9 July 2002 Application study on aircraft structures of CFRP laminates with embedded SMA foils
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Abstract
This paper reports some research results for the application study of the smart materials an structural using Shape Memory Alloy (SMA) foils. First, the authors acquired the recovery strain of CFRP laminates generated by the recovery stress of the pre-strained SMA foils. Then, the quasi-static load-unload tests were conducted using several kinds of quasi-isotropic CFRP laminates with embedded SMA foils. Micro-mechanics of damage behavior due to the effects of the recovery strain and the first transverse crack strain were discussed. The improvement of maximum 40 percent for the onset strain of the transverse cracks and maximum 60 percent for the onset strain of delamination were achieved for CFRP laminates with embedded pre-strained SMA foils compared with standard CFRP laminates. Furthermore, the authors conducted the structural element test for application to actual structures. Testing technique and the manufacturing technique of the structural element specimen were established.
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Toshimichi Ogisu, Toshimichi Ogisu, Masato Nomura, Masato Nomura, Norio Ando, Norio Ando, Junji Takaki, Junji Takaki, Nobuo Takeda, Nobuo Takeda, } "Application study on aircraft structures of CFRP laminates with embedded SMA foils", Proc. SPIE 4698, Smart Structures and Materials 2002: Industrial and Commercial Applications of Smart Structures Technologies, (9 July 2002); doi: 10.1117/12.475085; https://doi.org/10.1117/12.475085
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