小型固体火箭发动机低压自毁效果研究  

Study on the low-pressure self-destruction effect of an analog solid rocket motor

作　　者：刘平[1] 殷雅侠[1] 

机构地区：[1]中国航天科技集团公司四院,西安710025

出　　处：《固体火箭技术》2004年第1期22-23,36,共3页Journal of Solid Rocket Technology

摘　　要：根据导弹自毁装置低爆炸危险性要求,开展了低压自毁效果研究,进行了2发Φ260mm发动机自毁模拟试验。试验结果表明,低压状态下非点火发动机可以自毁,低压状态壳体全切开方案自毁效果及前封头切开方案自毁效果均能够满足安全自毁的要求。Based on the requirements of low explosion hazard, a study of the low-pressure self-destruction effect and two Φ260 mm solid rocket motor self-destruction simulation tests were carried out. Results show that the non-ignition motors at low-pressure can be destructed. The low-pressure self-destruction effect of both the whole-shell-cutting scheme and the forward-dome-cutting scheme can satisfy the safe self-destruction demand.

关 键 词：固体火箭发动机 交通分析 自毁装置 导弹安全系统 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程] TJ76[兵器科学与技术—武器系统与运用工程]