飞发一体化架构下航空发动机控制裕度定义及评估准则研究  

Research on the Definition and Evaluation Criteria of Aeroengine Control Margin under the Integrated Flight-Propulsion Architecture

作　　者：陈佳杰 王继强 张海波[4] 陈新民 牛伟[5] Chen Jiajie;Wang Jiqiang;Zhang Haibo;Chen Xinmin;Niu Wei(Qianwan Institute of Ningbo Institute of Materials Technology and Engineering,Ningbo 315336,China;Ningbo Institute of Materials Technology and Engineering of the Chinese Academy of Sciences,Ningbo 315201,China;Zhejiang Engineering Research Center for Special Aircraft,Ningbo 315336,China;Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;AVIC Aeronautics Computing Technology Research Institute,Xi’an 710119,China)

机构地区：[1]宁波杭州湾新材料研究院,浙江宁波315336 [2]中国科学院宁波材料技术与工程研究所,浙江宁波315201 [3]特种飞行器浙江省工程研究中心,浙江宁波315336 [4]南京航空航天大学,江苏南京210016 [5]航空工业西安航空计算技术研究所,陕西西安710119

出　　处：《航空科学技术》2024年第12期78-86,共9页Aeronautical Science & Technology

基　　金：航空科学基金(201919052001)。

摘　　要：针对传统的裕度评估标准难以直观地体现飞机端干扰量对发动机的控制耦合性问题,在飞发一体化架构下开展了航空发动机控制裕度及相应的评估准则研究。基于一种可以在有限频域内采用几何图解法进行控制性能改进的控制理论“几何设计法”,本文提出一种新的发动机控制裕度定义方法及评估准则,包括构造满足需求控制裕度的控制器求解方法、评估对比不同控制器的控制裕度和评估固定结构控制器的控制裕度。以某型宽速域组合动力(TBCC)航空发动机作为研究对象,在亚声速巡航典型工况下,基于几何设计理论所设计的控制器,控制性能可以达到控制裕度理论极限的99.61%。部件级模型仿真结果表明,相比于传统比例积分(PI)控制器,基于几何设计理论所设计的控制器的推力控制裕度和综合控制裕度分别提升了7.3%和5.9%,验证了所定义的控制裕度及其评估准则在解决飞发一体控制耦合性问题的有效性。In response to the difficulty of traditional margin evaluation standards to intuitively reflect the coupling problem of aircraft disturbance on aeroengine control,research on aeroengine control margin and corresponding evaluation criteria is carried out under the framework of integrated flight-propulsion architecture.A novel method for defining aeroengine control margin and evaluation criteria is proposed based on a control theory called geometric design method that can improve control performance using geometric methods in a finite frequency domain.This includes constructing a controller solution method that meets the required control margin,evaluating and comparing control margins of different controllers,and evaluating control margins of fixed structure controllers.Taking a certain type of turbine-based combined cycle(TBCC)engine as the research object,under the typical subsonic cruise condition,the controller designed based on geometric design method can achieve 99.61%of the control margin theoretical limit.The simulation results based on the TBCC component level model show that compared to the traditional proportional integral(PI)controller,the thrust control margin and comprehensive control margin of the controller designed based on geometric design method have increased by 7.3%and 5.9%,respectively,verifying the effectiveness of the defined control margin and its evaluation criteria in solving the coupling problem of integrated flight-propulsion control.

关 键 词：飞发一体化 涡轮基组合动力 控制裕度 几何设计法 评估准则 

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]