Analysis of filament wound composite structures considering the change of winding angles through the thickness direction

2002 ◽  
Vol 55 (1) ◽  
pp. 63-71 ◽  
Author(s):  
Jae-Sung Park ◽  
Chang-Sun Hong ◽  
Chun-Gon Kim ◽  
Cheol-Ung Kim
Keyword(s):  
Composite Structures ◽  
Thickness Direction ◽  
Filament Wound ◽  
Filament Wound Composite ◽  
Wound Composite

Environmental effects on the durability of filament wound composite structures

1996 ◽  
Author(s):  
J. Wlodarski ◽  
Charles Pergantis ◽  
Thomas Mulkern ◽  
James Kleinmeyer
Keyword(s):  
Environmental Effects ◽  
Composite Structures ◽  
Filament Wound ◽  
Filament Wound Composite ◽  
Wound Composite

CNT/epoxy interleaves for strengthening performance of filament wound composite structures

2021 ◽  
pp. 2140001
Author(s):  
Soo-Jeong Park ◽  
Yun-Hae Kim
Keyword(s):  
Structural Design ◽  
Composite Structures ◽  
Influencing Factor ◽  
Interfacial Bonding ◽  
Filament Wound ◽  
Interfacial Bonding Strength ◽  
The Matrix ◽  
Filament Wound Composite ◽  
Low Performance ◽  
Wound Composite

The failure mechanism of composites dominates the matrix, fiber and interface, and in general, the matrix corresponds to the definitive cause of damage. A filament–wound composite structure involves a notable bridging effect owing to the matrix between the layers, and particle additives are generally adopted to strengthen the matrix. However, particle additives exhibit a low performance when applied to structures, owing to the dispersibility and particle agglomeration. In this study, the strengthening performance of carbon nanotube (CNT)/epoxy interleaves was experimentally verified to facilitate their implementation in the structural design of a filament–wound cylinder structure. The burst pressure, compression, bending and interfacial bonding strength of the cylinder improved by approximately 20%, 161%, 16% and 36%, respectively, and the positioning of CNT/epoxy interleaves was a more notable influencing factor compared to the proportion of CNTs in the entire winding layer. The number of macro voids decreased inside the epoxy modified CNT. The findings demonstrated that the incorporation of CNTs through CNT/epoxy interleaves could facilitate the matrix strengthening and enhance the interfacial bonding.

APPLICATION OF NOVEL NANOSENSOR TECHNOLOGY TO FILAMENT WOUND COMPOSITE STRUCTURES

2008 ◽  
Vol 32 (2) ◽  
pp. 23-30
Author(s):  
T. Niblock ◽  
B.C. Laskowski ◽  
P.L. Howard ◽  
T.K. Ooi
Keyword(s):  
Composite Structures ◽  
Filament Wound ◽  
Filament Wound Composite ◽  
Wound Composite

Influence of mosaic pattern on hygrothermally-aged filament wound composite cylinders under axial compression

2020 ◽  
Vol 54 (19) ◽  
pp. 2651-2659 ◽  
Author(s):  
Cristiano B Azevedo ◽  
José Humberto S Almeida Jr ◽  
Heitor F Flores ◽  
Frederico Eggers ◽  
Sandro C Amico
Keyword(s):  
Compressive Strength ◽  
Composite Structures ◽  
Mechanical Response ◽  
Filament Winding ◽  
Environmental Conditioning ◽  
Filament Wound ◽  
Filament Wound Composite ◽  
Strength And Stiffness ◽  
Hygrothermal Conditioning ◽  
Wound Composite

The mechanical response of composite structures may be affected by harsh environments, particularly when the matrix has a major contribution, e.g. with off-axis plies. This study aims at investigating the influence of the winding pattern on the axial compressive behavior of filament wound composite cylinder under hygrothermal conditioning. Carbon fiber-reinforced epoxy cylinders were manufactured via filament winding with 1/1, 3/1, and 5/1 mosaic winding patterns and submitted to distilled and artificial seawater environmental conditioning. Water uptake for each hygrothermal conditioning was periodically monitored. The winding pattern influenced both compressive strength and stiffness, and the environmental conditioning decreased strength up to ≈10%. The winding pattern with three diamonds around the circumference of the cylinders provides the properties in term of compressive strength and stiffness.

scholarly journals Research of Dependence of the Damage Area on Tow Width on Filament-Wound Composite Tubes

2017 ◽  
Vol 2017 (1) ◽  
pp. 7-14
Author(s):  
Marcelina Bobrowska ◽  
Michał Barcikowski ◽  
Radosław Rybczyński
Keyword(s):  
High Velocity ◽  
Composite Structures ◽  
Layered Composite ◽  
Filament Winding ◽  
Composite Tubes ◽  
Damage Area ◽  
Gas Gun ◽  
Filament Wound ◽  
Filament Wound Composite ◽  
Wound Composite

Abstract This paper explores the effect of tow width on the damage area produced by high velocity impacts on glass fiber/epoxy composite structures made by filament winding. The subject of the research were a four-layered composite tubes that have been designed using matrix method. The method was used to select mosaic patterns with different rest of the winding stroke and number of interlaces, which are places of stress concentration and which affect the strength of the composite. The narrowest (5 mm) and the widest (17 mm) tow width available was chosen. Composite filament-wound structures were subjected to a high velocity impact by a 2.0 g spherical hardened steel impactor propelled to a velocity of 140 ÷ 170 m/s using a gas gun. It was observed that dependence of the damage area on tow width on filament-wound composite tubes is possible.

Design and Validation of a Filament Wound Composite Rocket Motor Case

2018 ◽  
Author(s):  
Emre Özaslan ◽  
Bülent Acar ◽  
Ali Yetgin
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Composite Structures ◽  
Rocket Motor ◽  
Fiber Direction ◽  
Element Analysis ◽  
Filament Wound ◽  
Filament Wound Composite ◽  
Winding Angle ◽  
Wound Composite

Filament wound composite structures are widely used in aerospace applications such as motor case of rockets owing to their high stiffness/weight ratio and high strength. However, design and analysis of a filament wound structure is so complex due to the anisotropic nature of the composite material. Variation of the winding angle through the rocket motor case axis and through the thickness, which is also a function of winding angle are the main challenges to the realistic modeling of a filament wound composite rocket motor case. In this study, finite element analysis of a filament wound rocket motor case with unequal dome openings was performed. The finite element model was compared with manufactured motor case in terms of winding angle and thickness to ensure the exact modeling. The finite element analysis was compared with burst tests in terms of fiber direction strain distribution through the outer surface of the motor case to verify analysis. The weak regions of the motor case were determined with finite element analysis to be transition region from cylinder to dome which is subjected to significant bending because of the stiffness difference between these regions. Then, some design improvements were proposed to increase the mechanic performance of motor case. Significant improvement was succeeded in terms of mechanic performance. Important aspects of designing and analyzing a filament wound composite rocket motor case were addressed for designers.

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