Northrop Grumman Systems Corporation

Northrop Grumman Corpoation

James J Karanik

Runyon H Tindell

Dominic Anton

Thomas Maurici

Warren Davis

An antenna assembly comprises a composite support structure including an electrically conductive outer layer, an inner layer and a core layer between the outer layer and the inner layer; a cavity structure positioned adjacent to the inner layer of the composite support structure; a window structure positioned adjacent to the outer layer of the composite support structure; and a plurality of conductive z-pins passing through the composite support structure and electrically connecting the cavity structure to the outer layer of the composite support structure.

Antenna assembly including z-pinning for electrical continuity

A low drag fan assembly is provided which is adapted to be mounted within a ducting conduit of a ram air induction system of a vehicle for cooling a heat exchanger. The assembly includes a motor having an output drive; a motor bracketing system attached to the motor for suspending the motor within the ducting conduit; a fan hub attached to the output drive; and a plurality of foldable fan blades hingedly attached to an outer perimeter of the fan hub. When the motor is not activated, the plurality of fan blades are folded back in a non-deployed state which is generally longitudinally congruent to the airflow within the ducting conduit. When the motor is activated, the plurality of fan blades radially extend to a deployed state generally normal to and transverse to the airflow within the ducting conduit.

Low drag fan for a ram air induction system

In accordance with the present invention, an aerodynamic turbo engine nacelle, disposable about an engine having an engine face, for mitigating boundary layer separation of intake airflow comprises an engine inlet. The engine inlet is provided with an interior surface and a curved portion. The curved portion having a leading edge. The geometry of the engine inlet is such that the ratio of the circular area defined by the diameter defined by the leading edge of the curved portion to the minimum circular area defined by the interior surface of the engine inlet is less than 1.33. The engine nacelle is further provided with a pressurized fluid injecting device for injecting pressurized fluid at the engine inlet in a direction generally parallel to intake airflow in response to sensed airflow conditions.

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Brookhaven, NY, United States of America

James J Karanik