Abstract:This paper presents a high-bandwidth flight control design for helicopters using integrated rotor control law. Based on an explicit model-following control design, a rotor state feedback control law was developed and integrated into the baseline control system. The rotor/body feedback gains were comprehensively optimized to improve the stability of helicopter. A rotor control augmentation was designed to enhance command tracking ability. Then, a command model design method was proposed based on the command tracking ability to improve helicopter attitude response bandwidth and attitude quickness. Finally, based on a high-order helicopter flight dynamics model, the helicopter handling qualities were analyzed. The results show that the integrated rotor control law can maintain the stability margin of the baseline control system while improve the control frequencies. The roll and pitch control bandwidths are improved by 10% and 18% respectively, while the roll and pitch attitude quickness are improved by 20% and 25% respectively.