Carbon fibre reinforced polymer (CFRP) composites are increasingly used in the aerospace field to reduce the weight and improve the stability of structures. In most conditions, micro-cracks presented in these structures propagate rapidly due to fatigue caused by vibrations, resulting in premature failure. In high-precision space missions, the structural design and dynamic performance of CFRP composites are integral to the performance of the spacecraft. This study focuses on the influence of a novel three-dimension (3 Dim) and four-direction (4 Dir) braided composite T-beam structural design on vibration properties. The effects of surface braided angles and geometry on the modal properties of the T-beam are investigated by means of modal experiments and finite element analysis. The results show that the structural design of the T-beam can meet various requirements of dynamic performance.
|Publication status||Published - 1 Jan 2017|
|Event||21st International Conference on Composite Materials, ICCM 2017 - Xi'an, China|
Duration: 20 Aug 2017 → 25 Aug 2017
|Conference||21st International Conference on Composite Materials, ICCM 2017|
|Period||20/08/17 → 25/08/17|
- Finite element analysis (FEA)
- Polymer-matrix composite (PMCs)