A planet revolves around the sun in an elliptical orbit. If `v_(p)` and `v_(a)` are the velocities of the planet at the perigee and apogee respectively, then the eccentricity of the elliptical orbit is given by :
A. `(v_(p))/(v_(a))`
B. `(v_(a)-v_(p))/(v_(a)+v_(p))`
C. `(v_(p)+v_(a))/(v_(p)-v_(a))`
D. `(v_(p)-v_(a))/(v_(p)+v_(a))`