Northrop Grumman Systems Corporation

Rohr, Inc.

Yuan Li

Steven M Kestler

James Alan Gerhardt

Kris I Lawrence

Christopher A Harris

Htet Htet Oo

Daniel R Cuppoletti

Russell V Westphal

Prithvi Sundar

A pressure sensor assembly for simultaneously providing a time-resolved total pressure measurement and steady state flow angles of an airflow. The assembly includes an outer shroud having a front face, a rear face and a central bore having a wall. A dynamic absolute pressure sensor is positioned within the bore and provides a time-resolved total airflow pressure measurement. First and second spaced apart static pressure ports extend from the front face of the shroud to the rear face of the shroud and adjacent to the bore. The pressure ports provide a pressure that can be measured by pressure probes, where a combination of the time-resolved total pressure measurement and pressure measurements from the probes provides a steady state flow angle of the airflow.

Directional dynamic absolute pressure sensor shroud and arrangement

An aircraft inlet comprising an annular air intake structure defined by an inner surface and an outer surface, a plurality of perforations formed in the outer surface of the aircraft inlet, a plenum chamber situated within the aircraft inlet and configured to receive air entering the plurality of perforations, and/or a plurality of sensors disposed about the outer surface of the aircraft inlet, each sensor associated with a region of the plurality of perforations. Each sensor may comprise a hot film anemometer. The aircraft inlet may further comprise a regulator coupled at one end to the plenum chamber and at another end to a pump, wherein the regulator regulates a suction produced by the pump.

Method of controlling boundary layer flow

Growing community of inventors

San Jose, CA, United States of America

Yuan Li