星载单端固定长杆型载荷的结构优化设计  

A Mechanical Optimization Design for Long-Pole-Shaped Payloads Fixed at One End

作　　者：董永进[1,2] 关燚炳[1,2] 安雅雅[1,2] 

机构地区：[1]中国科学院国家空间科学中心,北京100190 [2]天基空间环境探测北京市重点实验室,北京100190

出　　处：《航天制造技术》2016年第5期21-23,27,共4页Aerospace Manufacturing Technology

摘　　要：提出了一种适用于卫星上搭载的单端固定安装且具有长杆形状的有效载荷的结构设计方案。此种形状以及固定安装方式的载荷一般具有较低的谐振频率,很难通过力学环境模拟试验。本文提出的结构设计方案在多次失败方案基础上以及有限元分析的辅助下进行了针对性的优化,避免了结构尺寸突变带来的应力集中,对应力过大的部位进行了局部加固,在材料选择方面创新的采用了碳纤维复合材料,经过试验验证,选择此种材料以及设计的载荷能够很好地通过力学环境模拟试验,且相比于金属材料制造来说,载荷的某些力学特性更加优越。In this paper a mechanical optimization design for the long-pole-shaped astronomic payloads fixed at one end is proposed. Usually this type of payloads have a low resonant frequency. So it is hard for it to pass the dynamic environment testing. With the FEA result, the new optimization design can escape from the stress concentration by avoiding acute dimension change. At the same time the weak part is reinforced to avoid the failure. Innovatively the carbon fiber is used to manufacture the main part of the payloads. The dynamic enviroment testing proved that it has more outstanding dynamic features compared with metals.

关 键 词：单端固定 长杆型载荷 结构设计 优化设计 

分 类 号：V423.4[航空宇航科学与技术—飞行器设计]