Tujuan utama dalam projek tahun akhir ini adalah untuk menyiasat sifat-sifat mekanik
komposit sandwich selepas terbakar yang mana sandwic komposit ini banyak telah
digunakan secara meluas dalam struktur pesawat dan kapal angkasa. Dalam projek ini, E
glass epoksida telah digunakan sebagai polimer berpenguatan serat dan plastic
honeycomb sebagai teras spesimen. Dengan menggunakan kaedah eksperimen, projek ini
menyiasat kelakuan sandwic komposit selepas terdedah kepada api. Ujian dalam projek
ini untuk mensimulasikan kes terbakar terhadap sandwic komposit. Untuk mengkaji sifat
sifat mekanikal, kaedah ujian mampatan telah digunakan untuk mengukur tekanan,
ketegangan dan modulus muda komposit sandwic. Bagi memperolehi pengetahuan
terhadap terdedahnya sandwic komposit kepada api, projek ini menentukan mekanisme
kegagalan pada masa yang berbeza dan pembakaran lapisan lamina juga telah dijalankan
dalam projek ini untuk mengira pecahan isipadu gentian lapisan lamina sandwic
komposit. Hasil daripada ujikaji bahawa fiber volume friction telah diperolehi kira-kira
40% kepada 46%.
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The primary objective of this final year project is to investigate the post-fire, mechanical
properties of sandwich composite which is a structure that is widely used in aircraft and
spacecraft. In this project, E-glass reinforced epoxy laminate has been used as the
composite skin and a plastic honeycomb for the core of the composite specimen. By
applying fire, structural experiment method, this project investigates the behavior of
sandwich composite after exposure to fire (post-fire). The experiment conduct of this
project is to simulate the post-fire effect of on the sandwich composites. The effects of
increasing exposure times on the residual compressive properties of the sandwich
composite are experimentally determined. To investigate the mechanical properties, the
compression test method was used to measure the stress, strain and young modulus of the
sandwich composite. Compression test was performed for specimen at room condition
first to select the suitable length. Next, specimen with suitable length was exposed to fire
at different times and compression test was performed to find out the mechanical
properties. Moreover, burn-off test also was conducted in this project to identify the fiber
volume fraction of laminate layers of sandwich composite. It was found that the stress,
strain and young modulus of sandwich composite decrease when exposed to fire at
increasing the time. While for the burn-off test, the fiber volume fraction is obtaining
around 40% to 46%.
Post-fire compression properties of sandwich composite material / Abdul Rahman Zainul