Optimization and Evaluation of Supersonic Civil Aircraft Propulsion System Scheme Design Driven by Multiple Evaluation Indicators

In response to the issues of long design cycle and relatively independent design process and indicator evaluation in traditional propulsion system design method, this paper establishes a method for rapid optimization design and evaluation driven by multiple evaluation indicators. Starting from the analysis of the engine performance impossibility triangle, an EPN (Essential-Preferential-Noteworthy) hierarchical framework of indicator importance is proposed in the initial design stage, which classifies numerous evaluation indicators according to their importance. During the design process, a multi-objective optimization model is established by combining genetic algorithm with the EPN framework. This integrates the trade-off relationships of different indicators into the optimization design process, achieving rapid and automated optimization of system scheme. In the scheme evaluation phase, the Analytic Hierarchy Process (AHP) is employed to quantify the weights of various evaluation indicator, and the final design scheme is determined based on normalized comprehensive assessment values. Finally, this method is applied to the design of a new-generation propulsion system for the Concorde aircraft. The design results indicate that the proposed optimization design and evaluation method effectively meets the requirements of scheme design under multiple evaluation criteria. Compared to the original Concorde propulsion system, the new scheme reduces fuel consumption and takeoff nozzle exit jet velocity by 28.15% and 34.33% while meeting thrust requirement, thereby significantly improving the aircraft’s economy and environmental performance.