Design Method of Mode Transition Control Law for TBCC Engine

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.