摘要
姿控发动机用于提高导弹机动性能。确定了固体姿控发动机实验器的设计参数,给出了可重复使用的星形和管形装药实验器结构简图,描述了试验台和试验流程。分析发动机试验数据后认为点火药量、堵盖打开压强、推进剂药形分别影响内弹道曲线的爬升段、平衡段、拖尾段;根据试验现象认为胶体密封大于42MPa的压强不可靠,连接刚度不足使推力曲线出现振荡。
Control motor is used to improve missile maneuverability. The design parameter of solid rocket motor tester for Attitude Control is ascertained, and the diagrams of star grain motor and the tube is presented. And also, the test bed and test program are depicted here. The mass of ignition charge, opening pressure of closure and grain form affect climb stage, balance stage, and drag stage of internal ballistic curve respectively. Based on the experimentation phenomena, seal is failure when the pressure over 42 MPa and the thrust curve takes on oscillator when assembly rigidity is insufficiency.
出处
《现代防御技术》
北大核心
2010年第1期32-36,共5页
Modern Defence Technology
关键词
固体火箭发动机
姿态控制
内弹道
点火
实验
solid rocket motor
attitude control
internal ballistic
ignition
experimentation
