火箭推进2024，Vol.50Issue(4)：117-125,9.DOI:10.3969/j.issn.1672-9374.2024.04.012
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
摘要
Abstract
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 and a specific impulse 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Key words
nuclear thermal rocket engine system/thermal cycle/optimization and design of system parameters/genetic algorithm分类
航空航天引用本文复制引用
何雪晴,李耀阳..核热火箭发动机系统热力循环选型及参数优化[J].火箭推进,2024,50(4):117-125,9.基金项目
民用航天"十三五"技术预先研究项目(D010304) （D010304）
