PDF下载 分享
[1]张家仙,朱尚龙,王燕娜.输送管壁温对膏体推进剂燃速的影响[J].火箭推进,2010,36(05):31-35.
　ZHANG Jia-xian,ZHU Shang-long,WANG Yan-na.Influence of wall temperature of feed line on pasty propellant burning rate[J].Journal of Rocket Propulsion,2010,36(05):31-35.
点击复制

输送管壁温对膏体推进剂燃速的影响

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 36 期数: 2010年05期 页码: 31-35 栏目: 研究与设计 出版日期: 2010-10-15
Title:
Influence of wall temperature of feed line on pasty propellant burning rate
文章编号:
(2010)05-0031-0５
作者:
张家仙; 朱尚龙; 王燕娜
北京航天试验技术研究所，北京 100074
Author(s):
ZHANG Jia-xian;  ZHU Shang-long;  WANG Yan-na
Beijing Institute of Aerospace Testing Technology, Beijing 100074, China
关键词:
膏体推进剂; 燃速; 传热; 输送管
Keywords:
pasty propellant;  burning rate;  heat transfer;  feed line
分类号:
V439-34
文献标志码:
A
摘要:
膏体推进剂作为一种新型特种推进剂，具有广阔的应用前景。膏体推进剂燃速直接影响发动机内弹道性能，研究输送管道壁温对推进剂燃速的影响具有重要意义。采用幂律本构方程表征膏体推进剂粘度，Arrhenius方程表征温度对粘度影响，并利用中心有限差分格式对控制方程进行离散。对恒定壁温下的膏体推进剂与管道间传热特性进行数值仿真，并进行了数值验证。结合仿真结果，并借鉴固体推进剂初温与燃速关系，分析了热管道内膏体推进剂燃速特性。结果表明：近壁面加热层厚度随入口速度增高而减小，随管径增大而增大，管内膏体推进剂平均燃速较入口温度条件下有所提高，同时，高温壁面条件下，近壁面推进剂温度高于爆发点，需要考虑管道内的防窜火措施。
Abstract:
As a new kind of propellant, pasty propellant has a bright prospect in application. The burning rate of pasty propellant has a direct influence on interior ballistics of engines, so it is very important to study the influence of wall temperature of feed line on the pasty propellant burning rate. The power-law constitutive equation and Arrhenius equation are adopted to character the viscosity of pasty propellant and the influence of temperature on the viscosity respectively. The central finite difference scheme is used to disperse the control equations. After validating the numerical method, the numerical simulation on the characteristic of the heat transfer between the pasty propellant and feed line were carried out at constant wall temperature. According to the relationship between initial temperature and burning rate of a solid propellant, the burning rate characteristics of the pasty propellant in a hot feed line were analyzed based on the numerical simulations. The result shows that the heated layer thickness close to the wall decreases with the augment of inlet velocity and increases with the augment of feed line diameter. The average burning rate of the pasty propellant in feed line is higher than that at inlet temperature. Meanwhile, as the wall is at high temperature, the propellant temperature close to the wall is higher than that of its break out point, and it is necessary to take into account the anti-backfire methods.

参考文献/References:

[1]KUKUSHKIN V I, IVANCHENKO A N. The pasty propellant rocket engine development, AIAA 1993-1754 [R]. USA: AIAA, 1993. [2]KUKUSHKIN V I. State and prospects of solid propellant rocket development, AIAA 1992-3872[R]. USA: AIAA, 1992. [3]沈海琴. 膏体推进剂火箭发动机研究进展[J]. 化学推进剂与高分子材料, 2004, 2(4): 32-35. [4]张家仙, 鞠玉涛, 周超, 等. 膏体推进剂模拟液直圆管流动特性[J]. 固体火箭技术, 2009, 32(4): 439-442. [5]周超, 鞠玉涛, 周守强, 等. 膏体推进剂供给系统新方案探索与初步验证[J]. 力学与实践, 2008, 30(5): 62-64.

备注/Memo

收稿日期：2010-０9-21；修回日期：2010-10-1７
作者简介： 张家仙（1981—），男，工程师，研究领域为液体火箭发动机试验

更新日期/Last Update: 1900-01-01