Question

The orbit of a certain a satellite has a semimajor axis of 1.7 x 107 m and an eccentricity of 0.25. What are the satellite's perigee and apogee (in km)?

Answer 1

Answer:

The satellite's perigee and apogee are$2.13\times10^{4}\ km$ and $1.3\times10^{4}\ km$

Explanation:

Given that,

Semi major axis$a = 1.7\times10^{7}\ m$

Eccentricity = 0.25

We calculate the satellite's perigee

Using formula of perigee

$Perigee=a(1+e)$

$Perigee=1.7\times10^{7}(1+0.25)$

$Perigee=2.13\times10^{7}\ m$

$Perigee=2.13\times10^{4}\ km$

Using formula of apogee

$Apogee =a(1-e)$

$Apogee =1.7\times10^{7}(1-0.25)$

$Apogee =12750000$

$Apogee=1.3\times10^{7}\ m$

$Apogee=1.3\times10^{4}\ km$

Hence, The satellite's perigee and apogee are$2.13\times10^{4}\ km$ and $1.3\times10^{4}\ km$