A satellite of mass `m` orbits the earth in an elliptical orbit having aphelion distance `r_(a)` ad perihelion distance `r_(p)`. The period of the orbit is T. The semi-major and semi-minor axes of the ellipse are a and b respectively. The angular momentum of the satellite is

A satellite of mass m orbits the earth in an elliptical orbit having aphelion distance r_(a) and perihelion distance r_(p) . The period of the orbit is T. The semi-major and semi-minor axes of the ellipse are (r_(a) + r_(p))/(2) and sqrt(r_(p)r_(a)) respectively. The angular momentum of the satellite is: (A) (2m pi (r_(B)+r_(p)) sqrt(r_(a) r_(p)))/T (B) (m pi (r_(a)+r_(p)) sqrt(r_(a) r_(p)))/(2T) (C) (m pi (r_(a)+r_(p)) sqrt(r_(a)r_(p)))/(4T) (D) (mpi (r_(a)+r_(p)) sqrt(r_(a)r_(p)))/T

A satellite of mass m orbits the earth in an elliptical orbit having aphelion distance r_(a) and perihelion distance r_(p) . The period of the orbit is T. The semi-major and semi-minor axes of the ellipse are (r_(a) + r_(p))/(2) and sqrt(rho_(p)r_(a)) respectively. The angular momentum of the satellite is :

A satellite of mass m orbits around the Earth of mas M in an elliptical orbit of semi - major and semi - minor axes 2a and a respectively. The angular momentum of the satellite about the centre of the Earth is

A satellite of mass m orbits around the Earth of mas M in an elliptical orbit of semi - major and semi - minor axes 2a and a respectively. The angular momentum of the satellite about the centre of the Earth is

A Satellite is in an elliptic orbit around the earth with aphelion of 6R and perihelion of 2R

A satellite is in an elliptical orbit around the earth with aphelion of 6R_E and perihelion of 3R_E , where R_E is the radius of the earth. The eccentricity of the orbit is