Design, Analysis, Manufacturing, and Testing of Ceramic and Polymer Matrix Nanocomposites

Abstract

Chapter 1 of this thesis presents the Introduction and background for this thesis. InChapter 2 of this thesis, ceramic nanocomposites are introduced as a viable alternative to current material used in space telescopes. Based on SOLIDWORKS Finite Element Analysis, replacing the current combination of Titanium and Nitronic 60, used in the hinge of the primary mirror wing of the James Webb Space Telescope, by the new ceramic nanocomposite made from compaction, cure, and pyrolysis of newly developed Nano-Paste, in the Hawaii Nanotechnology Laboratory (HNL), made of SMP-10, silicon carbide nanoparticles, and carbon nanotubes (CNTs), will dramatically lower the strain and displacement on the mirror structure caused by thermal and structural loads. Low strain and displacement, under thermal and structural loads will lead to better performance, while lower density of the new ceramic material will also allow for significant weight savings for the next generation of telescopes. In Chapter 3 of this thesis, the effects of the inclusion of vertically aligned carbon nanotube Nanoforest II, VA-CNT-NF-II, and horizontally aligned carbon nanotube Nanoforest II, HA-CNT-NF-II, on interlaminar fracture toughness of prepreg carbon fiber laminates have been investigated and reported. The CNTs included in these samples were synthesized using Chemical Vapor Deposition (CVD) furnace, on steel substrate. The CNT-NF-II layers were then transferred onto the prepreg using a Hot Press. Double Cantilever Beam (DCB) testing in accordance with the ASTM test standard D 5528-01 shows exceptional improvements in Mode I (i.e., Opening Mode) interlaminar fracture toughness of both sets of NF-II samples when compared with the pristine (i.e., when no CNT-NF included), with the highest improvement (i.e., 174%) shown in the case of HA-CNT-NF-II samples followed by 124% improvement for the case of VA-CNT-NF-II.