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Control Design for a Generic Commercial Aircraft EngineThis paper describes the control algorithms and control design process for a generic commercial aircraft engine simulation of a 40,000 lb thrust class, two spool, high bypass ratio turbofan engine. The aircraft engine is a complex nonlinear system designed to operate over an extreme range of environmental conditions, at temperatures from approximately -60 to 120+ F, and at altitudes from below sea level to 40,000 ft, posing multiple control design constraints. The objective of this paper is to provide the reader an overview of the control design process, design considerations, and justifications as to why the particular architecture and limits have been chosen. The controller architecture contains a gain-scheduled Proportional Integral controller along with logic to protect the aircraft engine from exceeding any limits. Simulation results illustrate that the closed loop system meets the Federal Aviation Administration s thrust response requirements
Document ID
Document Type
Technical Memorandum (TM)
Csank, Jeffrey
(N and R Engineering and Management Services Cleveland, OH, United States)
May, Ryan D.
(ASRC Aerospace Corp. Cleveland, OH, United States)
Date Acquired
August 25, 2013
Publication Date
October 1, 2010
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA Paper 2010-6629
Meeting Information
Meeting: 46th Joint Propulsion Conference and Exhibit
Location: Nashville, TN
Country: United States
Start Date: July 25, 2010
End Date: July 28, 2010
Sponsors: American Society of Mechanical Engineers, American Inst. of Aeronautics and Astronautics, American Society for Electrical Engineers, Society of Automotive Engineers, Inc.
Funding Number(s)
WBS: WBS 457280.
Distribution Limits
Public Use Permitted.
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