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Gas pressure regulator is an essential component using for the pressurized system in the aircraft. In our paper, we aim to analyze the impact of structural parameters on output pressure for the I-stage structure of a dual-stage gas pressure reducing regulator. Initially, a numerical simulation of the regulator was established and verified by a comparison of dynamic response from the deflation start of the vessel to the deflation complete. Moreover, parametric analysis of the I-stage structure for the regulator was examined to determine the primary and secondary variables and interdependencies with the Box-Behnken design method applied. Furthermore, a multi-objective optimization based on regression analysis was adopted by using the MOGA-II algorithm method, and a Pareto frontier was obtained. Results indicate that the spool mass, the leakage area of spool seal, and their interaction are the significant factors on overshoot. The overshoot presents a trend of decrease first and then increase with the mass and leakage area increase. The spool mass, the mainspring stiffness, the leakage area of spool seal, and their interactions are influential factors on stability. The stability improves with the spool mass decrease, and other factors increase. Besides, the feedback hole area has a small effect on stability. Moreover, the Pareto of the optimization indicates that the performance of the I-stage structure would be optimal when the spool mass is 23.94 g, the feedback hole area is 89.94 mm<sup>2</sup>, the mainspring stiffness is 166.76N/mm, and the leakage area of spool seal is 0.06 mm<sup>2</sup>.

Parametric Analysis of the I-Stage Structure for a Dual-Stage Gas Pressure Reducing Regulator