燃气压力保险机构在火箭弹引信中的应用  

The Application of Gas-pressure Safety Mechanism to the Rocket Bomb Fuze

作　　者：蒋启凌 陈兴球 

机构地区：[1]中船重工集团第七一研究所,湖北宜昌443003

出　　处：《探测与控制学报》2006年第6期25-28,39,共5页Journal of Detection & Control

基　　金：国防预研项目资助(4010709020202)

摘　　要：对于火箭弹引信,在设计时选取可利用的环境相当困难,尤其是低旋的火箭弹时间引信。将火箭发动机燃气压力的变化特征作为火箭弹特有的飞行环境,可为这类火箭弹引信的设计提供可靠的依据。火箭发动机正常点火后,火箭发动机燃气压力会经历一个骤升、持续和骤降的过程。分析了火箭发动机燃气压力骤升、持续和骤降的表现特征,并详细地介绍了利用这些特征工作的燃气压力保险机构及其常有的结构形式,对这些机构的工作特征进行了具体的安全性分析和比较,在此基础上根据实践经验对于设计中应注意的密封环节提供了具体的技术方案,结合试验验证,提出了廉价有效的隔热措施。It is rather difficult to select environment available to design for rocket bomb fuze, especially low- speed rotating rocket bomb time fuze. The gas -pressure variation characteristics of the rocket motor being treated as the rocket＇s peculiar flight environment provides a rdliable basis to the desing of the rocket bomb fuze. After the motor is normally ignited, the gas pressure of the motor will experience a process form sharp rise, keeping to sharp drop. In this article, the presenting features of sharp rise, keeping and sharp drop of the gas - pressure of the rocket motor are analyzed, the gas - pressure safety mechanism which utilizes these features to work and its common configuration are introduce in detail and a specific safety analysis and comparison of the working features of the configuration are conducted. On this basis, a specific technical scheme is provided to the sealing link that should be paid attention to according to practical experience and low -cost effective heat insulation measures, which are instructional to the application and design, are presented through the test validation.

关 键 词：火箭弹 火箭发动机 引信 燃气压力 保险机构 

分 类 号：TJ415[兵器科学与技术—火炮、自动武器与弹药工程] TJ430.3