METHOD AND DEVICE FOR DETECTING AN ELECTRICAL FAILURE AFFECTING AN ELECTRICAL SYSTEM FOR CONTROLLING A HYDRAULIC ACTUATOR OF VARIABLE GEOMETRIES OF AN AIRCRAFT ENGINE.

摘要

The detection method comprises, after the start of the control system (10), the latter being provided with two control channels (V1, V2) alternately used to send an electric control current (i) to an electrohydraulic member (11). ) for transforming this current into hydraulic power delivered to the actuator, and before powering up a starter-generator of the engine, the implementation of the following steps, for each control channel successively: - sending on this channel a predetermined electrical test current (itest); - Evaluation of a difference between the test electric current and a measurement of the electric current converted into hydraulic power by the electrohydraulic member; - if this difference is greater than a predefined threshold, detection of an electrical failure on this channel.