------------------------------------------------------------------------------- Computes two impulses needed to transfer between two elliptical coplanar orbits. ------------------------------------------------------------------------------- Form: [dv, dv1, dv2, et, at] = DVHohE( e1, a1, e2, a2, mu ) ------------------------------------------------------------------------------- ------ Inputs ------ e1 Eccentricity of first orbit a1 Semi-major axis of first orbit e2 Eccentricity of final orbit a2 Semi-major axis of final orbit mu Gravitational parameter ------- Outputs ------- dv Total delta v dv1 Low orbit to transfer orbit delta v dv2 Transfer orbit to high orbit delta v et Transfer orbit eccentricity at Transfer orbit semimajor axis -------------------------------------------------------------------------------