TY - GEN
T1 - Dynamic modeling of a turboshaft engine driving a variable pitch propeller: A decentralized approach
AU - Pakmehr, Mehrdad
AU - Fitzgerald, Nathan
AU - Paduano, James D.
AU - Feron, Eric
AU - Behbahani, Alireza
N1 - Generated from Scopus record by KAUST IRTS on 2021-02-18
PY - 2011/1/1
Y1 - 2011/1/1
N2 - In this paper, a nonlinear performance based model for a twin spool turboshaft engine which drives a variable pitch propeller, is developed. Then a piecewise linear representa- tion of the model, which can be used for control of the turboshaft engine for large throttle commands (i.e. for the entire ight envelope), is developed. Open loop simulation results of SPT5 engine dynamics, using piecewise linear modeling approach, are presented. Fi- nally, a decentralized piecewise representation of the model suitable for distributed and decentralized engine control, is developed. Simulation results for decentralized piecewise linear control of the JetCat SPT5 turboshaft engine also are presented. Fuel ow is the control input for the engine core subsystem, and prop pitch angle is the control input for the engine fan/prop subsystem. © 2011 by the American Institute of Aeronautics and Astronautics, Inc.
AB - In this paper, a nonlinear performance based model for a twin spool turboshaft engine which drives a variable pitch propeller, is developed. Then a piecewise linear representa- tion of the model, which can be used for control of the turboshaft engine for large throttle commands (i.e. for the entire ight envelope), is developed. Open loop simulation results of SPT5 engine dynamics, using piecewise linear modeling approach, are presented. Fi- nally, a decentralized piecewise representation of the model suitable for distributed and decentralized engine control, is developed. Simulation results for decentralized piecewise linear control of the JetCat SPT5 turboshaft engine also are presented. Fuel ow is the control input for the engine core subsystem, and prop pitch angle is the control input for the engine fan/prop subsystem. © 2011 by the American Institute of Aeronautics and Astronautics, Inc.
UR - http://arc.aiaa.org/doi/abs/10.2514/6.2011-6149
UR - http://www.scopus.com/inward/record.url?scp=85086950247&partnerID=8YFLogxK
U2 - 10.2514/6.2011-6149
DO - 10.2514/6.2011-6149
M3 - Conference contribution
SN - 9781600869495
BT - 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011
PB - American Institute of Aeronautics and Astronautics [email protected]
ER -