高空高速环境热光学分析及光学窗口设计  

Thermal optical analysis and design of optical window in high-altitude and high-speed environment

作　　者：范达[1,2] 明星[1] 刘昕悦[1] 王国名 郭文记[1] 黄旻[1] 董登峰[1] 

机构地区：[1]中国科学院光电研究院,北京100094 [2]中国科学院大学,北京100049

出　　处：《红外与激光工程》2016年第8期195-201,共7页Infrared and Laser Engineering

基　　金：中国科学院科研装备研制项目(yz201309)

摘　　要：为提高高空高速环境下机载光谱相机光学系统的成像性能，分析了飞行高度对光学窗口面型变形的影响，合理设计光学窗口厚度。基于有限元流固耦合、流热耦合模型，仿真高空高速环境下气动压力、气动热载荷对光学窗口的作用，分析了飞行高度对不同厚度光学窗口面型变形的影响；初步选择光学窗口厚度，利用Zernike多项式对该光窗面型变形进行拟合并输入光学软件，以MTF及波相差为评价指标，分析了光学窗口变形对光学系统成像性能的影响，最终确定合理的光学窗口厚度。结果表明：飞行器在5～30 km高空以3 Ma速度、5毅攻角飞行时，口径200 mm的光学窗口合理设计厚度为15 mm。为不同飞行高度范围光学窗口厚度的选择及优化提供了一定依据。In order to improve the imaging performance of aviation camera optical system in high-altitude and high-speed environment, an analysis of the influence on the optical window surface deformation caused by the aerodynamic pressure and aerodynamic heat loading in different flying altitudes environment was conducted, and the thickness of optical window was well designed. Based on fluid-solid interaction model and fluid-heat interaction model with finite element, how aerodynamic pressure and aerodynamic heat loadings affected optical window was simulated and how different flying environment altitude impacted on the surface deformation of different thickness of optical window was analyzed. A proper optical window thickness was chosen in the consideration of not only strength requirement but also various flying altitude circumstances to meet unique flying environment demands; and then, to judge the influence on the imaging performance of optical system caused by the surface deformation of optical window with that thickness can be accepted or not, Zemike polynomial was used to fit the surface deformation of optical window in that working condition. Putting the Zemike polynomial coefficients into optical software, taking MTF and wavefront error as assessment indexes, the influence of deformation of optical window on the imaging performance of optical system was analyzed. Finally, the appropriate thickness of optical window was gotten. The result shows when an aviate flies at a speed of 3 Ma, in the 5-30 km altitude ranges and with the 5° angle, designing its optical window thickness to be 15 mm is fitted with the 200 mm diameter. A foundation is also built in the aspect of selecting and optimizing for the thickness of optical window in different flying altitude scopes.

关 键 词：热光学分析 气动效应 光学窗口 有限元分析 成像性能分析 

分 类 号：V416.5[航空宇航科学与技术—航空宇航推进理论与工程]