面向成本的固液火箭发动机方案设计优化

Optimization design for a cost-effective hybrid rocket motor

对固液火箭发动机(HRM)系统进行参数化建模,研究影响推力室等主要部件成本的主要因素,并建立相应成本模型。针对某运载火箭上面级固体火箭发动机CPKM的技术指标要求,采用多岛遗传算法(MIGA),开展面向成本和性能的多目标HRM设计优化。结果表明,HRM在主要功能和部分性能上可替代CPKM;相比于CPKM,HRM在同速度增量下成本下降21.0%,同成本下速度增量提升15.8%;HRM方案设计阶段中,扩张比与比冲、长度、工作时间具有较强线性关系,速度增量和成本等两个优化目标的主要影响因素是初始推力和药柱肉厚。

The parametric modeling of hybrid rocket motor （HRM） system is developed.The main factors affecting the cost of the main components such as thrust chamber are studied and the cost model is built.Using multi-island genetic algorithm （MIGA）,multi-objective design optimization of HRM considering both the cost and performance is carried out,aiming to obtain an alternative design for solid rocket motor （named CPKM） of a lunch vehicle upper-stage.The results show that HRM can replace CPKM in the main function and part of the performance.Compared with CPKM,HRM possesses a 21.0% decrease in cost at the same speed increment,and possesses a 15.8% increase in the speed increment at the same cost.In the conceptual design stage of HRM,the expansion ratio has a strong linear relationship with the specific impulse,the length and the time.The main influential factors of the two optimization targets,the speed increment and cost,are the initial thrust and the fuel grain thickness.