Patent ID: 8874285

Claim:
An aircraft steering angle control system that outputs an operation signal related to a steering angle as a control command signal for a nose steering wheel, the control command causing an airframe that is taxiing to turn to a desired direction, the system comprising: a reference steering angle setting unit that calculates a reference steering angle on an assumption that the airframe is not skidding; a skid detection unit that determines a skidding state of the airframe based on the reference steering angle, the skidding state indicating whether or not the airframe is skidding; and a switch unit that selects and outputs the control command signal in conjunction with the skid detection unit, wherein when the determined skidding state of the airframe indicates that the airframe is skidding, a signal related to the reference steering angle is output as the control command signal for the nose steering wheel and the operation signal related to the steering angle is not used and output, and wherein the reference steering angle is determined by L*ω/V, where V represents a ground speed of the airframe, ω represents a yaw rate of the airframe, and L represents a distance between a center of gravity of the airframe and the nose steering wheel.