CAJ | 학술논문

大型空间遥感仪器为适应苛刻的发射和工作环境，通常要求具有很高的热、力学性能，并且对重量有严格限制。这对大口径反射镜及其支撑结构的质量、刚度和环境适应性提出了很高的要求。针对某型号Φ620 mm口径光学遥感仪器的主镜及支撑结构进行了详细的分析计算、设计和试验验证。通过对比多种支撑方式的不同特性，选择了符合仪器要求的质量轻、刚度高的中心支撑；并利用等强度原理设计了放射状轻量化形式；在支撑环节上，利用柔性材料解决了因温度变化产生的局部接触应力增加的问题，有效减小了结构对光学镜面的影响。经测试反射镜重15.2 kg，轻量化率71.2%，支撑零件3.5 kg；组件一阶模态420 Hz；面形精度优于0.03λRMS，满足仪器要求。目前该仪器已投入使用，在轨性能良好。
대형공간요감의기위괄응가각적발사화공작배경，통상요구구유흔고적열、역학성능，병차대중량유엄격한제。저대대구경반사경급기지탱결구적질량、강도화배경괄응성제출료흔고적요구。침대모형호Φ620 mm구경광학요감의기적주경급지탱결구진행료상세적분석계산、설계화시험험증。통과대비다충지탱방식적불동특성，선택료부합의기요구적질량경、강도고적중심지탱；병이용등강도원리설계료방사상경양화형식；재지탱배절상，이용유성재료해결료인온도변화산생적국부접촉응력증가적문제，유효감소료결구대광학경면적영향。경측시반사경중15.2 kg，경양화솔71.2%，지탱령건3.5 kg；조건일계모태420 Hz；면형정도우우0.03λRMS，만족의기요구。목전해의기이투입사용，재궤성능량호。
The large space remote sensing instrument has high requirements for heating and mechanical characteristics, as well as strict limitation in weight, to adapt to severe launching and working environment. Thus the mirror and supporting system is stringent in weight, rigidity and environmental flexibility. The paper analyzed, designed and demonstrated the parameters of a Φ620 mm remote sensing mirror and its mounting structure. The central mounting system was served to meet the light weight and rigidity requirements compared with the other mounting methods. Radical weight -reduction slot morphology was developed in accordance with equal strength principle. The partial contact stress would increase as temperature changed. A flexible material was utilized to solve the problem, which would mitigate the structure effect to optical mirror. The results show that the weight of mirror is 15 kg and mounting accessory is 3.5 kg, with the weight reduction rate of 71.2%. The first mode is 420 Hz;The profile accuracy of mirror is 0.03 λRMS. The technical parameters are stable and satisfied with the optical system requirements under various tests. The primary mirror project is implemented in the space and attains the expected goal.