摘要
由于高体分铝基复合材料应用在空间遥感器的结构设计中可能会存在疲劳问题,对高体分SiCp/Al复合材料的疲劳破坏行为进行了研究。首先,介绍了疲劳试验方法,确定采用常规试验方法来研究高体分铝基复合材料的疲劳强度,并对疲劳试验进行了规划。然后通过用三参数幂函数模型处理实验数据获取了S-N曲线中关键参数的数学模型,提出了振动试验中的振动频率选取方法。最后利用振动试验台对5个疲劳试件进行了试验,并用三参数幂函数模型对观测值进行了拟合。结果表明,高体分SiCp/Al复合材料的疲劳强度为161 MPa。该研究结果能够有效地指导航天遥感器的结构设计工作。
Since there may be a fatigue problem when a high volume fraction SiCp/Al-based composite material is used in the structure design of a space remote sensor, the fatigue failure behavior of the material is studied. Firstly, several fatigue testing methods are presented. A conventional testing method is selected to test the fatigue strength of the material. The fatigue test is planned. Then, a mathematic model of the key parameters in the S-N curve is established by using a three-parameter exponential function model to process the experimental data. A method for selecting vibration frequency in the vibration test is proposed. Finally, five specimens are tested on a vibrating table. The observed test data are fitted by using the three-parameter exponential function model. The result shows that the material has a fatigue strength of 161 MPa. This result is very helpful to the structure design of space remote sensors
出处
《红外》
CAS
2013年第10期20-25,共6页
Infrared
基金
中国科学院三期创新工程资助项目(074Z3JN70)
关键词
高体分
反射镜
三参数
振动
疲劳强度
high volume fraction
mirror
three-parameter
vibration
fatigue strength