机载激光扩束系统主反射镜组件设计试验

Design of the Primary Mirror Assembly for an Airborne Laser Beam Expander System

针对某机载平台对设备结构性能提出的严格要求,提出了一种应用于机载激光扩束系统的轻小型主反射镜组件设计方法。由激光扩束系统的光学指标分析出发,得到主反射镜的机械设计性能约束;结合机载平台环境要求开展了反射镜的支撑方案设计和各部件的轻量化设计;并对所设计的结构组件实施了工程分析,基于此进行了各零部件的加工装配和组件的试验检测。结果显示:组件内部粘接部分的安全系数达到2.7;组件在光轴水平、光轴竖直以及5℃均匀温升三种工况下的镜面面形误差RMS值均优于设计要求的λ/50(λ=632.8 nm);在随机振动环境下,镜面敏感点的加速度响应RMS值相比输入条件的比值最大为6.29,力学性能良好;试验检测结果显示镜面误差RMS值仅0.018λ。结果表明所设计的结构是合理可行的,满足机载平台应用要求。

In terms of the strict design requirements on the stability and mass of equipment for the airborne platform,an opto-mechanical structure design method of a lightweight primary mirror assembly is proposed.In this study,based on the analysis of the optical index of the laser beam expander system,the mechanical design index of the primary mirror is obtained.Combined with the environment requirements of the airborne platform,the support scheme of the mirror and lightweight design are studied.The engineering analysis and test of the primary mirror assembly are carried out.The results show that the safety factor of the bonding strength between internal components reaches 2.7.The RMS values of the mirror surface shape error are better than λ/50(λ=632.8 nm)in the horizontal state of optical axis,the vertical state of optical or the uniform 5℃ temperature rise.In the random vibration environment,the amplification factor of the acceleration response RMS value of the mirror sensitive point is 6.29.The surface shape error test is carried out,and the RMS value of the surface error is 0.018λ.These results demonstrate that the mirror assembly design method is reasonable,meets the design requirements.It has important guiding significance for the similar structural design.