| 摘要 |
A method and system for detecting in-flight fault characteristics of flight control actuators is provided. Commands are sequentially sent to sets of actuators during flight in a manner that is expected to produce little or no net aircraft motion. The detection of motion indicates the possibility of a faulty actuator. If additional tests confirm the failure, the actuator is isolated and other actuators are compensated to adjust for the failed actuator, permitting continuation of safe and controllable fight by the flight crew and control for a safe landing. This isolation of the suspect failed actuator serves to prevent a possible upset of the aircraft control should the suspect actuator completely fail to a large offset condition, due to continued use during flight, a situation that may cause loss of control of the aircraft.
|
