Northrop Grumman Systems Corporation

Yu-Hang Ho

Clarence Lui

Chris K Lee

A power and cooling management system configured to flexibly couple various adaptive modules to an integrated power and cooling unit to suit any aircraft platform is provided. The integrated power and cooling unit has a compressor(s), power turbine(s), cooling turbine(s) and integral starter generator(s) mounted to the shaft of the power and cooling turbine. The integrated power and cooling unit may be pneumatically and/or pneumatically coupled to an adaptive module that comprises an additional compressor and an additional turbine or electrically coupled to a fuel cell which provides the main power after entering the full operation mode. When the engine includes an integral starter generator mounted thereto, the integral starter generator of the integrated power and cooling unit is operative to receive electric power from the engine mounted generator. Alternatively, a motor/generator may be mounted to the shaft of the additional turbine of the adaptive module.

Flexible power and thermal architectures using a common machine

An apparatus for providing environmental control, secondary power and emergency power for an aircraft, comprises a cooling turbine coupled to a first electromechanical machine rotor, and including an input for receiving compressed air or ram air, and an output for discharging cooled air or exhaust air; a compressor coupled to a second electromechanical machine rotor, and including an input for receiving engine bleed air or ambient air, and an output for discharging compressed air; means for magnetically coupling the first and second rotors; a power turbine coupled to the compressor; a heat exchanger connected between the compressor output and the cooling turbine input; and a control unit for controlling the magnetic coupling between the first and second rotors.

Magnetically coupled integrated power and cooling unit

According to one embodiment of the invention, a system for deflecting an aerodynamic control surface includes a first piezoelectric actuator coupled to a first flexure member. The first flexure member has a first end coupled to a first surface of the aerodynamic control surface and is operable to amplify a linear motion of the first piezoelectric actuator. The system further includes a second piezoelectric actuator coupled to a second flexure member. The second flexure member has a first end coupled to a second surface of the aerodynamic control surface and is operable to amplify a linear motion of the second piezoelectric actuator.

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Torrance, CA, United States of America

Yu-Hang Ho