AN ELECTROMECHANICAL ACTUATOR FOR A

AN ELECTROMECHANICAL ACTUATOR FOR A - AN ELECTROMECHANICAL...

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AN ELECTROMECHANICAL ACTUATOR FOR A TRANSPORT AIRCRAFT SPOILER SURFACE Gregory L. Fronista Wright Laboratory WUPOOC Wright Patterson AFB, Ohio, 45433-7251 (937)255-6016, Fax: (937)255-3211 Graham Bradbury Sundstrand Aerospace 4747 Harrison Avenue Rockford, Illinois, 61 125-7002 (815)394-4226, fax: (81 5)394-2497 ABSTRACT The More Electric Aircraft Initiative (MEI) embraces the concept of utilizing electrical power for driving aircraft subsystems currently powered by hydraulic, pneumatic or mechanical means including utility and flight control actuation, environmental control system, lubrication and fuel pumps, and numerous other utility functions. An important part of this initiative is the development and demonstration of electrical power and power electronic components and systems to enhance reliability, fault-tolerance, power density and performance. The integration of advanced ME1 technologies will dramatically increase aircraft reliability and reduce susceptibility to battle damage. The needs for aircraft maintenance and support will be reduced along with ground support equipment and maintenance personnel. Power electronics and motor drives are essential elements of the MEI. Advancements in power semiconductor devices, capacitors, and integrated circuits for control has enabled high density, reliable power electronic and motor drive systems for the MEI. Power electronic systems include power conversion and conditioning for generators, battery chargers, DC to AC inverters, and DC to DC converters. These type of power electronic systems would be considered an integral part of the electrical power system. On the other hand, motor drive systems are an integral part of the utilization equipment and provide the interface between the electrical power system and the motor. Wright Laboratory and Sundstrand Aerospace have been working on the development of an electromechanical actuator to be compatible with the requirements of a spoiler for a typical transport aircraft. The focus of this development effort is in the motor drive, meaning the controller, inverter and motor utilized to control the actuator. Efforts are underway to increase the power density of the motor drive to achieve 1 kW/lb, with an efficiency of greater than 80%. This paper will discuss the design criteria and some of the trade-offs that were accomplished during this development. This work will include the use of a novel soft switched inverter driving a five-phase switched reluctance motor. A digital signal processing (DSP) chip will be utilized for responsive controls and field programmable gate arrays (FPGA) to reduce size and increase control electronics reliability. A power electronics module will be developed which is comprised of insulated gate bipolar transistor (IGBT) inverter switches, diodes, a current sensor and gate drives. The thermal management system will utilize a reflux heat exchanger with integral phase change material that will enable the motor drive to operate in the
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This note was uploaded on 05/08/2011 for the course MECHANICAL 203 taught by Professor Krishna during the Spring '11 term at Akademia Ekonomiczna w Poznaniu.

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AN ELECTROMECHANICAL ACTUATOR FOR A - AN ELECTROMECHANICAL...

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