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[1]陈锐达,刘昌国,关 亮.国外单组元变推力发动机应用与关键技术[J].火箭推进,2020,46(02):1-8.
　CHEN Ruida,LIU Changguo,GUAN Liang.Application and key technologies of foreign monopropellant throttling engine[J].Journal of Rocket Propulsion,2020,46(02):1-8.
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国外单组元变推力发动机应用与关键技术

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 46 期数: 2020年02期 页码: 1-8 栏目: 专论与综述 出版日期: 2020-04-28
Title:
Application and key technologies of foreign monopropellant throttling engine
文章编号:
1672-9374(2020)02-0001-08
作者:
陈锐达1; 2; 刘昌国1; 2; 关 亮1; 2
(1.上海空间推进研究所, 上海 201112; 2.上海空间发动机工程技术研究中心, 上海 201112)
Author(s):
CHEN Ruida1; 2;  LIU Changguo1; 2;  GUAN Liang1; 2
(1.Shanghai Institute of Space Propulsion, Shanghai 201112, China; 2.Shanghai Engineering Research Center of Space Engine, Shanghai 201112, China)
关键词:
单组元;  变推力发动机;  火星软着陆;  “海盗”号;  “好奇”号
Keywords:
monopropellant;  throttling engine;  Mars soft landing;  Viking;  Curiosity
分类号:
V43
文献标志码:
A
摘要:
介绍了国外单组元变推力发动机的应用现状,阐释了单组元变推力发动机的结构和设计原理,总结了研制和改进过程中的关键技术,主要包括径向双层夹套催化床设计、径向喷注器设计、流量稳定调节技术和催化床空穴控制技术等。美国为火星软着陆研制的MR-80和MR-80B无水肼单组元变推力发动机分别应用于“海盗”号和“好奇”号着陆器下降级推进系统。MR-80发动机可实现275～2 835 N变推力调节,推力变比为10:1,比冲为205 s,呈120°均布于“海盗”号着陆器三角形基座的长边。“好奇”号下降级推进系统由2个高压氦气瓶、3个推进剂贮箱、8台单组元变推力发动机、8台单组元250 N姿控发动机、1个压力控制组件和3个推进剂控制组件组成,MR-80B发动机可产生31～3 603 N的真空推力,推力变比达到100:1,比冲范围为204～223 s。
Abstract:
The application status of the foreign monopropellant throttling engine was introduced.The structure and design principles of the monopropellant throttling engine were explained.The key technologies in the development and improvement process were summarized, mainly including the radial double-layer catalyst bed design, radial injector design, flow stability regulation technology and catalyst bed void control technology.The MR-80 and MR-80B monopropellant throttling hydrazine engines developed by the United States for soft landing on Mars were used for the “Viking” and “Curiosity” lander descent stage propulsion systems respectively.The MR-80 engine can produce a throttleable thrust range from 275 N to 2 835 N with the capability of 10:1 throttling and the specific impulse of 205 s, distributed at 120° on the long sides of the “Viking” lander triangle base.The “Curiosity” lander descent stage propulsion system consists of two high-pressure helium tanks, three propellant tanks, eight monopropellant throttling engines, eight 250 N reaction control system engines, one pressure control assembly and three propellant control assemblies.The MR-80B engine can produce the vacuum thrust range from 31 N to 3 603 N with the capability of 100:1 throttling and the specific impulse of 204～223 s.

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相似文献/References:

[1]白云峰,林庆国,金盛宇,等.过氧化氢单元催化分解火箭发动机研究[J].火箭推进,2006,32(04):15.
　Bai Yunfeng,Lin Qingguo,Jin Shengyu,et al.Research on rocket engine using hydrogen peroxide of catalytic decomposition[J].Journal of Rocket Propulsion,2006,32(02):15.

备注/Memo

收稿日期:2019-11-13; 修回日期:2019-12-17作者简介:陈锐达(1995—),男,硕士,研究领域为空间液体火箭发动机通信作者:刘昌国(1976—),男,研究员,研究领域为空间液体火箭发动机

更新日期/Last Update: 2020-04-25