1. Tardigrade
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  4. A satellite is in an elliptic orbit around the earth with aphelion of 6RE and perihelion of 2RE, where RE is the radius of the earth. The eccentricity of the orbit is

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Q. A satellite is in an elliptic orbit around the earth with aphelion of $6R_E$ and perihelion of $2R_E$, where $R_E$ is the radius of the earth. The eccentricity of the orbit is

Gravitation

Solution:

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Here, $r_A = 6R_E$, $r_P = 2R_E$
The eccentricity of the orbit is
$e = \frac{r_{A}-r_{p}}{r_{A}+r_{P}}$;
$e = \frac{6R_{E}-2R_{E}}{6R_{E}+2R_{E}} = \frac{4}{8} = \frac{1}{2}$