| 摘要 |
A slip-reduction control unit is employed on an aircraft (1; 102) having a longitudinal axis (6) and a steerable landing gear, for example a nose landing gear (8; 108) wheel (NLG). The control unit 130 is arranged to receive steering input signals from which a target steering command output may be ascertained. The control unit is arranged to receive one or more additional input signals 140, 150, 190 concerning at least one of (a) the motion of the aircraft, (b) a steering angle, and (c) a parameter relating to the slip sustained by the steerable landing gear. The slip-reduction control unit 130, 133 is arranged so that, in dependence on at least the additional input signals the rate of change of the angle (ϴNLG) of the one or more steerable wheels 12 that would otherwise be commanded is reduced. Vibration on the aircraft that might otherwise be caused by such steering may be reduced by so controlling the rate of change of the steering angle. |
