含能材料2013，Vol.21Issue(1)：75-79,5.DOI:10.3969/j.issn.1006-9941.2013.01.017
点火过程对小型固体火箭发动机内弹道影响
Effects of Ignition Process on the Internal Ballistics of Small-size Solid Rocket Motor
刘赟 1王浩 1陶如意 1朱德龙2
作者信息
- 1. 南京理工大学能源与动力工程学院,江苏南京210094
- 2. 中国人民解放军73071部队,江苏新沂221400
- 折叠
摘要
Abstract
To study the effects of ignition process on interior ballistic performance of a small-size solid rocket motor,the model for interior ballistic calculation including ignition process of small-size solid rocket motor and verification plan were set up. The numerical calculations interior ballistic performance with 1.0 g,0.8 g,0,6 g and 0.4 g igniter masses were carried out. The tests of 1.0 g and 0.8 g igniter mass were done. The compute result and test data were basically consistent. The results indicated that; the effect of ignition process on interior ballistic about small-size solid rocket motor is obvious for the small combustion chamber volume. The igniting charge density and pressure peak increase .stable operating time of motor decreases as the igniter mass increases. The 1.0 g igniter mass is estimated by empirical formula,1.0 g igniter mass brings too high pressure to motor,the value of pressure reaches three times the stable pressure. 0.8 g igniter mass meets ignition reliability and general design requirements,and the maximum pressure is 27.08 MPa,and stable work time is 159 ms,and 0.8 g igniter mass is suggested for the small-size solid rocket motor.关键词
兵器发射理论与技术/小型固体火箭发动机/点火过程/内弹道/数值仿真Key words
armament launch theory and technology/ small-size solid rocket motor/ ignition process/ internal ballistic/ numerical simulation分类
军事科技引用本文复制引用
刘赟,王浩,陶如意,朱德龙..点火过程对小型固体火箭发动机内弹道影响[J].含能材料,2013,21(1):75-79,5.
