Optimization of the Composite Airplane Fuselage for an Optimum Structural Integrity

2018 ◽  
Author(s):  
Athreya Nagesh ◽  
Ola Rashwan ◽  
Ma’moun Abu-Ayyad
Keyword(s):  
Carbon Fiber ◽  
Static Loading ◽  
Composite Laminates ◽  
Structural Integrity ◽  
Carbon Composite ◽  
The Finite Element Method ◽  
Nomex Honeycomb ◽  
Honeycomb Cores ◽  
Laminate Thickness ◽  
Airplane Fuselage

The newly developed airplanes are using composite laminates to replace the metal alloys for different components, such as the fuselage and the wings. The major advantage of the composite materials is to reduce structural weight which results in reducing the fuel consumption. The aim of this project is to investigate the structural integrity of an airplane fuselage, which uses various types of carbon composite laminates under the static loading of the cabin pressurization. The research is performed using the finite element method and the HYPERMESH commercial software with a composite tool to change the thickness and the orientation of carbon fiber laminates used in the facesheet of the sandwich structure. Three different orientations/stacking sequence of the HexPly 8552 AS4 carbon fibers with two honeycomb cores: Hexagonal Al and Nomex. The results show that the composite material using the HexPly 8552 carbon fiber oriented at angle 30 and angle 45 and the Nomex Honeycomb core of a total laminate thickness of 15.875mm outperform all other thicknesses and orientations in regards to the static loading failure.

scholarly journals Hygrothermal Deformation of Composite Sandwich Panels

2000 ◽  
Vol 9 (1) ◽  
pp. 096369350000900 ◽  
Author(s):  
Ernest G. Wolff ◽  
Hong Chen ◽  
Darrell W. Oakes
Keyword(s):  
Composite Laminates ◽  
Sandwich Panels ◽  
Adhesive Properties ◽  
Modified Model ◽  
Moisture Expansion ◽  
Composite Sandwich Panels ◽  
Composite Sandwich ◽  
Laminate Theory ◽  
Nomex Honeycomb ◽  
Honeycomb Cores

Coefficients of thermal and moisture expansion (CTE and CME) can be predicted for many composite laminates and sandwich panels. Core and adhesive properties, such as geometry and stiffness are important variables. Laminate theory is augmented with a modified model for anisotropic core properties to predict the CTE and CME of sandwich panels. Procedures to measure both CTE and CME are described. Since these are thermodynamic properties, methods to obtain equilibrium moisture strains are needed. Results are given for CFRP facesheets with Al and NOMEX honeycomb cores, and for woven Kevlar facesheets with Al cores. Agreement with predictions is good and depends highly on knowledge of properties of all constituents.

Study on ultrasonic vibration–assisted cutting of Nomex honeycomb cores

2019 ◽  
Vol 104 (1-4) ◽  
pp. 979-992 ◽  
Author(s):  
Di Kang ◽  
Ping Zou ◽  
Hao Wu ◽  
Jingwei Duan ◽  
Wenjie Wang
Keyword(s):  
Ultrasonic Vibration ◽  
Nomex Honeycomb ◽  
Honeycomb Cores

scholarly journals Improving flexural and dielectric properties of carbon fiber epoxy composite laminates reinforced with carbon nanotubes interlayer using electrospray deposition

2020 ◽  
Vol 9 (1) ◽  
pp. 1170-1182
Author(s):  
Muhammad Razlan Zakaria ◽  
Hazizan Md Akil ◽  
Mohd Firdaus Omar ◽  
Mohd Mustafa Al Bakri Abdullah ◽  
Aslina Anjang Ab Rahman ◽  
...  
Keyword(s):  
Carbon Nanotubes ◽  
Dielectric Properties ◽  
Carbon Fiber ◽  
Composite Laminates ◽  
Epoxy Composite ◽  
Flexural Modulus ◽  
X Ray Diffraction ◽  
Electrospray Deposition ◽  
Ft Ir ◽  
Carbon Fiber Epoxy

AbstractThe electrospray deposition method was used to deposit carbon nanotubes (CNT) onto the surfaces of woven carbon fiber (CF) to produce woven hybrid carbon fiber–carbon nanotubes (CF–CNT). Extreme high-resolution field emission scanning electron microscopy (XHR-FESEM), X-ray diffraction (XRD), Raman spectroscopy and Fourier transform infrared spectroscopy (FT-IR) were used to analyze the woven hybrid CF–CNT. The results demonstrated that CNT was successfully and homogenously distributed on the woven CF surface. Woven hybrid CF–CNT epoxy composite laminates were then prepared and compared with woven CF epoxy composite laminates in terms of their flexural and dielectric properties. The results indicated that the flexural strength, flexural modulus and dielectric constant of the woven hybrid CF–CNT epoxy composite laminates were improved up to 19, 27 and 25%, respectively, compared with the woven CF epoxy composite laminates.

