摘要
针对亚声速情况下飞机机动飞行过程中大攻角状态下进气道和发动机之间流量难以匹配而导致推进系统推力损失较大的问题,提出了一种进气道/发动机一体化多变量控制方法。基于进气道/发动机一体化模型推导出了带有辅助进气门的进气道/发动机共同工作方程,并分析了共同工作原理,选用进气道和发动机的共同工作点位置作为进气道反馈量,增广到状态量中以保证进气道和发动机流量匹配。为了抑制攻角等因素引起的推力瞬间损失,在控制回路中加入了进气道限制保护环节修正控制指令,基于H_(2)/H_(∞)算法设计了进气道/发动机多变量控制器。在发动机非线性部件级模型上开展了全数字仿真验证,仿真结果表明,与常规的进气道开环控制结构相比,所提出的进气道/发动机一体化多变量控制具有良好的动态性能,并且在攻角变化情况下推力损失更小。
Aiming at the problem that the flow between inlet and engine is difficult to match at high angle of attack in subsonic maneuvering flight,resulting in large thrust loss of propulsion system,a multivariable inlet/engine integrated control method is proposed.Based on the inlet/engine integration model,the common working equation of inlet/engine with auxiliary inlet valve is derived,and the common working principle is analyzed.The common working point position of inlet and engine is selected as the inlet feedback quantity and extended to the state quantity to ensure the flow matching between inlet and engine.In order to suppress the instantaneous loss of thrust caused by angle of attack and other factors,the inlet restriction protection link is added to the control loop to modify the control command,and the inlet/engine multivariable controller is designed based on H_(2)/H_(∞) algorithm.The full digital simulation verification experiments have been carried out on the engine nonlinear component level model.The simulation results show that compared with the conventional inlet open-loop control structure,the proposed inlet/engine integrated multivariable control has good dynamic performance and less thrust loss under the change of angle of attack.
作者
唐杰
鲁峰
周文祥
黄金泉
TANG Jie;LU Feng;ZHOU Wen-xiang;HUANG Jin-quan(College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2023年第1期243-252,共10页
Journal of Propulsion Technology
基金
两机重大专项基础研究项目(2017-Ⅴ0004-0054)。
