Multi-sensor system and the failure decision method for control supersonic flight vehicle's engine intake

摘要

The present invention relates to a multi-measurement sensor system for supersonic engine inlet flow control and a failure determination method thereof, and more particularly, to a multi-measurement sensor for supersonic engine inlet flow control for generating an output signal for engine inlet control, and failure determination thereof A method, comprising: an endothelial structure provided at an engine inlet; An outer skin structure surrounding the inner skin structure; By providing a multi-measuring sensor for controlling the flow of a supersonic engine inlet, including at least one pressure probe provided between the inner skin structure and the outer shell structure, there is a merit of enabling precise operation of the supersonic engine inlet.