Research on optimization of uncertainty analysis for reliability of aircraft propulsion system

This study investigates the propulsion system of hypersonic aircraft, addressing the limitations of traditional deterministic design optimization approaches that neglect the influence of uncertainties. To overcome these limitations, research on reliability-based multidisciplinary design optimization is conducted. By thoroughly analyzing uncertainty theory alongside multidisciplinary design optimization methodologies, the validity of the suggested method is illustrated through the optimization of engineering case studies using the multidisciplinary optimization platform ISIGHT. The parameters of various propulsion system components are parameterized and categorized according to disciplinary divisions. Design variables and performance metrics are defined, and deterministic as well as reliability-based optimization processes are carried out using MATLAB and ISIGHT. The findings show that after reliability-based optimization, the total pressure recovery coefficient is enhanced, whereas the system mass rises.The thrust generated by the combustion chamber is slightly reduced, yet the reliability of the constraint conditions exceeds 98%. These outcomes significantly enhance both the reliability and accuracy of the propulsion system design scheme, offering a valuable reference for future optimization of hypersonic aircraft propulsion systems.