An artificial satellite is in an elliptical orbit around the earth with aphelion of `6R` and perihelion of `2R` where `R` is radius of the earth `=6400 km`. Calculate the eccentricity of the elliptical orbit.

Options

A. `(1)/(2)`
B. `(1)/(3)`
C. `(1)/(4)`
D. `(1)/(6)`

Answer

A

Explanation

(a)
Here, `r_(A)=6R_(E),r_(p)=2R_(E)`
The eccentricity of the orbit is
`e=(r_(A)-r_(P))/(r_(A)-r_(P)),e=(6r_(E)-2R_(E))/(6R_(E)+2R_(E))=(4)/(8)=(1)/(2)`