This 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


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Control Design for a Generic Commercial Aircraft Engine


    Contributors:

    Conference:

    46th Joint Propulsion Conference and Exhibit ; 2010 ; Nashville, TN, United States


    Publication date :

    2010-10-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Control Design for a Generic Commercial Aircraft Engine

    Csank, Jeffrey / May, Ryan / Litt, Jonathan et al. | AIAA | 2010



    A High-Fidelity Simulation of a Generic Commercial Aircraft Engine and Controller

    May, Ryan / Csank, Jeffrey / Lavelle, Thomas et al. | AIAA | 2010



    Generic Aircraft Design Flowchart

    Keane, Andrew J. / Sóbester, András / Scanlan, James P. | Wiley | 2017