Real Time Linear Simulation and Control for Small Aircraft Turbojet Engine
The performance of the aircraft gas turbine engine requires optimization because it is directly related to overall aircraft performance. In this study, a modified DYNGEN, a nolinear dynamic simulation program with component maps of the small aircraft turbojet engine, was used to predict the overall...
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Published in | Journal of mechanical science and technology Vol. 13; no. 9; pp. 656 - 666 |
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Main Authors | , |
Format | Journal Article |
Language | English |
Published |
Seoul
대한기계학회
01.09.1999
Springer Nature B.V |
Subjects | |
Online Access | Get full text |
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Abstract | The performance of the aircraft gas turbine engine requires optimization because it is directly related to overall aircraft performance. In this study, a modified DYNGEN, a nolinear dynamic simulation program with component maps of the small aircraft turbojet engine, was used to predict the overall engine performance. Response characteristics of various cases, such as 6%, 5% and 3% rpm step models and the real-time linear model of the interpolation scheme within the operating range were compared. Among them, the real time linear model was selected for the turbojet engine with nonlinear characteristics. Finally control schemes such as PI (Proportional-Integral Controller) and LQR (Linear Quadratic Regulator) were applied to optimize the engine performance. The overshoot of the turbine inlet temperature was effectively eliminated by LQR controller with the proper control gain K.[PUBLICATION ABSTRACT] |
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AbstractList | The performance of the aircraft gas turbine engine requires optimization because it is directly related to overall aircraft performance. In this study, a modified DYNGEN, a nolinear dynamic simulation program with component maps of the small aircraft turbojet engine, was used to predict the overall engine performance. Response characteristics of various cases, such as 6%, 5% and 3% rpm step models and the real-time linear model of the interpolation scheme within the operating range were compared. Among them, the real time linear model was selected for the turbojet engine with nonlinear characteristics. Finally control schemes such as PI (Proportional-Integral Controller) and LQR (Linear Quadratic Regulator) were applied to optimize the engine performance. The overshoot of the turbine inlet temperature was effectively eliminated by LQR controller with the proper control gain K.[PUBLICATION ABSTRACT] The performance of the aircraft gas turbine engine requires optimization because it is directly related to overall aircraft performance. In this study, a modified DYNGEN, a nolinear dynamic simulation program with component maps of the small aircraft turbojet engine, was used to predict the overall engine performance. Response characteristics of various cases, such as 6%, 5% and 3% rpm step models and the real-time linear model of the interpolation scheme within the operating range were compared. Among them, the real time linear model was selected for the turbojet engine with nonlinear characteristics. Finally control schemes such as PI (Proportional-Integral Controller) and LQR (Linear Quadratic Regulator) were applied to optimize the engine performance. The overshoot of the turbine inlet temperature was effectively eliminated by LQR controller with the proper control gain K. |
Author | Chang Duk Kong Suk Choo Chung |
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CitedBy_id | crossref_primary_10_1115_1_1610014 crossref_primary_10_1007_BF02939343 crossref_primary_10_5139_IJASS_2014_15_2_123 crossref_primary_10_1007_s12206_019_0847_3 |
Cites_doi | 10.1115/97-AA-114 10.1115/96-GT-104 10.1115/1.2906159 10.2514/3.19909 10.1115/1.2906568 10.1115/1.3445601 10.1017/S000192400002340X 10.2514/3.8548 10.1115/1.2906157 10.1115/1.2906571 10.1115/1.2906160 10.1115/1.2906847 10.1115/1.2906536 10.2514/3.21350 10.1115/1.2906516 10.1115/96-GT-332 10.1115/1.2906654 |
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References | A. Stamatis (BF03184576_CR17) 1990; 112 J. R. Mihaloew (BF03184576_CR11) 1984; 7 BF03184576_CR21 I. H. Ismail (BF03184576_CR7) 1991; 113 Y. Wang (BF03184576_CR19) 1991; 113 J. W. Watts (BF03184576_CR20) 1992; 114 D, L Smith (BF03184576_CR15) 1990; 112 L. J. Kerr (BF03184576_CR5) 1992; 114 D. L Smith (BF03184576_CR16) 1990; 112 N. Sugiyama (BF03184576_CR18) 1994; 17 C. D. Kong (BF03184576_CR6) 1995; 23 Z. Ping (BF03184576_CR12) 1992; 114 BF03184576_CR8 BF03184576_CR9 BF03184576_CR4 M. T. Schobeiri (BF03184576_CR13) 1994; 116 BF03184576_CR2 BF03184576_CR3 BF03184576_CR14 W. Merrill (BF03184576_CR10) 1984; 7 BF03184576_CR1 |
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SubjectTerms | Aerospace engines Aircraft Aircraft components Computer simulation Gas turbine engines Nonlinearity R&D Real time Research & development Studies Turbojet engines |
Title | Real Time Linear Simulation and Control for Small Aircraft Turbojet Engine |
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