随机振动环境下太阳翼驱动机构强度安全性设计分析研究

Research on Strength Safety Design for Solar Array Driving Mechanism in Random Vibration Environment

随机振动环境是航天器结构强度设计时考虑的主要因素,等效的准静态设计方法是航天器结构强度设计时采用的主要方法。在研究了用Miles公式法、试验规范法和全频段功率谱密度法计算峰值响应加速度的基本原理和处理方法的基础上,将直接影响航天器结构强度的随机振动载荷等效为准静态的设计载荷。以太阳翼驱动机构为例,采用Miles公式法进行了结构强度仿真计算,仿真结果表明,太阳翼驱动机构主壳体上十二个个螺栓孔边缘处的应力最大,且小于材料的许用应力,满足结构设计要求,为太阳翼驱动机构结构强度设计提供依据。

The random vibration environment is the main factor in the structural strength designing for the spacecraft. The quasi-static design is the main method that used for structural strength during spacecraft designing. The principle and processing method of the Miles Formula Method, Test Specification Method and Full-band Power Spectral Density Method are researched to calculate the peak of response acceleration. The random vibration load, which will directly influence the quality of spacecraft structure, is converted into quasi-static design load. Taking the Solar Array Driving Mechanism as an example, the Miles Formula Method is used to calculate the structural strength. The simulation results show that the stresses of the six bolt holes on main shell of the Solar Array Driving Mechanism is the biggest, which is less than the allowable stress of the material. The design of Solar Array Driving Mechanism is reasonable, and provides a basis for structural strength of the Solar Array Driving Mechanism.