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Static Pull and Push Bending Properties of RTM-made TWF Composite Tee-joints

Chinese Journal of Aeronautics 2012年第2期25卷 198-207页

作者： LUO Chuyang XIONG Junjiang School of Transportation Science and Engineering Beihang University Beijing 100191 China China Airborne Missile Academy Luoyang 471009 China

This paper deals with static pull and push bending tests on two-dimensional （2D） orthogonal EW220/5284 twill weave fabric （TWF） composite tee-joints processed with the resin transfer moulding （RTM） technique. Static pull and push bending properties are determined and failure initiation mechanism is deduced from experimental observations. The experiments show that the failure initiation load, on average, is greater for push bending than for pull bending, whereas the scatter is smaller for push bending than for pull bending. The failure mode of RTM-made tee-joints in pull bending tests can be reckoned to be characteristic of debonding of resin matrix at the interface between the triangular resin-rich zone and the curved web of tee-joint until complete separation of the curved web from the bottom plate. In contrast, as distinct from the products subject to pull bending loading, the RTM tee-joints in push bending tests experience matrix cracking and fibre fracture from outer layers to inner layers of the bottom plate until catastrophic collapse resulting from the bending. Three-dimensional finite element （FE） models are presented to simulate the load transfer path and failure initiation mechanism of RTM-made TWF composite tee-joint based on the maximum stress criterion. Good correlation between experimental and numerical results is achieved.

关键词： fabrics mechanical properties finite element analysis resin transfer moulding tee-joint

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Thermo-mechanical properties of RTM-made carbon fibre/polyimide composite attaching collar under transient heating

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Chinese Journal of Aeronautics 2023年第3期36卷 393-405页

作者： Shengda JIANG Chuyang LUO Peng ZHANG Jianwen BAO Peipei CAI Xufeng XIA Shanghai High Performance Fibers and Composites Center(Province-Ministry Joint) Center for Civil Aviation CompositesDonghua UniversityShanghai 201620China AVIC Composite Technology Center Science and Technology on Advanced Composites LaboratoryBeijing 101300China Luoyang Optoelectro Technology Development Center Luoyang 471009China

This study focuses on the thermo-mechanical properties of Carbon Fibre/Polyimide Composite(CFPC)attaching collars under transient *** CFPC attaching collars were fabricated by a high-temperature resin transfer moulding process,and their thermo-mechanical properties under the conditions of simultaneous transient heating and bending load were *** results show that the attaching collar tends to fail at 118% of the limit *** failure mode includes the fracture of the connecting screws,local extrusion damage of the hole edges,and slight ablation damage at the outer *** there is no observable residual deformation in the composite attaching ***,considering that the material properties vary with temperature,a progressive damage model based on the sequential thermo-mechanical coupling method was established to study the failure mechanism of the attaching ***,the damage factor of the CFPC was calculated to assess the safety status of the attaching *** results show that the primary damage modes of the composite attaching collar are intralaminar failure,which mainly occurs at the heat insulation layer and the hole edges,and these slightly affect the structural bearing capacity.A good correlation between the experiment and FEA is *** test methods and analysis models proposed contribute to the safety assessment of composite structures under transient heating.

关键词： Polyimide composites Progressive damage model resin transfer moulding Thermo-mechanical properties Transient heating

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