A planet revolves around the sun in an elliptical orbit. If vp and va are the velocities of the planet at the perigee and apogee respectively, then the eccentricity of elliptical orbit is given by :
A
vpva
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B
va−vpva+vp
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C
vp+vavp−va
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D
vp−vavp+va
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Solution
The correct option is Bvp−vavp+va As vpva=a(1+e)a(1−e) where a is semi-major axis of the ellipse