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[1]徐辉,易琪,钟徐,等.1 0kN双向摇摆再生冷却发动机技术研究[J].火箭推进,2009,35(05):8-12.
　Xu Hui,Yi Qi,Zhong Xu,et al.Research on 1 0kN gimbaled regeneratively cooled engine[J].Journal of Rocket Propulsion,2009,35(05):8-12.
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1 0kN双向摇摆再生冷却发动机技术研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 35 期数: 2009年05期 页码: 8-12 栏目: 研究与设计 出版日期: 2009-10-30
Title:
Research on 1 0kN gimbaled regeneratively cooled engine
作者:
徐辉; 易琪; 钟徐; 金广明
上海空间推进研究所，上海，200233
Author(s):
Xu Hui; Yi Qi; Zhong Xu; Jin Guang Ming
Shanghai Institute of Space Propulsion，Shanghm 200233，China
关键词:
液体火箭发动机; 再生冷却; 摇摆; 热试车
Keywords:
iquid rocket engine; regenerative cooling; gimbaled chamber; firing test
分类号:
434.14
文献标志码:
A
摘要:
介绍了10kN双向摇摆发动机的主要技术方案和关键技术。对涂层和边区余氧 系数等影响因素进行了传热计算及分析，获得了再生冷却身部的气壁温、液壁温和热流密度 的轴向分布曲线，指出了发动机身部可靠冷却的边界工况。针对两种推进剂(N20+／MMH、 N204／UDMH)，设计了喷注压降和流量不同的两种喷注器方案，地面热试车表明，两种喷注器 方案燃烧稳定。其燃烧效率相当。可达95％～96％。发动机多次地面试验研究验证了发动机设 计方案的可行性。
Abstract:
Main concept and key technologies for a 1 0kN gimbaled rocket engine were intro— duced in this paper．Heat transfer calculation and analysis were performed for main influencing fac— tors such a8 coating and peripheral excess oxidizer coefficient．Axial distribution curves of gas-side wall temperature，liquid-side wall temperature and heat flux were obtained．Boundary condition for engine combustion chamber cooling was established．Two types of injectors with different pressure drops and flow rates for two kinds of propellants combination(N20JMMH；N204／UDMH)were designed．Ground hot tests indicated that the two injectors operated well with high combustion effi— ciency of 95％～96％，which proved the reasonability and feasibility of the engine design concept．

参考文献/References:

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备注/Memo

收稿日期：2009—07—26；修回日期：2009—08—13。 作者简介：徐辉(1979一)，女，工程师，研究领域为液体火箭发动机技术。

更新日期/Last Update: 1900-01-01