Question

The radius of orbit of a geostationary satellite is given by ..... (M = Mass of the earth; R = Radius of the earth; T = Time period of the satellite)

• A. $[(T^2*G*M)/(4*pi^2)]^(3/2)$
• B. $[(T^2*G*M)/(4*pi^2)]^(2/3) – R$
• C. $[(T^2*G*M)/(4*pi^2)]^(1/3) – R$
• D. $[(T^2*G*M)/(4*pi^2)]1/3$

Answer 1

Answer:

$[(T^2*G*M)/(4*pi^2)]1/3$

The time period of a satellite is given by;$T = 2 * pi * (R+h) ^(3/2)/ (G * M)^(1/2)$

Solving for orbital radius “(R+h)”, we get; (R+h) =$[(T^2 * G * M)/(4 * pi^2)]^(1/3)$.