to the right rotor 12 a tends to be pitched upwardly and rotor 12 b tends to be pitched downwardly this results in a close clearance 32 at a forward portion 36 of the rotors 12 a and 12 b one of ordinary skill in the art will readily understand that other maneuvers such as pitch maneuvers of the helicopter 10 will result in substantially equal and opposite rotor moments in the rotors 12 a and 12 b such rotor moments induce stresses in the rotors 12 a and 12 b due to the large gyroscopic bending loads and it is desired to minimize the bending loads and provide sufficient clearance between rotors 12 a and 12 b referring to fig4 in order to compensate reduce the rotor moments induced by such maneuvers a model following control system 38 implements a gyroscopic feed forward compensation algorithm 52 hereinafter u201c feed forward algorithm 52 u201d in order to improve stability and robustness of the control system 38 the feed forward algorithm 52 uses in an embodiment body pitch or body roll commanded rates and a schedule of corrective cyclic inputs for these commanded body pitch or roll rates in order to drive cyclic pitch changes in the rotors 12 a and 12 b these cyclic pitch changes counteract the gyroscopic rotor moments with aerodynamic forces on the blades the feed forward algorithm 52 utilizes a feed forward commanded body pitch or body roll rate as the actual pitch or roll rate a schematic of a control system 38 to accomplish this is illustrated in fig4 pilot inputs 40 from for example a cyclic controller such as a pilot cyclic stick and or foot pedals are received by a.