摘要
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 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 was analyzed and investigated. Finite Element（FE） and Boundary Element（BE） methods were used to establish numerical analysis models for acoustic response in composite solar panel. The numerical analysis model was verified and validated by acoustic test of the solar panel in reverberation chamber. The results showed that the fatigue damage was distributed symmetrically along the long axis of the structure and the fatigue damage at the point of maximum rate of D=0.0232 when subjected to sound excitation sustained action over 60 s. No fatigue failure appeared and the shortest lifetime of solar panel was 2.58×103 s. All results lead to the conclusion 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, and easily gets broken.
出处
《装备环境工程》
CAS
2016年第5期41-47,共7页
Equipment Environmental Engineering
关键词
噪声激励
FE/BEM
混响
声学响应
疲劳寿命
acoustic excitation
EF/BEM
reverberation
acoustic response
fatigue life
