Fault monitoring system for aircraft power control units
AssigneeThe Boeing Company
InventorsJames E. Klansnic, Bernus G. Turner
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Abstract
A monitoring system for detecting a fault condition in any one of multiple power control actuator units used for positioning an aircraft's control surface includes sensors for producing sense signals corresponding to the load on each actuator unit under a given control surface loading condition. The sense signals are compared with a reference level signal corresponding to a maximum allowable load. An indication is produced in response to the load on any actuator unit exceeding its allowed value.
Claims6
In an aircraft control surface positioning system wherein multiple actuator units respond to a control input to position the control surface, a monitoring system for detecting a fault condition in any one of said actuation units, the monitoring system comprising:
- activation means for detecting the presence of a predetermined load condition on the control surface and activating the monitoring system in response thereto;
- sense means for producing a sense signal related to the load at each actuator unit;
- reference level means for producing a predetermined reference level signal;
- comparator means for comparing each sense signal with said reference level signal and producing a fault signal in response to a predetermined relation therebetween;
- and,
- indicator means for producing a fault indication in response to a comparator means produced fault signal.
Dependencies are inferred from the claim text.