摘要
高速导弹具有大气层内外作战、高速高加速、高精度光学探测等特点 ,特别是它在稠密大气层内高超声速飞行时 ,在红外探测窗口附近形成复杂的高超声速流场 ,带来严重的气动效应。文章首先介绍了光学侧窗口的主要技术指标要求和所面临的气动热环境 ,在此基础上对内冷、外冷效果进行了理论计算和风洞实验的验证。
High speed missile has following characteristics: endoatmospheric/exoatmospheric interception, high speed high acceleration, high precision detection and so on. Especially it should carry out high supersonic flight in atmosphere, thus result in a complicate high supersonic flow around its infrared detection window which leads to very serious aero\|optical effects. In this paper, the main technical specifications and aero thermal environment faced of optical side window are described, on that basis, theoretical calculation and wind tunnel experiment are conducted both on internal cooling and external cooling. \;
出处
《红外与激光工程》
EI
CSCD
2000年第3期68-72,共5页
Infrared and Laser Engineering
关键词
导弹
光学头罩
红外制导
侧窗口制冷
Missile\ \ Dome\ \ Infrared guidance\ \ Cooling technology
