高压物理学报2017，Vol.31Issue(4)：433-442,10.DOI:10.11858/gywlxb.2017.04.012
装药结构对固体火箭发动机烤燃温度分布的影响
Influence of Charge Structure on the Cook-off Temperature Distribution of Solid Rocket Motor
杨筱 1智小琦 1杨宝良 2李娟娟3
作者信息
- 1. 中北大学地下目标毁伤技术国防重点学科实验室,山西太原030051
- 2. 西安现代控制技术研究所,陕西西安 710065
- 3. 晋西工业集团有限责任公司,山西太原030027
- 折叠
摘要
Abstract
To investigate the influence of the charge structure on the cook-off characteristics of the solid rocket motor,we established 3 simplified cook-off models with 3 different charge structures,including the composite,the mono tube and the star tube,for the solid rocket motor with HTPE propellant.We conducted a cook-off test of small-size cook-off samples with HTPE propellant at the heating rate of 1 ℃/min and 2 ℃/min,and based on this experiment result,we adjusted the parameters of propellant material.By using the FLUENT software,we conducted the numerical simulation of the models' cookoff behaviors with 3 different charge structures at different heating rates (β).The results show that the charge structure has influence on the cook-off response time,the ignition point and the fast or slow cook-off division.The star tube charge leads to a critical heating rate effect,i.e.the jumping change of the ignition point,whereas the mono tube charge does not.Under the condition of this study,the critical heating rate of the composite charge motor with a star tube section is 0.2 ℃/min,and the critical heating rate of the star tube charge motor is 0.3 and 0.5 ℃/min,that is,when 0.3 ℃/min≤β≤ 0.5 ℃/min the ignition point jump changes.关键词
固体火箭发动机/装药结构/HTPE推进剂/数值模拟Key words
solid rocket motor/charge structure/HTPE propellant/numerical simulation分类
数理科学引用本文复制引用
杨筱,智小琦,杨宝良,李娟娟..装药结构对固体火箭发动机烤燃温度分布的影响[J].高压物理学报,2017,31(4):433-442,10.
