an earth satellite is planned to be launched into a circular orbit with an altitude of 500 km. the launch vehicle reaches the planned burnout velocity, with a flight path angle of 0. however, due to a guidance and control error, this occurs at an altitude of only 300 km. determine whether or not the satellite will remain in orbit, and calculate the orbit’s eccentricity and the radii at perigee and at apogee (km). draw a neat sketch of the resulting trajectory, showing the earth’s surface and the locations of the apogee and perigee.