Dynamic response characteristics of mirror-shaped structures in temperature gradient fields
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摘要:
飞机起飞到抵达巡航高度的过程中，外界环境温度会发生剧烈变化，由于内部摆镜转台在步进扫描工作模式下周期性快速启停，驱动电机和轴承会持续产生热量，导致转台整体形成温度梯度，进而对摆镜面形产生影响，最终影响整个光学系统的成像质量。针对这一问题，本文提出了相应分析方法。建立摆镜转台热平衡方程，并结合实际热边界条件，构建热固耦合有限元分析模型。利用该模型，可以优化摆镜转台和粘接层的设计。本文通过分析摆镜在复杂温度环境变化及步进扫描工况条件下的面形变化规律和胶层参数的关系，得到胶层在1 mm厚度时，摆镜面形最优精度RMS为43.54 nm。在地面温箱中模拟起飞时温度变化和工作状态，检测摆镜面形，检测结果与分析方法所得仿真结果相比，误差小于10%，验证该方法可用于评估摆镜面形在温度梯度场中的动态响应特性，有利于摆镜粘接层和相关部件的设计。
Abstract:During the ascent of an aircraft to its cruising altitude, the external environmental temperature changes drastically. Simultaneously, the internal stepper motors and bearings continuously generate heat due to the periodic rapid start-stop operations of the scanning mirror turntable in the step-scanning mode. These factors cause a temperature gradient across the turntable, which induces thermal deformation of the mirror surface figure and ultimately degrades the imaging quality of the optical system. To address this issue, an analysis method based on thermal-structural coupling is proposed. First, the thermal balance equation of the scanning mirror turntable was established. Combined with the actual thermal boundary conditions, a finite element analysis (FEA) model was constructed. This model was utilized to optimize the design of the mirror assembly and the adhesive layer by analyzing the relationship between the surface figure and adhesive parameters under complex thermal environments and working conditions. The optimization results show that when the adhesive layer thickness is 1 mm, the mirror achieves the optimal surface figure accuracy with a root-mean-square (RMS) value of 43.54 nm. Furthermore, ground thermal chamber tests were conducted to simulate the temperature variations and operating status during takeoff. The relative error between the experimental measurements and the simulation results is less than 10%. These results verify that the proposed method is effective for evaluating the dynamic response characteristics of the scanning mirror surface in a temperature gradient field, providing theoretical support for the design of the mirror bonding layer and related components.
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图 5 镜面温差最大时刻的结构温度场
Figure 5. Temperature field of the structure at the maximum mirror surface temperature difference
图 6 热固耦合下的结构位移云图
Figure 6. Structural displacement contours under thermal-structural coupling
图 7
1037 s时重力场叠加温度场下的镜面面形图Figure 7. Mirror surface figure at
1037 s under combined gravity and thermal fields
图 8 摆镜镜面温差随时间的变化曲线
Figure 8. Variations of the scanning mirror surface temperature difference with time
图 9 摆镜镜面温差随胶层厚度的变化曲线
Figure 9. Variations of the scanning mirror surface temperature difference with adhesive layer thickness
图 10 不同工况下的摆镜面形
Figure 10. Scanning mirror surface figure under different working conditions
表 1 摆镜转台主要材料参数
Table 1. Main material parameters of the scanning mirror turntable
部件 Material Density
$ \rho {\text{/(g/cm}}^{\text{3}}\text{)} $Young's
modulus
$ E\text{/(Gpa)} $CTE
$ \alpha {\text{/(10}}^{\text{-6}}\text{/K)} $Thermal
conductivity
$ \lambda \text{/[W/(m}\cdot \text{K)]} $摆镜 SiC 3.2 450 2.3 155 背板 4J32 8.1 150 2.4 145 结构件 AlSiC
（40%）2.89 135 11 130 
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表 2 不同工况下的摆镜面形
Table 2. Scanning mirror surface figure under different operating conditions
时间 模拟飞行 1037 s模拟飞行3 h 常温0 s 常温3 h RMS/nm 43.54 39.59 20.77 33.80
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