Design Method of Mode Transition Control Law for TBCC Engine

Yongliang Zhang, Lingcong Nie, Ting Yu, F. Lu, Jin-Quan Huang
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Abstract

In this paper, a mathematical model of tandem turbine-based combined cycle (TBCC) engine is studied based on the component-level concept, and then the mode transition is focused on with the controller design. The aerodynamic thermodynamic equations are drawn out in the establishment of engine component-level model, and Newton-Raphson method is applied to solve the common operation equations. In addition, the modal transition process is simulated and analyzed, the mode transition operating point of the TBCC engine is determined in the flight trajectory. Thus, the combined engine modal transition control quantity adjustment plan is formulated. Finally, a multi-variable controller based on neural network estimation and inverse control is designed and verified in the TBCC simulation.
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TBCC发动机模态过渡控制律设计方法
本文基于部件级的概念,研究了串列涡轮联合循环发动机的数学模型,并在此基础上重点研究了串列涡轮联合循环发动机的模态转换和控制器设计。在建立发动机部件级模型时,建立了气动热力学方程,并采用牛顿-拉夫森法求解了常见的运行方程。此外,对TBCC发动机的模态过渡过程进行了仿真分析,确定了TBCC发动机在飞行轨迹上的模态过渡工作点。据此,制定了组合发动机模态过渡控制量调整方案。最后,设计了一种基于神经网络估计和逆控制的多变量控制器,并在TBCC仿真中进行了验证。
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