A satellite is launched into a circular orbit, R 4 above the surface of the earth. The time period of revolution is T = 2 π n 3 2 R g . Where R is the radius of the earth and g is the acceleration due to gravity. Then what is value on n ?

Step-by-step solution

T ⁡ = 2 π r ⁡ 3 2 g R ⁡ 2   where  r  =  R  +  h Then, T ⁡ = 2 π R ⁡ + h ⁡ R ⁡ R ⁡ + h ⁡ g Here, h = R 4 T ⁡ = 2 π R ⁡ + R ⁡ 4 R ⁡ R ⁡ + R ⁡ 4 g = 2 π 1 . 2 5 3 2 R ⁡ g