellite in Earth orbit can be calculated using the given information. The perigee is the point of closest approach to Earth, while the apogee is the point of furthest distance from Earth. To find the radii, we subtract the radius of the Earth from the given altitudes of perigee and apogee.
Perigee radius = 500 km + 6370 km = 6870 km
Apogee radius = 2500 km + 6370 km = 8870 km