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[1]程 诚,熊靖宇,周国峰,等.NASA液氧甲烷集成推进系统热真空试验[J].火箭推进,2020,46(05):10-20.
　CHENG Cheng,XIONG Jingyu,ZHOU Guofeng,et al.Thermal vacuum test of NASA’s integrated LO2/LCH4 propulsion system[J].Journal of Rocket Propulsion,2020,46(05):10-20.
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NASA液氧甲烷集成推进系统热真空试验

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 46 期数: 2020年05期 页码: 10-20 栏目: 专论与综述 出版日期: 2020-10-20
Title:
Thermal vacuum test of NASA’s integrated LO2/LCH4 propulsion system
文章编号:
1672-9374(2020)05-0010-11
作者:
程 诚; 熊靖宇; 周国峰; 林庆国
(上海空间推进研究所 上海空间发动机工程技术研究中心,上海 201112)
Author(s):
CHENG Cheng; XIONG Jingyu; ZHOU Guofeng; LIN Qingguo
(Shanghai Engineering Research Center of Space Engine, Shanghai Institute of Space Propulsion, Shanghai 201112, China)
关键词:
空间推进系统;  液氧/甲烷;  姿控动力系统;  热真空模拟;  电火花点火
Keywords:
space propulsion system;  liquid oxygen/liquid methane;  attitude control propulsion system;  thermal vacuum simulation;  electric spark ignition
分类号:
V434.1
文献标志码:
A
摘要:
为降低液氧/甲烷空间推进系统未来应用的技术风险,NASA先后实施了多个研究计划,持续不断地提升液氧/甲烷空间推进技术的成熟度水平。低温推进系统集成试验平台(ICPTA)顺利在梅溪试验站空间推进热真空舱内完成一系列热真空模拟环境下的集成热试车,标志着NASA液氧/甲烷轨姿控一体化推进技术已经具备了在轨飞行验证试验的条件。介绍了ICPTA的研制背景,采用的液氧/甲烷轨姿控一体化推进系统的构成、冷氦加温增压方案和供应管路热控方案。重点讨论了ICPTA热真空模拟试验的具体情况,以及变推力主发动机、姿控动力系统和COP点火系统等核心组件的设计方案、涉及的主要技术问题与试验结果,其成果对于未来星球着陆器的先进低温推进系统的研制具有重要参考价值。
Abstract:
In order to reduce the technical risk of liquid oxygen/liquid methane(LO2/LCH4)propulsion system for the future application, NASA has implemented several research projects to continuously improve the technology readiness level(TRL)of this cryogenic propulsion system.The Integrated Cryogenic Propulsion Test Article(ICPTA)has successfully completed a series of hot-fire tests in the space propulsion thermal vacuum chamber of Plum Brook station, NASA Glenn Research Center.It indicates that NASA’s integrated LO2/LCH4 propulsion technologies for the orbit and attitude control have the capability of in-orbit flight test.The development background of ICPTA, the composition of integrated LO2/LCH4 propulsion system, the cold helium system heating and pressurization scheme and thermal control method of feed lines are discussed in detail.Besides, the specific situation of the ICPTA thermal vacuum simulation test is mainly investigated, as well as the design principles, major technical issues and test results of the main engine, attitude control system and Coil-on-Plug ignition system.Its results are valuable for the advanced cryogenic propulsion system development of future planet lander.

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备注/Memo

收稿日期:2020-02-10; 修回日期:2020-03-14
基金项目:上海市空间发动机工程技术研究中心资助项目(17DI2280800)
作者简介:程诚(1987—),男,博士,高级工程师,研究领域为空间推进技术

更新日期/Last Update: 2020-10-20