Question

A satellite is in an elliptic orbit around the earth with aphelion of $6 \mathrm { R } _ { \mathrm { E } }$ and perihelion of where is the radius of the earth. The eccenttricity of the orbit is

• A. $\frac { 1 } { 2 }$
• B. $\frac { 1 } { 3 }$
• C. $\frac { 1 } { 4 }$
• D. $\frac { 1 } { 6 }$

Answer 1

Answer: (A)

$\frac { 1 } { 2 }$

Answer 2

Here,

The eccentricity of the orbit is

$e = \frac { r _ { A } - r _ { P } } { r _ { A } + r _ { p } }$