Co-cured manufacturing of advanced composite materials using vacuum assisted resin transfer molding

Download
2018
Akın, Mert
Sub-structures of aircraft structures mainly consist of stiffened shells such as fuselage frames, ribs, and multi-cell box beams. Conventionally, these stiffened shells are manufactured through a process wherein shells and stiffeners are fabricated separately and then are integrated either through mechanical fastening or adhesive bonding. Co-curing is an integral molding technique that can greatly reduce the part count and the final assembly costs for composite materials. In this study, a low-cost co-curing manufacturing technique for stiffened shells of aircraft structures, particularly multi-cell box beams, is developed. Foam material, foam strength, curing operation and foam coating are considered to be the process parameters and the process is improved by optimizing these parameters. The study also has a wider goal of aiding the simulation tools of composite material processing by providing a material data, including preform permeability, porosity, and resin viscosity model. For this purpose, the three-fold approach is followed. First, an extensive characterization of the preform and the resin properties is performed. Then, resin impregnation simulations of the co-cured three-cell box beam are performed. In the final part, the co-curing manufacturing technique is developed and the co-curing process is compared with the conventional method, secondary bonding, from part bending strength, manufacturing and energy consumption perspectives. The four-point bending test results show that the co-cured part withstands 95% higher load and fails at 99% higher load compared to the secondary-bonded part. Additionally, it is found that almost 57% energy and 25% labor time savings can be achieved by using the co-curing technique.

Suggestions

A helicopter rotor modelling and meshing system
Uzun, Halit Eldem; Yutük, Kaan; Baran, Özgür Uğraş; AKSEL, MEHMET HALUK (2021-09-08)
Helicopter rotors in flight constitute a fairly complex wing geometry and exhibit motion in several axes. As a result, rotor motion creates quite complex flow patterns, and unlike fixed wings, flow around each rotor blade interacts with each other. These complexities make the analysis of the rotor flow is a challenge for CFD solvers. The challenge starts with very high requirements on the quality of the computational mesh. A modern helicopter rotor involves a number of different airfoil sections, complex pr...
Experimental investigation of failure mechanism in cross-ply and fabric curved composite laminates
Çevik, Ahmet; Çöker, Demirkan; Department of Aerospace Engineering (2021-8)
Laminated curved-shape composite parts which are used in the spar and ribs in aircraft and wind turbine blades are subjected to high interlaminar tensile and shear stresses. These stresses cause delamination and subsequent reduction in load-carrying capacity. In this study, failure mechanism of cross-ply and fabric curved composite laminates under pure transverse loading are examined experimentally using an in-house designed test fixture. Stress field over the curved beam is obtained with finite element ana...
Numerical modeling of failure in composite L-beam and T-joint structures
Temiz, Pakize; Çöker, Demirkan; Department of Aerospace Engineering (2022-12-02)
Laminated curved-shape composite structures which are used as stiffening components in aerospace, wind, automotive and marine industries are subjected to high radial and tangential stresses. For the scope of this thesis, different modelling strategies are investigated to simulate interlaminar and intralaminar failure in composite L-beam and T-joint structures using commercial finite element (FE) code ABAQUS/Standard 2020. In the first part, [030] and [03/903/03/903/03]s laminated L-beams are evaluated using...
Experimental Observations of Dynamic Delamination in Curved [0] and [0/90] Composite Laminates
Imren, Uyar; Miray, Arca; Burak, Gozluklu; Çöker, Demirkan (null, Springer, 2015-01-01)
Curved composite parts are increasingly replacing metal ribs and box structures in recent civil aerospace structures and wind turbine blades. Delamination of L-shaped composite laminates occurs by interlaminar opening stresses in addition to the interlaminar shear stresses at the curved region. An experimental setup is designed to investigate dynamic delamination in L-shaped composite brackets under quasi static shear loading. The materials are unidirectional [0]17and cross-ply [0/90]17 epoxy/graphite compo...
Experimental Observations of Dynamic Delamination in Curved [0] and [0/90] Composite Laminates
Uyar, I.; Arca, M.A.; Gozluklu, B.; Çöker, Demirkan (2015-01-01)
Curved composite parts are increasingly replacing metal ribs and box structures in recent civil aerospace structures and wind turbine blades. Delamination of L-shaped composite laminates occurs by interlaminar opening stresses in addition to the interlaminar shear stresses at the curved region. An experimental setup is designed to investigate dynamic delamination in L-shaped composite brackets under quasi static shear loading. The materials are unidirectional [0]17and cross-ply [0/90]17 epoxy/graphite compo...
Citation Formats
M. Akın, “Co-cured manufacturing of advanced composite materials using vacuum assisted resin transfer molding,” M.S. - Master of Science, Middle East Technical University, 2018.