涡轴发动机模型修正及控制方法研究

发布时间：2017-12-28 21:36

本文关键词：涡轴发动机模型修正及控制方法研究　出处：《南京航空航天大学》2016年硕士论文　论文类型：学位论文

【摘要】：高精度的涡轴发动机模型是涡轴发动机控制系统设计的基础,提高模型精度使其与试车数据相匹配是极其重要的研究内容。而先进的控制规律可以提升涡轴发动机的功率响应速度以及转速抗干扰能力,是涡轴发动机控制系统设计的重点与难点。为此本文从某型涡轴发动机模型与实验数据的匹配以及发动机控制规律两个方面开展研究工作。在模型匹配方面,首先对部件级模型的设计点精度进行修正。基于变适应度函数的微分进化算法,对各部件特性修正系数进行优化,以达到减小总体建模误差,提高模型精度的目的。采用变步长牛顿-拉夫逊迭代算法,基于平衡方程残差范数变化趋势来改变牛顿-拉夫逊迭代算法的步长,提高了模型的收敛性和收敛速度。在稳态模型的基础上,采用微分进化算法对核心部件的引气系数、非转动部件的总压恢复系数以及各转动部件的特性进行了修正,使修正后的模型在设计点的输出与试车数据匹配精度满足要求。在模型非设计点匹配方面,采用了两种方法进行修正。一种是对非设计点的相邻两条转速线进行修正达到多点匹配,另外一种是采用修正因子函数的方法,以已匹配的非设计点换算转速线为基准,对非设计点进行修正。在修正完成的发动机模型基础上,针对功率控制以及转速控制系统设计控制器。基于小扰动法建立状态变量模型,利用DE(微分进化)算法进行模型元素的求解,提高了模型的建模精度。基于状态变量模型,针对功率控制设计了基于LMI(线性矩阵不等式)方法的H_2/H_∞控制器,针对转速控制设计了基于多目标优化算法的H_2/H_∞控制器求解。论文通过仿真验证了算法的有效性。
[Abstract]:High precision turboshaft engine model is the basis of turboshaft engine control system design. Improving the accuracy of the model and matching it with the trial data is a very important research content. The advanced control law can improve the power response speed and speed anti-interference capability of turboshaft engine, and is the key and difficult point of turboshaft engine control system design. In this paper, the research work is carried out from two aspects: the matching of the model of a certain type of vortex shaft engine and the experimental data and the control law of the engine. In the aspect of model matching, the precision of the design point of the component level model is corrected. Based on the differential evolution algorithm of variable fitness function, the correction coefficient of each part is optimized, so as to reduce the overall modeling error and improve the accuracy of the model. The variable step Newton lahson iteration algorithm is used to change the step length of the Newton Ravson iterative algorithm based on the change trend of the residual norm of the balance equation, which improves the convergence and convergence speed of the model. Based on the steady-state model, the total pressure of air entraining coefficient, non rotating parts of the differential evolution algorithm on the core components of the recovery coefficient and the characteristics of the rotating parts is modified, the modified model in the design of output point with test data, the accuracy meets the requirements. In the non design point matching of the model, two methods are used to modify the model. One is to modify the two adjacent speed lines of non design points to achieve multi point matching. The other one is to use modified factor function to modify the non design points based on the matching non design point converted speed line. On the basis of the modified engine model, the controller is designed for the power control and the speed control system. Based on the small perturbation method, the state variable model is built, and the DE (differential evolution) algorithm is used to solve the model element, and the modeling accuracy is improved. Based on the state variable model, a H_2/H_ infinity controller based on LMI (linear matrix inequality) method is designed for power control. A H_2/H_ objective controller based on multi-objective optimization algorithm is designed for speed control. The validity of the algorithm is verified by simulation.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V235.12

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