Path: Orbit/OrbitManeuver
% Find a coplanar orbit with a different altitude Compute the new eccentricity and semimajor axis after adding the delta altitude to both the apogee and perigee. -------------------------------------------------------------------------- Form: el2 = CoplanarOrbit( el1, deltaH ) -------------------------------------------------------------------------- ------ Inputs ------ el1 (1,6) Element set [a i W w e M] deltaH (1,1) Altitude change ------- Outputs ------- el2 (1,6) Element set [a i W w e M] --------------------------------------------------------------------------