变马赫数下的内并联式TBCC模态转换控制  

Mode transition control of over-under TBCC under variable Mach number

作　　者：于华锋[1] 郭迎清[1] 王佳美 YU Huafeng;GUO Yingqing;WANG Jiamei(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China)

机构地区：[1]西北工业大学动力与能源学院,西安710129

出　　处：《北京航空航天大学学报》2024年第11期3456-3462,共7页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家科技重大专项(J2019-V-0003-0094)。

摘　　要：随着高超声速技术的发展,涡轮基组合循环(TBCC)发动机越来越受到重视。模态转换是制约TBCC发动机投入实用的障碍之一,有必要对这个过程中的控制方式进行研究。提出一种模型综合方式,实现一维进气道、冲压发动机及涡轮发动机的综合迭代,基于MATLAB/Simulink环境构建了适用于控制系统设计的TBCC模型。对单模态控制系统进行分析,在最小改动原则上提出模态转换控制器架构;通过线性矩阵不等式(LMI)工具给出控制器设计方法。给出变马赫数仿真的意义,通过2.5~3马赫数下的模态转换仿真验证了控制系统。仿真结果表明:控制系统可以保证TBCC发动机处于安全状态,变马赫数模态转换阶段推力波动小于4.2%。With the development of hypersonic technology,turbine-based combined cycle(TBCC)engines have received much attention.Mode transition is one of the obstacles that restrict the application of TBCC engines.Therefore,it is necessary to study the control methods in this process.First,a model synthesis method was proposed,which realized the comprehensive iteration of a one-dimensional inlet,ramjet,and turbine engine.A TBCC model suitable for control system design was constructed based on the MATLAB/Simulink environment.Then,the single mode control system was analyzed,and a mode transition controller structure was proposed following the principle of minimal modification.The controller design method was developed by linear matrix inequality(LMI)tool.Finally,the significance of variable Mach number simulation was illustrated.The control system was verified by mode transition simulation at Mach number of 2.5–3.The simulation result shows that the control system can ensure the safety of TBCC engines,and the thrust fluctuation is less than 4.2%in the variable Mach number mode transition stage.

关 键 词：涡轮基组合循环发动机 模态转换 变马赫数 控制系统设计 多变量控制 

分 类 号：V233.75[航空宇航科学与技术—航空宇航推进理论与工程] TB553[理学—物理]