固体火箭冲压发动机进气道出口堵盖研究  

Research on Air Intake Port Cover in Solid Rocket Ramjet

作　　者：张全[1] 兰飞强[1] 单睿子[1] 张国宏[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《航空兵器》2008年第1期31-33,45,共4页Aero Weaponry

摘　　要：简要对比了固体火箭冲压发动机不同形式进气道出口堵盖设计方案,着重对可烧蚀堵盖进行了研究,对其进行结构设计?应力分析和试验验证。结果表明,该设计方案初步满足固冲发动机对进气道出口转级控制的要求,为可烧蚀堵盖在未来先进空空导弹上的应用提供参考。Different types of air intake port cover in solid rocket ramjet were compared in brief. The structure design, stress analysis and experimental verification of consumable port cover were described in detail, and the results showed that this design basically met the need for control terms of air intake port cover in solid rocket ramjet. It was valuable for the application of the consumable port cover in air-to-air missile.

关 键 词：固体火箭冲压发动机 进气道出口 可烧蚀堵盖 空空导弹 

分 类 号：TJ760.33[兵器科学与技术—武器系统与运用工程]