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| 1. |
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` |
| Answer» Correct Answer - C | |