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

Question

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

Tardigrade Admin · Accepted Answer

<img class="img-fluid question-image" alt="image" src="https://cdn.tardigrade.in/img/question/chemistry/1d58f8d32b34464c67b4885dcc5d14fa-.jpeg" /> Here, rA = 6RE, rP = 2RE The eccentricity of the orbit is e = (rA-rp/rA+rP); e = (6RE-2RE/6RE+2RE) = (4/8) = (1/2)

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

$\frac{1}{2}$

$\frac{1}{3}$

$\frac{1}{4}$

$\frac{1}{6}$

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

Q. 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

21​

31​

41​

61​