弹用固体姿控发动机内弹道性能实验研究  

Internal Ballistic Property of Solid Propellant Rocket Motor for Missile Attitude Control

作　　者：樊建龙[1] 唐金兰[2] 王占利[1] 赵艳红[1] 

机构地区：[1]中国航天科工集团二院210所,陕西西安710068 [2]西北工业大学,陕西西安710072

出　　处：《现代防御技术》2010年第1期32-36,共5页Modern Defence Technology

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.

关 键 词：固体火箭发动机 姿态控制 内弹道 点火 实验 

分 类 号：V439.7[航空宇航科学与技术—航空宇航推进理论与工程]