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[1]刘晓伟,姚明明,李佳明,等.轻质高比冲1 000 N双组元轨控发动机研制[J].火箭推进,2015,41(04):8-12.
　LIU Xiaowei,YAO Mingming,LI Jiaming,et al.Development of 1 000 N bipropellant orbit control engine with light weight and high specific impulse[J].Journal of Rocket Propulsion,2015,41(04):8-12.
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轻质高比冲1 000 N双组元轨控发动机研制

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 41 期数: 2015年04期 页码: 8-12 栏目: 研究与设计 出版日期: 2015-09-30
Title:
Development of 1 000 N bipropellant orbit control engine with light weight and high specific impulse
作者:
刘晓伟; 姚明明; 李佳明; 曹 晶; 曲海军
西安航天动力研究所，陕西 西安 710100
Author(s):
LIU Xiaowei;  YAO Mingming;  LI Jiaming;  CAO Jing;  QU Haijun
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
关键词:
轨控发动机; 高比冲; 陶瓷基复合材料
Keywords:
orbit control engine;  high specific impulse;  ceramic based composite
分类号:
V434-34
文献标志码:
A
摘要:
介绍了空间飞行器用轻质高比冲1 000 N轨控发动机的研制过程。为了实现高比冲的目标，从喷注器选型、喷注对设计、冷却设计等方面采取措施，并通过工作过程仿真，对集液腔结构、冷却液百分比和特征长度等参数进行优化设计。发动机身部选取了陶瓷基复合材料（Cf/SiC），利用该材料密度低的特点实现发动机轻质化要求。发动机经过了地面热试车考核，燃烧室外壁温、燃烧效率的仿真值均与测量值基本相当。其中，燃烧效率约96.6％，真空比冲约3 169 m/s，长程试车后发动机结构完好。
Abstract:
The development process of the 1 000 N bipropellant orbit control engine with light weight and high specific impulse is introduced. In order to achieve high specific impulse, some measures (selection of suitable injector, injector pair design and cooling design) is adopted. In addition, the design of bipropellant collection cavity, cooling liquid percentage and characteristic length are optimized based on simulation of engine-working process. The ceramic based composite reinforced by carbon fibers (Cf/SiC) is selected for body of the engine due to its characteristic of low density. The ground hot-fire testing is executed. The engine test shows that calculated and measured values of the chamber exterior wall temperature and combustion efficiency are almost same. The combustion efficiency is 96.6% and vacuum specific impulse is 3 169 m/s. After long hot-fire testing, the structure of this engine was still in good condition.

参考文献/References:

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备注/Memo

收稿日期：2015-01-23；修回日期：2015-06-17 作者简介：刘晓伟（1978—），男，高级工程师，研究领域为液体火箭发动机设计

更新日期/Last Update: 1900-01-01