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[1]孙海雨,刘志让,明磊.火药起动系统双喉道管路特性分析[J].火箭推进,2010,36(01):43-49.
　Sun Haiyu,Liu Zhirang,Ming Lei.Research on gas pipeline performance of the solid powder start system[J].Journal of Rocket Propulsion,2010,36(01):43-49.
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火药起动系统双喉道管路特性分析

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 36 期数: 2010年01期 页码: 43-49 栏目: 研究与设计 出版日期: 2010-02-15
Title:
Research on gas pipeline performance of the solid powder start system
文章编号:
(2010)01-0043-07
作者:
孙海雨1; 刘志让2; 明磊3
1 西安航天动力研究所，陕西 西安710100；2 航天推进技术研究院，陕西 西安710100；
Author(s):
Sun Haiyu1;  Liu Zhirang2;  Ming Lei3
1 Xi'an Aerospace Propulsion Institute, Xi'an 710100, China; 2 Academy of Aerospace Propulsion Technolagy, Xi'an 710100, China; 3 Aviation University of Air Force, Changchun 130022, China
关键词:
液体火箭发动机; 火药起动系统; 双喉道燃气管路; 起动特性; 数值仿真
分类号:
V434
文献标志码:
A
摘要:
起动系统工作特性是液体火箭发动机研究的重点之一。对于采用火药起动器起动的液体火箭发动机，火药起动器后双喉道管路对起动系统的功效以及发动机的起动性能影响巨大。针对火药起动器以及起动器后双喉道燃气管路建立了计算模型，并通过试验数据对模型进行了验证。利用模型计算分析了火药起动器喷管喉部直径、起动器喷管扩张比、起动器及涡轮喷嘴喉径比等参数对火药起动器和燃气管路工作特性的影响。根据管路的工作特性，提出了一种双喉道燃气管路的设计方法。
Abstract:
The capability of the start system is important to liquid rocket engines. Aimed at the turbopump-fed liquid rocket engine, started by Solid Start Cartridge (SSC), performance of the powder gas pipeline with two throats behind the Solid Start Cartridge is studied in this paper. The numerical model of the powder gas pipeline is established to analyze the effect of the diameter of the solid start cartridge nozzle throat, the divergent ratio of the cartridge nozzle and the ratio of the cartridge nozzle throat to the turbine injector element throat. One way is offered to design this kind of pipelines

参考文献/References:

[1]董师颜, 张兆良. 固体火箭发动机原理[M]. 北京: 北京理工大学出版社. 1996. [2]John D, Anderson, Jr. Fundamentals of aerodynamics[M]. Maryland University. [3]潘锦珊. 气体动力学基础[M]. 西安: 西北工业大学出版社, 2007. [4]契万诺夫 B K, 别利亚耶夫 E H, 切尔瓦科夫 B B. 液体火箭发动机工作过程的数学模拟[M]. [5]李应强. 液体火箭发动机火药起动器性能设计及考核[J]. 火箭推进, 2003, 29(5): 24-29.

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备注/Memo

收稿日期：200９-０9-0３；修回日期：200９-11-05。
作者简介： 孙海雨（1983—），男，硕士，研究领域为液体火箭发动机。

更新日期/Last Update: 1900-01-01