[an error occurred while processing this directive] [an error occurred while processing this directive] [an error occurred while processing this directive]
[an error occurred while processing this directive]

弹箭与制导学报 >

2011 , Vol. 31 >Issue 6: 146 - 148

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2011.06.027

火箭技术

喉栓体装配偏差引起流动变化及其受力分析

  • 卢明章 ,
  • 张胜敏 ,
  • 周战锋 ,
  • 何国强
展开
  • 西北工业大学固体火箭发动机燃烧、热结构与内流场国防科技重点实验室,西安 710072

卢明章(1959-),男,山东蓬莱人,高级工程师,博士研究生,研究方向:航空宇航推进理论与工程。

收稿日期: 2010-12-20

  网络出版日期: 2025-05-30

收起

The Study on the Effect of Flow and Stress Change Caused by Pintle Assembly Deviation

  • LU Mingzhang ,
  • ZHANG Shengmin ,
  • ZHOU Zhanfeng ,
  • HE Guoqiang
Expand
  • National Key Laboratory of Combustion, Flow and Thermo-structure, Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2010-12-20

  Online published: 2025-05-30

Fold

摘要

为了解决喉栓发动机中喉栓体严重烧蚀和折断的问题,文中通过数值模拟,分析了喉栓体装配偏差引起的流动变化及其对喉栓体受力的影响,得到如下结论:喉栓体沿径向受力随着平移偏差的增大而增加。喉栓体的偏转角度小于2℃时,可以不考虑径向偏差对流动的影响;偏转角度在2~4°,则需要考虑其对流动的影响;当偏转角度大于4°时,喉栓发动机推力会出现较大偏心,严重影响发动机性能,必须严加防范。

关键词： 变推力; 固体火箭发动机; 喉栓; 数值模拟

本文引用格式

卢明章 , 张胜敏 , 周战锋 , 何国强 . 喉栓体装配偏差引起流动变化及其受力分析[J]. 弹箭与制导学报, 2011 , 31(6) : 146 -148 . DOI: 10.15892/j.cnki.djzdxb.2011.06.027

Abstract

A numerical analysis was performed to study the effect of flow and stress change caused by pintle assembly deviation, providing flow details argumentation for pintle ablation and disjunction observed in experiment. The results obtained are as follow: (i) the stress along radial direction grow with increase of translation deviation; (ii) the effect of radial deviation can be neglected when it's less than 2°; when it is between 2°~4°, the effect needs to be considered; when it is more than 4°, eccentricity occurs in pintle motor, where the performance is severely jeopardized.

Key words： thrust control; solid rocket motor; pintle; numerical simulation

[an error occurred while processing this directive]

参考文献

[1]
MJ Ostrander, JL Bergmans, ME Thomas, et al. Pintle motor challenges for tactical missiles, AIAA-2000-3310 [R]. 2000.
[2]
Habchi SD, Rock SG, Hufford SG, et al. Computational fluid dynamics tools for escape systems aerodynamic analysis, ADA353481[R]. 1996.
[3]
秦飞, 何国强, 李江, 等. 可控推力发动机非稳态数值模拟[J]. 弹箭与制导学报,2006,26(1):412-413.
[4]
李娟, 李江, 王毅林, 等. 喉栓式变推力发动机性能研究[J]. 固体火箭技术,2007,30(6):505-509.
[5]
王毅林, 何国强, 李江, 等. 非同轴式喉栓变推力固体发动机试验[J]. 固体火箭技术,2008,31(1):43-46.
[6]
魏祥庚, 何国强, 李江, 等. 非同轴式喉栓变推力发动机压强响应分析[J]. 固体火箭技术,2009,32(4):409-412.
[7]
周战锋, 胡春波, 李江, 等. 变推力固体火箭发动机喉栓烧蚀试验研究[J]. 固体火箭技术,2009,32(2):163-166.
[8]
周战锋. 变推力发动机喉栓烧蚀特性研究[D]. 西安:西北工业大学,2008.
Options
文章导航

/

〈 〉

[an error occurred while processing this directive]