摘要
处于气动加热环境下的红外窗口,由于强热流影响会导致窗口材料外形和光学性质发生变化,严重影响光学窗口的正常工作。以红外成像在高超声速飞行器上的应用为需求背景,针对气动加热条件下红外窗口的传热特性,建立红外窗口三维非稳态传热计算模型,利用FLUENT软件对红外窗口采用主动冷却与被动热防护效果进行了数值模拟,验证了主动冷却技术在红外窗口温度控制的可行性,并对所需的冷量进行了计算,给出了典型状态下的计算结果。
In the aero-dynamic environment,optical windows shape and optical property will be changed because of high heat flow,then the employment of the transmission of optical windows will be effected. According to the requirement of IR imaging technique applied in hypersonic aircraft,the heat transfer characteristic in optical windows under aerodynamic heating were studied and the three dimensions unsteady state heat conduction equations in unstructured were established. The effect of initiative cooling and passive heat insulation thermal protection technology were calculated with the engineering prediction software- Fluent. The feasibility of initiative cooling technology on temperature control of optical windows were validated. The capacity were caculate and some computer simulation results at classical state were presented.
出处
《真空与低温》
2015年第2期92-95,共4页
Vacuum and Cryogenics
基金
真空低温技术与物理重点实验室基金项目(9140C550211120C5501)
关键词
热防护
气动加热
红外窗口
数值模拟
thermal protection
aerodynamic heating
Optical Windows
Numerical Simulation
