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The Integrated Actuation Package Approach to Primary Flight Control
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English
Abstract
Renewed interest in the attributes of the More Electric Airplane (MEA) is accelerating the development of power-by-wire actuation systems to perform the critical function of primary flight control. The Integrated Actuation Package (IAP™), which utilizes an electric motor driven servopump to control actuator position, is presented within as a prospective candidate to fill this demanding role.
Also presented is a design and performance overview of a dual channel IAP™ produced for flight test evaluation on the Lockheed High Technology Test Bed (HTTB).
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Authors
Citation
Acee, H., "The Integrated Actuation Package Approach to Primary Flight Control," SAE Technical Paper 920968, 1992, https://doi.org/10.4271/920968.Also In
References
- Integrated Servo Actuator Subsystem - Rudder Control System, HTTB Lockheed Aeronautical Systems Company 1991
- Richardson, Donald V. Caisse, Arthur J. (Jr.) Rotating Electric Machinery and Transformer Technology 3rd Prentice-Hall Englewood Cliffs, NJ 1979
- Keller, George R. Hydraulic System Analysis 2nd Penton/IPC Cleveland 1985
- Lee Technical Hydraulic Handbook Lee Company 1987