Bending response of carbon fiber composite sandwich beams with three dimensional honeycomb cores

2014 ◽  
Vol 108 ◽  
pp. 234-242 ◽  
Author(s):  
Jian Xiong ◽  
Li Ma ◽  
Ariel Stocchi ◽  
Jinshui Yang ◽  
Linzhi Wu ◽  
...  
Keyword(s):  
Carbon Fiber ◽  
Fiber Composite ◽  
Three Dimensional ◽  
Sandwich Beams ◽  
Carbon Fiber Composite ◽  
Composite Sandwich ◽  
Honeycomb Cores ◽  
Bending Response

ANALYSIS OF PRINTING PARAMETERS IN 3D PRINTED CARBON FIBER COMPOSITES USING DESIGN OF EXPERIMENTS

2021 ◽  
Author(s):  
JAKUB SYCHLA ◽  
CHAO ZHANG ◽  
K. T. TAN
Keyword(s):  
Carbon Fiber ◽  
Flexural Strength ◽  
Structural Integrity ◽  
Fiber Composites ◽  
Fiber Reinforced Polymers ◽  
Carbon Fiber Composites ◽  
3D Print ◽  
Cfrp Composite ◽  
Fill Pattern ◽  
Ductile Behavior

Additive manufacturing of carbon fiber reinforced polymers (CFRP) provides the advantage of quick prototyping of complex geometries, while maintaining light-weight characteristics and keeping structural integrity. This paper presents flexural strength data from 3D printing of an onyx and carbon fiber composites. A MarkForged Mark 2 3D printer, with a dual printer head, is used to 3D print several configurations of CFRP composites. The configurations are set to examine the extreme parameters of the rectangular fill pattern, including fill density, roof and floor layers, and wall layers. The print angle along with the fill pattern stays consistent. Each sample comprises twenty- four layers of CFRP and undergoes a three-point bend test. Test data of load, deflection, and maximum stress are compared among the different configurations. Results show that the roof/floor layer has the largest impact on the flexural strength for each configuration. The configurations with less roof/floor layers are able to take on a larger load, because there are more CFRP layers present; while specimens with more roof/floor layers withstand less load and behave more ductile. These results show that the amount of roof/floor layers can change the CFRP composite from its usual brittle characteristic to a ductile behavior.

Flexural Response of Inorganic Hybrid Composites With E-Glass and Carbon Fibers

2010 ◽  
Vol 132 (2) ◽  
Author(s):  
James W. Giancaspro ◽  
Christos G. Papakonstantinou ◽  
P. N. Balaguru
Keyword(s):  
Carbon Fibers ◽  
Hybrid Composite ◽  
Composite Laminates ◽  
Hybrid Composites ◽  
Glass Fibers ◽  
Composite Plates ◽  
Carbon Composite ◽  
Primary Objective ◽  
Flexural Capacity ◽  
Compression Failure

By far, carbon and glass fibers are the most popular fiber reinforcements for composites. Traditional carbon composites are relatively expensive since the manufacturing process requires significant heat and pressure, while the carbon fibers themselves are inherently expensive to produce. In addition, they are often flammable and their use is restricted when fire is a critical design parameter. Glass fabrics are approximately one order of magnitude less expensive than similar carbon fabrics. However, they lack the stiffness and the durability needed for many high performance applications. By combining these two types of fibers, hybrid composites can be fabricated that are strong, yet relatively inexpensive to produce. The primary objective of this study was to experimentally investigate the effects of bonding high strength carbon fibers to E-glass composite cores using a high temperature, inorganic matrix known as geopolymer. Carbon fibers were bonded to E-glass cores (i) on only the tension face, (ii) on both the tension and compression faces, or (iii) dispersed throughout the core in alternating layers to obtain a strong, yet economical, hybrid composite laminate. For each response measured (flexural capacity, stiffness, and ductility), at least one hybrid configuration displayed mechanical properties comparable to all carbon composite laminates. The results indicate that hybrid composite plates manufactured using 3k unidirectional carbon tape exhibit increases in flexural capacity of approximately 700% over those manufactured using E-glass fibers alone. In general, as the relative amount of carbon fibers increased, the likelihood of precipitating a compression failure also increased. For 92% of the specimens tested, the threshold for obtaining a compression failure was utilizing 30% carbon fibers. The results presented herein can dictate future studies to optimize hybrid performance and to achieve economical configurations for a given set of design requirements.

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