航空减压器输出特性回归分析及参数优化

为研究某型航空双级气体减压器设计参数对输出特性的影响规律,建立减压器AMESim模型并与测试结果对比验证;采用响应面法获得减压器设计参数与输出特性的二次回归模型,分析减压器设计参数的影响;利用带精英策略的快速非支配排序遗传算法(NSGA-Ⅱ)对二次回归模型进行优化,得到最优设计参数。响应面结果显示:反馈孔面积是影响输出压力超调量的关键因素,与阀芯密封处动泄漏面积的交互作用对超调量影响显著;阀芯质量是影响输出压力脉动强度的关键因素,与弹簧刚度、膜片刚度的交互作用对脉动强度影响显著。优化结果表明:减压器二级结构的阀芯质量、反馈孔面积、主弹簧刚度、副弹簧刚度、阀芯密封处动泄漏面积和膜片刚度分别为52.26 g、9.06 mm2、67.27 N/mm、10.68 N/mm、0.64 mm2和89.49 N/mm时输出特性达到最优,优化后输出压力超调量降低了28.72%,脉动强度降低了40.63%。 

Regression analysis and parameters optimization of output characteristics for aviation pressure reducing regulator

To study the impact of design parameters and interdependencies on an aviation dual-stage gas pressure reducing regulator’s output characteristics, the AMESim model was established and verified by comparing results with the test. A quadratic regression model of the output characteristics and design parameters was obtained by the response surface method to analyze design parameters’ influence. The quadratic regression model was optimized by using the non-dominated sorting genetic algorithm-Ⅱ (NSGA-Ⅱ) to obtain the optimal design parameters. The response surface results showed that the feedback hole area was the primary factor affecting overshoot, whose interaction with the spool seal’s dynamic leakage area had a significant impact on overshoot. The spool mass was the primary factor affecting output pressure pulsation intensity, whose interaction with the spring stiffness and diaphragm stiffness had a significant influence on pulsation intensity. The optimization indicated that the output characteristics would be optimal when the spool mass, feedback hole area, mainspring stiffness, auxiliary spring stiffness, spool seal’s dynamic leakage area and diaphragm stiffness in Ⅱ-stage structure were 52.26 g, 9.06 mm2, 67.27 N/mm, 10.68 N/mm, 0.64 mm2 and 89.49 N/mm, respectively. The output pressure overshoot was reduced by 28.72%, and the pulsation intensity reduced by 40.63%.