固体火箭发动机水射流清理工艺的多目标优化

摘要

为兼顾固体火箭发动机水射流清理工艺的安全性、高效性、环保性，在水射流清理实验和废水收集实验的基础上，以清理作业中推进剂质量损失速率、废水产生速率为优化目标，以射流压力、靶距、喷嘴直径、单次清理时间为变量并加以约束条件，建立了固体火箭发动机水射流清理工艺的多目标优化方法。利用代理模型技术建立了推进剂质量损失速率的代理计算模型和废水产生速率的理论计算模型，使用非支配排序遗传算法（ NSGA-Ⅱ）求得了 Pareto 优化解集。该优化解集可为不同情况下的水射流清理工艺设计中推进剂质量损失速率和废水产生速率的匹配提供多种方案。用推进剂质量损失速率和废水产生速率的最佳匹配，由HTPB 推进剂单位质量损失所造成的废水产生量仅为14．25 mL·g -1。%To achieve a balance among safety,efficiency and environment-friendliness of waterjet cleaning process of solid rocket motor,on the basis of waterjet cleaning experiments and wastewater collection experiments,a multi-objective optimization meth-od for waterjet cleaning process of solid rocket motor was established with propellant massloss rate and wastewater generation rate as the optimization objectives,and waterjet pressure,target distance,nozzle diameter and single cleaning time as the variables with constrained conditions. The calculation models of propellant massloss rate and wastewater generation rate were established with agent modeling technology,and Pareto optimal solution set was obtained by the non-dominated sorting genetic algorithm (NSGA-Ⅱ). Results show that the optimal solution set can offer a variety of programs for the matching between propellant mass-loss rate and wastewater generation rate in waterjet cleaning process design under different conditions. With the best matching between them,the wastewater production caused by HTPB propellant′s unit massloss is only 14. 25 mL·g -1 .