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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。
Random vibration environment is the main factor in spacecraft structural strength design. The equivalent quasi-static design method is the main method used in the design of spacecraft structural strength. On the basis of studying the basic principle and processing method of calculating peak response acceleration by Miles formula method, experimental standard method and full band power spectral density method, the random vibration load that directly affects the strength of spacecraft structure is equivalent to the quasi-static design Load. Taking the solar wing drive mechanism as an example, the calculation of the structural strength is carried out by the Miles formula method. The simulation results show that the stress at the edge of the twelve bolt holes on the main shell of the solar wing drive mechanism is the largest and less than the allowable stress , To meet the structural design requirements, provide the basis for the structural strength design of the solar wing drive mechanism.