微型航空发动机推力矢量系统建模与控制  

Modeling and control of a micro aero-engine thrust vector system

作　　者：李颖杰[1] 吴林峰[1] 李春文[1] LI Yingjie;WU Linfeng;LI Chunwen(Department of Automation,Tsinghua University,Beijing 100084,China)

机构地区：[1]清华大学自动化系,北京100084

出　　处：《清华大学学报（自然科学版）》2020年第3期198-205,共8页Journal of Tsinghua University(Science and Technology)

基　　金：国家自然科学基金面上项目(61174068).

摘　　要：以微型航空发动机推力矢量系统为对象,对先进战机缩比验证机的推力矢量系统进行了建模与控制研究。对推力矢量系统建模,采用了机理模型结合试验数据的方法,引入了气动偏角与推力损失系数,对机理模型进行了修正。控制律设计采用改进后的广义最小方差方法,在保证响应速度的同时,相比传统广义最小方差方法降低了对控制参数的敏感性。最后在全工况区间对修正后的推力矢量系统进行了控制律的仿真验证,结果表明:所建立的基于改进广义最小方差控制律在经过修正的推力矢量系统模型上,具有良好的控制效果。A micro aero-engine model was used to study the control of the thrust vector system of a sub-scaled flight demonstrator.A mechanism model was combined with experimental data to model the thrust vector system.Aerodynamic declination and thrust loss coefficients were introduced to modify the mechanism model.The control laws were based on an improved generalized minimum variance method.Simulations show that the new method improves the model sensitivity to the control parameters compared with the traditional generalized minimum variance method.A control scheme was developed for the thrust vector system with simulations showing that the predictions are acceptable for the control of sub-scaled fighters.

关 键 词：微型航空发动机 推力矢量系统 气动偏角 推力损失系数 改进广义最小方差控制 

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]