Entity

Time filter

Source Type

Hertford, United Kingdom

Gao Y.,Institute of the Motor Industry | Liu Z.,Harbin Institute of Technology | Chen H.,Jilin University
Journal of Control Theory and Applications | Year: 2012

The main contribution of this paper is to present a novel robust observer-based controller design method for discrete-time piecewise affine systems with norm-bounded uncertainties. The key ideas are to construct a piecewise-quadratic Lyapunov function to guarantee the stability of the closed-loop systems, approximate polytopic operating regions by ellipsoids, and use the singular value decomposition technique to treat the constraint of matrix equality. It is shown that the suggested control method can be formulated as linear matrix inequalities that are numerically feasible with commercially available software. A numerical example is also given to verify the proposed approach. © 2012 South China University of Technology, Academy of Mathematics and Systems Science, Chinese Academy of Sciences and Springer-Verlag Berlin Heidelberg. Source


Yao H.,Institute of the Motor Industry
Hangkong Dongli Xuebao/Journal of Aerospace Power | Year: 2011

Mathematical model for a turbo-shaft engine and actuator was developed by using Simulink simulation tools in this thesis. Control laws for turbo-shaft engine control system, such as steady-state, acceleration and deceleration, fault-tolerant for key sensor failure found out afterward, were studied in simulation. It presented a full solution scheme of turbo-shaft engine control. Simulation results show that, the solution scheme can assure control system works steadily and has better steady-state and dynamic performance features, where there is fault or not. Source


Lu F.,Nanjing University of Aeronautics and Astronautics | Huang J.-Q.,Nanjing University of Aeronautics and Astronautics | Kong X.-T.,Institute of the Motor Industry
Hangkong Dongli Xuebao/Journal of Aerospace Power | Year: 2012

In order to meet the requirements of turbo-fan engine fault diagnosis, a kind of rapid prototype simulation design way based on the baseline of the engine for gas-path fault diagnosis was proposed. Considering the precision of the fault diagnosis in the flight envelope influenced by the engine baseline, optimal transformation index was selected in simulation transformation for the setup of baseline. The weighted least-squares algorithm was used to design the fault diagnosis model, which was downloaded to National Instrument (NI) CompactRIO to form rapid prototype simulation system. A series of test experiments on a turbo-fan engine show the effectiveness of this rapid prototype design method for gas-path fault diagnosis. Source


Huang X.,Nanjing University of Aeronautics and Astronautics | Zhao X.,Institute of the Motor Industry
APISAT 2015 - 7th Asia-Pacific International Symposium on Aerospace Technology | Year: 2015

Matching calculation model of "auxiliary power unit(APU)-pipeline-air turbine starter(ATS)" system, which has the advantages of flexibility and high efficiency, is investigated based on APU air bleeding model in order to meet the design requirement of large civil airplane starting system. Firstly, APU air bleeding parameter curves are converted to APU air feeding characteristic curves by simplifying compressed air pipeline calculation. Then mathematical model of "APU-pipeline-ATS" cooperation system is established in accordance with the matching principle of invariable corrected flow at the minimum cross section of turbine guide. Model simulation results of "APU-Pipeline-ATS" system agree with the working parameters of ATS100-400 quite well, which verifies the rationality and computational accuracy of modeling method. Base on the cooperation system model, the influence of guide inlet pressure limit on cooperation points is emphatically studied, and principles should be following when designing starting air feeding system are provided. Source


Lu F.,Nanjing University of Aeronautics and Astronautics | Lu F.,Institute of the Motor Industry | Huang J.,Nanjing University of Aeronautics and Astronautics | Lv Y.,Nanjing University of Aeronautics and Astronautics
Energies | Year: 2013

Different approaches for gas path performance estimation of dynamic systems are commonly used, the most common being the variants of the Kalman filter. The extended Kalman filter (EKF) method is a popular approach for nonlinear systems which combines the traditional Kalman filtering and linearization techniques to effectively deal with weakly nonlinear and non-Gaussian problems. Its mathematical formulation is based on the assumption that the probability density function (PDF) of the state vector can be approximated to be Gaussian. Recent investigations have focused on the particle filter (PF) based on Monte Carlo sampling algorithms for tackling strong nonlinear and non-Gaussian models. Considering the aircraft engine is a complicated machine, operating under a harsh environment, and polluted by complex noises, the PF might be an available way to monitor gas path health for aircraft engines. Up to this point in time a number of Kalman filtering approaches have been used for aircraft turbofan engine gas path health estimation, but the particle filters have not been used for this purpose and a systematic comparison has not been published. This paper presents gas path health monitoring based on the PF and the constrained extend Kalman particle filter (cEKPF), and then compares the estimation accuracy and computational effort of these filters to the EKF for aircraft engine performance estimation under rapid faults and general deterioration. Finally, the effects of the constraint mechanism and particle number on the cEKPF are discussed. We show in this paper that the cEKPF outperforms the EKF, PF and EKPF, and conclude that the cEKPF is the best choice for turbofan engine health monitoring. © 2013 by the authors; licensee MDPI, Basel, Switzerland. Source

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