RECONFIGURATION CONTROLLING METHOD FOR A ROTORCRAFT HAVING LEFT AND RIGHT SIDE ROTORS, AND RECONFIGURATION CONTROLLING METHOD FOR A TILT ROTOR AIRCRAFT IN THE FIXED-WING MODE

摘要

The present invention relates to a failure avoidance control method for a rotorcraft vehicle having left and right rotors, such as a tilt rotor aircraft, and a failure avoidance control method in a fixed wing mode of a tilt rotor aircraft. The failure avoidance control method of the present invention replaces a failed actuator with a remaining normal actuator when a failure occurs in one of the actuators of the rotor or nacelle, which is applied to the upper rotorcraft. As the failure avoidance control method of the present invention can perform a lower level of redundancy design, the weight and price of the aircraft can be lowered, and even when one actuator is completely broken when compared to other aircraft having the same redundant channel, the control of the vehicle can be avoided. This allows for the design of safer aircraft.;Tilt rotor, rotor actuator, vertical axis cyclic, horizontal axis cyclic, collective