A method, apparatus, and computer usable program code for monitoring an actuator for a control surface on an aircraft. In one advantageous embodiment, an error signal generated is received in response to sending a command to the actuator to move the control surface on the aircraft. Responsive to receiving the error signal, an amplitude and a frequency are identified for the error signal. A determination is made as to whether the amplitude exceeds a set of amplitude limits for the frequency, wherein each amplitude in the set of amplitude limits is associated with a requirement in a set of requirements. An exceedance count is incremented for each requirement in the set of requirements in which an associated amplitude limit has been exceeded by the amplitude to form an updated set of exceedance counts. A fault indication is generated if any exceedance count in the updated set of exceedance counts is greater than a threshold.
Actuation response oscillation detection monitor
Oszillationserkennungsvorrichtung für eine Aktuatorreaktion
Détecteur d'oscillations pour la réponse d'un actionneur
2018-09-12
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge / G05B Steuer- oder Regelsysteme allgemein , CONTROL OR REGULATING SYSTEMS IN GENERAL / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen / G08B SIGNALLING OR CALLING SYSTEMS , Signalisier- oder Rufsysteme |
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