Optimization design of serpentine nozzle and load transfer <?A3B2 pi6?>structure of rear fuselage web plate

<?A3B2 tlb=1.25h?>The web plate structure of the serpentine nozzle exhibits good stiffness and low stress <?A3B2 tlsb=-.02w?>concentration, making it a typical connection form between the nozzle and the rear fuselage. However, the layout and size design of the web plate are deeply coupled with the thermal stress and deformation of the nozzle, leading to significant structural redundancy. To simultaneously meet the requirements of nozzle structural strength and lightweight design, a multi-objective optimization design method was studied for the layout and size of the web plate-type reinforcement structure with equal wall thickness in the serpentine nozzle, and a topological optimization research was also conducted under aerothermal loads to address the force transfer redundancy of the web plate structure. The results show that the deformation of the serpentine nozzle mainly manifests as global upward deformation at the lip of the nozzle exit section and local thermal warping <?A3B2 tlsb?>at the rear of the nozzle convergence section. The variation in the axial layout position of the web plate has a greater impact on the deformation than the change in the structural thickness of the web plate. After multi-objective optimization, the maximum deformation of the structure is reduced by 26%, and the total weight of the structure is reduced by 43%. After topological optimization, the stress level of the web plate is reduced by 23%, and the total weight of the structure is reduced by 47%. This indicates that there is significant optimization design space for the traditional web plate-type reinforcement structure in serpentine nozzles.