核热火箭发动机系统热力循环选型及参数优化  

Thermal cycle selection and parameter optimization of nuclear thermal engine system

作　　者：何雪晴 李耀阳 HE Xueqing;LI Yaoyang(Beijing Aerospace Pr Beijing Aerospace Propulsion Institute,Beijing 100076,China)

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《火箭推进》2024年第4期117-125,共9页Journal of Rocket Propulsion

基　　金：民用航天“十三五”技术预先研究项目(D010304)。

摘　　要：针对核热火箭发动机系统方案展开深入研究,提出了3种液体火箭发动机系统循环选型和3种系统流路设计方案。以高比冲和经济性为优化目标进行系统热力循环选型和系统参数优化设计,最终选择了一种基于带驱动元件金属陶瓷(CERMET)快堆的闭式膨胀循环高性能系统方案。采用遗传算法进行该优化方案下系统参数最优化分析,结合工程实际最终得到室压5 MPa,涡轮前温度400 K,比冲大于900 s的优化设计系统方案,并对相关组合件理论特性进行分析,提出未来组件优化方向,为后续核热火箭发动机设计提供基础。Based on the further research of nuclear thermal rocket engine system,three types of thermal cycle selection and flow path design of liquid rocket engines have been proposed.Aiming to obtain the high specific impulse and economy,a closed-expansion-cycle based on CERMET with a driver was finally selected.The genetic optimization algorithm was adopted to optimize the engine system.Combined with the engineering practice,the final scheme is obtained with a chamber pressure of 5 MPa,a turbine inlet temperature of 400 K,the and a specific impulse of greater than 900 s.In addition,the theoretical characteristics of related components are analyzed and the future component optimization direction is proposed,which provides the basis for the subsequent design of nuclear thermal rocket engine.

关 键 词：核热火箭发动机系统 热力循环 系统参数优化设计 遗传算法 

分 类 号：V11[航空宇航科学与技术—人机与环境工程]