某星载天线反射罩的热应力优化设计  

Optimization Design for Thermal Stress of a Satellite-borne Antenna Reflector Structure

作　　者：于坤鹏[1] 彭超[1] 王志海[1] 

机构地区：[1]中国电子科技集团公司第三十八研究所,安徽合肥230088

出　　处：《电子机械工程》2016年第1期48-51,共4页Electro-Mechanical Engineering

摘　　要：星载天线在轨运行时主要受温度载荷的影响,其天线结构的热应力优化设计对于系统的安全性和稳定性具有重要意义。文中采用有限元仿真分析的方法研究了某星载天线单元的热应力状态,针对天线单元中反射罩底板热应力远超材料许用应力的问题,从结构形式和材料选择方面提出了多种优化方案。研究结果表明,将反射罩底板的安装位置由外围向内圈转移、将圆形安装孔改为腰形安装孔及选择热膨胀系数小的材料均可使结构的热应力得到优化。The satellite-borne antenna is mainly affected by the temperature load while it works on the orbit.The optimization design for the thermal stress of the antenna structure,therefore,becomes very important to the security and stability of the system. In this paper the thermal stress status of a satellite antenna cell is studied with the finite element method and optimization design programs are put forward from the structure type and the material selection for the problem that the thermal stress level of the antenna reflector is much larger than the allowable stress of the material. Results show that the thermal stress of the reflector structure can be optimized by changing the installation location of the reflector backplane from outside to inside,changing the circular installation holes to waist-shaped installation holes and selecting material with a larger thermal expansion coefficient.

关 键 词：星载天线 有限元仿真 热应力 优化设计 

分 类 号：V443.4[航空宇航科学与技术—飞行器设计]