Variable-geometry control method for variable-cycle engine considering aircraft thermal resistance

Abstract

This invention relates to the field of aero-engine control technology and discloses a variable geometry control method for a variable-cycle engine considering aircraft thermal tolerance. The method includes establishing a simulation model encompassing the fuel thermal management system and the adaptive variable-cycle engine. Flight boundary conditions are obtained by discretizing the flight process into typical flight operating points. The seven-dimensional variable geometry parameters of the adaptive variable-cycle engine are set as optimization variables, and the minimization of engine fuel consumption rate and fuel tank temperature rise rate are set as objective functions, utilizing safety physical boundaries. A multi-objective optimization algorithm is employed, and under the premise of satisfying aerodynamic constraints, iterative optimization is performed using the simulation model. The non-dominated solution set is calculated, and a comprehensive evaluation function is constructed through normalization and dynamic weight allocation. The optimal control point with the minimum function value is extracted. Finally, a control scheduling table corresponding to the entire flight profile is generated. Based on this, the controller issues variable geometry adjustment commands, achieving synchronous and coordinated control of engine aerodynamic performance and fuel thermal load.

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