航天推进技术研究院主办
[1]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(04):117-125.[doi:10.3969/j.issn.1672-9374.2024.04.012]
HE Xueqing,LI Yaoyang.Thermal cycle selection and parameter optimization of nuclear thermal engine system[J].Journal of Rocket Propulsion,2024,50(04):117-125.[doi:10.3969/j.issn.1672-9374.2024.04.012]
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HE Xueqing,LI Yaoyang.Thermal cycle selection and parameter optimization of nuclear thermal engine system[J].Journal of Rocket Propulsion,2024,50(04):117-125.[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
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
50
期数:
2024年04期
页码:
117-125
栏目:
目次
出版日期:
2024-08-25
- Title:
- Thermal cycle selection and parameter optimization of nuclear thermal engine system
- 文章编号:
- 1672-9374(2024)04-0117-09
- Keywords:
- nuclear thermal rocket engine system; thermal cycle; optimization and design of system parameters; genetic algorithm
- 分类号:
- V11
- 文献标志码:
- A
- 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。
- 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.
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相似文献/References:
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备注/Memo
收稿日期:2023- 07- 31修回日期:2024- 01- 25
基金项目:民用航天“十三五”技术预先研究项目(D010304)
作者简介:何雪晴(1994—),女,硕士,工程师,研究领域为液体火箭发动机系统设计。
更新日期/Last Update:
1900-01-01