基于非线性模型预测的航空发动机性能寻优控制  

Performance seeking control of aero-engine based on nonlinear model prediction

作　　者：郑前钢 金崇文 项德威 ZHENG Qiangang;JIN Chongwen;XIANG Dewei(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Shanghai Aircraft Design and Research Institute,Commercial Aircraft Corporation of China,Limited,Shanghai 201210,China;China Simulation Sciences Company Limited,Shanghai 201315,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国商用飞机有限责任公司上海飞机设计研究院,上海201210 [3]上海华模科技有限公司,上海201315

出　　处：《航空动力学报》2023年第6期1525-1536,共12页Journal of Aerospace Power

基　　金：国家自然科学基金(51906102,52176009);国家科技重大专项(J2019-Ⅱ-0009-0053,J2019-Ⅰ-0020-0019,2019-Ⅲ-0014-0058);先进航空动力创新工作站项目(HKCX2020-02-022,HKCX2020-02-027);南京航空航天大学前瞻布局科研专项(ILA220341A22,ILA220371A22)。

摘　　要：提出一种基于非线性模型预测的航空发动机性能寻优控制方法,以提升性能寻优控制的响应速度。基于风扇进口温度插值的复合推进系统动态模型建模方法建立全包线机载预测模型,以实时估计发动机性能参数及有限时域内的未来输出;基于非线性模型预测控制方法,将最大推力模式、最小油耗模式、最低涡轮温度模式3种性能寻优控制模式转化为实时动态性能寻优问题,并设计相应实时控制的性能指标,提升发动机响应速度。仿真结果表明:相比于传统方法,所提出方法建立的机载模型在3种性能寻优控制模式下有较好的控制效果且响应速度提升0.5~5s,在高空巡航工作点,最大推力模式下推力提高19.8%,最小耗油模式下耗油率下降3.12%,最低涡轮前温度模式下涡轮前温度下降17K,验证了控制方法的有效性。To improve the response speed of aero-engine performance seeking control,an aeroengine performance seeking control method based on nonlinear model prediction control was proposed.The full envelope interpolation compact propulsion system dynamic model was used as the on-board model to estimate the engine performance parameters and the future outputs of the limited time domain.With the nonlinear model prediction control method,three typical performance seeking control modes,i.e.:the maximum thrust mode,the minimum fuel consumption mode and the minimum turbine temperature mode were changed into real-time performance seeking,and corresponding real-time control performance indexes were designed to improve engine response speed.The simulation results showed that compared with the traditional method,the proposed control method had better control effect under three performance optimization control modes,and the response speed increased from 0.5 s to 5 s.At the high altitude cruising working point the thrust of the maximum thrust mode increased by 19.8%;the fuel consumption rate of the minimum fuel consumption mode dropped by 3.12%;the temperature of the minimum turbine temperature mode dropped by 17 K,helping to verify the effectiveness of the control method.

关 键 词：航空发动机控制 非线性模型预测控制 性能寻优控制 复合推进系统动态模型 机载模型 

分 类 号：V233.7[航空宇航科学与技术—航空宇航推进理论与工程]