Velocity to Eccentricity

Let \(v\) be velocity at which a satellite is being projected into an elliptical trajectory, such that at apogee, it is a distance \(r\) from earth. Let \(u\) be the critical velocity at which the satellite must be projected at a distance \(r\) to move in circular path. If the eccentricity of elliptical orbit is \(0.44\) then find the ratio of \(v\) is to \(u\)?

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