Northrop Grumman Systems Corporation

Ghetzler Aero-power Corporation

Richard Ghetzler

Donald A Sofia

Michael A Mast

Jerome F Wojtalik, Jr

Jeff Browning

Terrance W Mollison

Neils Kruse

Nate Newman

Kim D Volendorf

Harold Schmulenson

Neil E Hodge

Kendal R Stephens

A novel device and method for the injection and molding of a body of elastomeric composition within a mold cavity, around a core member and against the prepared surface of a test substrate, such as a ceramic or metallic disk, at the base of the mold cavity. The molded elastomeric composition is molded as an axial-symmetrical frustro-conical body which tapers down to a uniformly thin layer between the test substrate surface and the flat undersurface of the core member, and the core member supporting the molded elastomeric body bonded to the test substrate are separable from the mold cavity for attachment to a conventional tension test machine for measuring the interfacial bond strength between the elastomer and the prepared surface of the test substrate.

Molding device and method for measuring the bonding strength of elastomers

A low drag ducted ram air turbine generator and cooling system is provided. The ducted ram air turbine generator and cooling system has reduced drag while extracting dynamic energy from the air stream during the complete range of intended flight operating regimes. A centerbody/valve tube having an aerodynamically shaped nose is slidably received in a fairing and primary structure to provide a variable inlet area. An internal nozzle control mechanism attached to the valve tube positions nozzle control doors to provide variable area nozzles directing air flow to the turbine stator and rotor blades to maintain optimum generator efficiency. An alternate embodiment includes an annular internal nozzle having interleaved panels to modulate the air flow to the turbine.

Low drag ducted Ram air turbine generator and cooling system

Apparatus for simulating aerodynamic heating and cooling on the outer surface of equipment externally mounted on an aircraft or missile as if airborne and exposed to an air stream. A first proximately spaced enclosure substantially uniformly conforms to the outer surface of the equipment and defines a low pressure chamber. A second enclosure envelops the first enclosure and defines a high pressure chamber. An adjustable flow producing mechanism directs flow of pressurized inlet air into the high pressure chamber. A temperature control mechanism selectively heats and cools the inlet air. Vents in the second enclosure exhaust the air from the low pressure chamber to the ambient region and a plurality of spaced orifices in the first enclosure direct jets of the pressurized air from the high pressure chamber into the low pressure chamber which vigorously impinge on the outer surface of the equipment. A first sensor measures the temperature of the air in the high pressure chamber and generates a first proportional signal and a second sensor measures the heat transfer coefficient at a plurality of locations on the outer surface of the equipment and generates a second proportional signal. A processor containing known information concerning the temperature and heat transfer properties of the equipment if airborne and exposed to an air stream under specified operating flight conditions compares the first and second signals with the known information and operates the flow producing and temperature control mechanisms until the signals conform to the known information.

Apparatus to simulate aerodynamic cooling and heating effects on

A ram air turbine generator comprises a cylindrical external fairing having bypass exhaust orifices adjacent the leading end and external exhaust ports adjacent the aft end. A central flow guide is coaxially mounted and has a contoured outer surface spaced from the external fairing. A valve tube is coaxial with, and intermediate, the external fairing and the central flow guide and extends between a nose end with openings nearest the leading end of the external fairing and an aft plate. The valve tube also has a plurality of aft internal exhaust ports generally coextensive with the aft external exhaust ports in the external fairing. The valve tube is spring biased to a first position at which its nose end is proximate the leading end of the fairing and blocks the bypass exhaust orifices such that air is caused to flow through an annular nozzle defined between the valve tube and the central flow guide, through a turbine wheel, then out to the surrounding region through the aft internal and external exhaust ports. Ram air is effective to move the valve tube to a second position so as to expose the bypass exhaust orifices enabling substantial flow of bleed air therethrough. Additionally, a nozzle flow control mechanism is operable in response to movement of the valve tube between the first and second positions.

RAM air turbine generating apparatus

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Buffalo Grove, IL, United States of America

Richard Ghetzler