1. (a) The orbital period can be calculated using the equation
T = 2πrr r
gR2
e
where r = Re + h
where re = 6378 km is the earth’s radius, r is the satellites distance
from the earth’s center and h = 205 km is the satellite’s orbital altitude, and g = 9.81m/s2
is the gravitational acceleration. With these
given values the orbital period is
Torbit = 5312.5s = 1.4757h