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 `=6400km`. Calculate the eccentricity of the elliptical orbit.

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.

A Satellite is in an elliptic orbit around the earth with aphelion of 6R and perihelion of 2R

A satellite is in an elliptical orbit around the earth with aphelion of 6R_E and perihelion of 3R_E , where R_E is the radius of the earth. The eccentricity of the orbit is

A satellite is an elliptic orbit around the earth with aphelion of 6R and perihelion of 2R wherer R = 6400 KM is the radius of the earth. Find the eccentricity of the orbit.

A satellite is in an elliptic orbit around the earth with aphelion of 6R and perihelion of 2R where R = 6400 km is the radius of the earth . Find the velcoity of the satellite at apogee and perigee.[ G = 6.67 xx10^(-1) SI unit and M = 6 xx 10^(24)kg ]

A satellite is in an elliptical orbit around the earth with aphelion of 6 R and perihelion of 2 R where R = 6400 km is the radius of the earth. Find eccentricity of the orbit. Find the velocity of the satellite at apogee and perigee. What should be done if this satellite has to be transferred to a circular orbit of radius 6R ? [G = 6.67 xx 10^(-11) SI units and M = 6 xx 10^(24) kg]