Minimal Transfer Trajectories with Optimum Correctional Manoeuvre Programme

Abstract

Inter-orbital transfer trajectories with correctional maneuvers are investigated with the object to reduce the energy consumption to the minimum in the transfer operation. Various cases arising out of the required missions have been analysed and it is demonstrated that contangential Hohmann type trajectories are not minimal in transfer with correctional maneuvers country to the case of inter-orbital transfer without correctional maneuvers. Transfer with no corrective thrusts have also been discussed and laws for optimum heading angles of the space vehicle are derived.