复合材料太阳翼基板声学疲劳特性研究

研究航天器在声激励下的疲劳行为及其演变规律,对证航天器的运行安全。针对碳纤维蒙皮-铝蜂窝的太阳翼基板声致疲劳问题,使用耦合FE/BEM方法,建立航天器太阳翼基板的数值分析模型,以声学试验结果为依据,对仿真模型进行验证。噪声激励持续作用60 s后,损伤率分布呈沿结构长轴对称状态,疲劳危险点处最大损伤率D=0.0232,太阳翼基板未出现疲劳破坏,最短疲劳寿命T=2.58×103s。太阳翼基板中心区域为结构设计薄弱处,该区域在多阶模态下的应力水平较高,疲劳寿命较短,极易导致疲劳破坏。

THE INVESTIGATION FOR ACOUSTIC FATIGUE ONCOMPOSITE SOLAR PANEL

In the launch process, the spacecraft has been subjected to huge sound excitation. The investigation on the fatigue behavior and its evolution law of spacecrafts under sound excitation is very significant to ensure the safety of the spacecraft in the launch. In this paper, the acoustic fatigue of composite solar panel is analyzed and investigated. Finite Element (FE) and Boundary Element(BE) methods are used to establish numerical analysis models for acoustic response in composite solar panel. The numerical analysis model is verified and validated by acoustic test of the solar panel in reverberation chamber. Furthermore, the fatigue life of composite solar panel under acoustic excitation is calculated and predicted. The results show that the center location in composite solar panel has the shortest fatigue life due to high stress level caused by several vibro-acoustic coupling modes. This research provides an analysis and prediction method to acoustic fatigue life of some key components in spacecraft such as satellites, solar panel and others.