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Reduced-dimensional MPC controller for direct thrust control

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Chinese Journal of Aeronautics 2022年第4期35卷 66-81页

作者： Shuwei PANG Soheil JAFARI Theoklis NIKOLAIDIS Qiuhong LI Jiangsu Province Key Laboratory of Aerospace Power System Nanjing University of Aeronautics and AstronauticsNanjing 210016China Propulsion Engineering Center School of AerospaceTransport and ManufacturingCranfield UniversityBedford MK43 OALUK

With the development of the aircraft gas turbine engine, a control system should be able to achieve effective thrust control to gain better operability. The main contribution of this paper is to develop a novel direct thrust control approach based on an improved model predictive control method through a strategy that reduces the dimension of control sequence. It can not only achieve normal direct thrust control tasks but also maximize the thrust level within the safe operation boundaries. Only the action of switching the objective functions is required to achieve the switch of these two thrust control modes while there is no modification to the control structure. Besides,a shorter control sequence is defined for multivariable control by updating only one control variable at every simulation time instant. Therefore, the time requirement for the solving process of the optimal control sequence is reduced. The proposed controller is implemented to a twin-spool engine.Simulations are conducted in the wide flight envelope, and results show that the average timeconsumption can be reduced up to 65% in comparison with the standard model predictive control,and the thrust can be increased significantly when maximum thrust mode is implemented by using engine limit margins.

关键词： Computation time direct thrust control Gas turbine engine Model predictive control thrust optimization

Neural network-based model predictive control with fuzzy-SQP optimization for direct thrust control of turbofan engine

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Chinese Journal of Aeronautics 2022年第12期35卷 59-71页

作者： Yangjing WANG Jinquan HUANG Wenxiang ZHOU Feng LU Wenhao XU Jiangsu Province Key Laboratory of Aerospace Power System College of Energy and Power EngineeringNanjing University of Aeronautics and AstronauticsNanjing 210016China

A nonlinear model predictive control method based on fuzzy-Sequential Quadratic Programming(SQP)for direct thrust control is proposed in this paper for the sake of improving the accuracy of thrust control.The designed control system includes four parts,namely a predictive model,rolling optimization,online correction,and feedback correction.Considering the strong nonlinearity of engine,a predictive model is established by Back Propagation(BP)neural network for the entire flight envelope,whose input and output are determined with random forest algorithm and actual situation analysis.Rolling optimization typically uses SQP as the optimization algorithm,but SQP algorithm is easy to trap into local optimization.Therefore,the fuzzy-SQP algorithm is proposed to prevent this disadvantage using fuzzy algorithm to determine the initial value of SQP.In addition to the traditional three parts of model predictive control,an online correction module is added to improve the predictive accuracy of the predictive model in the predictive time domain.Simulation results show that the BP predictive model can reach a certain degree of predictive accuracy,and the proposed control system can achieve good tracking performance with the limited parameters within the safe range。

关键词： direct thrust control Fuzzy-SQP algorithm Limit protection Neural network Nonlinear model predictive control Random forest Turbofan engine

Research on direct-thrust-control of permanent magnet linear synchronous motor 25th

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Research on direct-thrust-control of permanent magnet linear...

thrust estimator design based on least squares support vector regression machine

第25届中国控制与决策会议

作者： Xusheng Wang Lijun Zhao Yan Wang Electrical Engineering Department Chengde Petroleum College Thermal energy and power engineering HeFei University of Technology

ISBN: (纸本)9781467355339

This paper presents direct torque control principle for a permanent magnet synchronous motor. Mathematical model of the permanent magnet linear synchronous motor is further described on the basis of this principle. The thrust control and flux linkage control are studied in this paper. In order to implement direct trust control, voltage vectors are suitably selected in the system according to the error between the true values and their reference of the trust and primary flux linkage. Moreover this paper introduces the realization of some key parts for the control system and analyzes the feasibility of direct thrust control of the linear motor. Some simulations with SIMULINK of MATLAB have been given to demonstrate validity of the control system.

关键词： permanent magnet linear synchronous motor direct torque control direct thrust control

来源： cnki会议评论

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Journal of Harbin Institute of Technology(New Series) 2010年第4期17卷 578-583页

作者：赵永平孙健国 Intelligent Ammunition Tecnology Laboratory of National Defence Nanjing University of Science & Technology College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics

In order to realize direct thrust control instead of traditional sensor-based control for aero-engines,it is indispensable to design a thrust estimator with high accuracy,so a scheme for thrust estimator design based on the least square support vector regression machine is proposed to solve this problem. Furthermore,numerical simulations confirm the effectiveness of our presented scheme. During the process of estimator design,a wrapper criterion that can not only reduce the computational complexity but also enhance the generalization performance is proposed to select variables as input variables for estimator.

关键词： least squares support vector machine direct thrust control wrapper criterion

Cascade Sliding Mode Variable Structure control of Permanent Magnet Synchronous Linear Servo System

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Cascade Sliding Mode Variable Structure Control of Permanent...