Analysis of orthotropic composite cylinders

Kokan, David; Gramoll, Kurt

doi:10.1016/s0961-9526(09)80001-4

Cited by 6 publications

(4 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The closing displacements were -10.69 mm at the inner ring and -15.24 mm at the outer ring. Even similar residual stresses were reported to be induced in a 7.7 mm composite cylinder of inner radius = 38 mm and outer radius = 45.7 mm in Reference [9] under normal autoclave cure. The corresponding stress distributions are shown in Figures 10 and 11.…”

Section: Resultssupporting

confidence: 68%

See 1 more Smart Citation

Continuous Curing and Induced Thermal Stresses of a Thick Filament Wound Composite Cylinder

Kim

White

2001

Journal of Reinforced Plastics and Composites

View full text Add to dashboard Cite

A new composite manufacturing technique called continuous curing is discussed and analyzed. This method is especially suited to the manufacture of thick composite materials in which thermal spiking is a common problem. Thermal and cure fronts are propagated in the thickness direction as material is accreted on the outer surface. An experimental apparatus was designed and built for use with a filament winder to continuously cure thick composite cylinders. A demonstration experiment was carried out using IM6/3501-6 graphite/epoxy prepreg tow. A hoop-wound composite cylinder with 152 mm wall thickness was manufactured and embedded thermocouples and strain gages were monitored throughout the cure process. Results indicate that very thick and good quality composite cylinders can be fabricated without long manufacturing time, material degradation due to thermal spiking, and high level of thermally induced residual stresses.

show abstract

Section: Resultssupporting

confidence: 68%

“…The resulting stresses are relatively low compared to the thickness (152 mm). Even similar residual stresses were reported to be induced in a 7.7 mm composite cylinder of inner radius = 38 mm and outer radius = 45.7 mm in Reference [9] under normal autoclave cure.…”

Section: Resultssupporting

confidence: 68%

Continuous Curing and Induced Thermal Stresses of a Thick Filament Wound Composite Cylinder

Kim

White

2001

Journal of Reinforced Plastics and Composites

View full text Add to dashboard Cite

show abstract

“…To verify the results obtained from the above experiments, an analysis of the residual stresses induced at the FW process was carried out by applying the method proposed by Kokan and Gramoll. (4) Figure 5 shows the geometry for the composite specimen. The stress distribution in a composite pipe may be found by decomposing the problem into a number of simpler ones, solving each of them, and superimposing the solutions.…”

Section: Discussionmentioning

confidence: 99%

Residual Stress of Hoop-Wound CFRP Composites Manufactured with Simultaneous Heating

Tabuchi

Sajima

Doi

et al. 2012

Sensors and Materials

View full text Add to dashboard Cite

Carbon-fiber-reinforced plastic (CFRP) is used to strengthen high-pressure hydrogen composite vessels. However, the existence of excessive resin between CFRP layers and a drop in the strength of CFRP resulting from the fiber tension during the layer stacking of CFRP composites are the points at issue. To solve them, a curing method using simultaneous heating has been proposed. The purpose of this paper is to evaluate the influence of the simultaneous heating on the residual stress of the CFRP composite. CFRP test specimens were manufactured with simultaneous heating, and strains from their stress releases were measured. As a result, with the simultaneous heating method, the difference in residual stresses between the CFRP inner and outer surfaces is smaller than that with the conventional filament winding (FW) method. We conclude that the simultaneous heating method has an advantage to increase the pressure capacity of composite pressure vessels.

show abstract

“…Suemasu et al [4] proposed a method to obtain a dome shape of pressure vessel based on the nonlinear finite element result. Kokan and Gramoll [5] analyzed thermal and mechanical stresses of cylindrical shells due to the tension force during winding procedure. Park et al [6] numerically analyzed 1.5 portion of a real FW rocket motor case considering its periodicity as a 3D finite element method (FEM).…”

Section: Introductionmentioning

confidence: 99%

A Failure Mechanism of Pressure Vessels from Filament-wound Hoop Layer

Suemasu

Sakajiri

2009

Journal of Composite Materials

View full text Add to dashboard Cite

This article studied a possible mechanism of a failure from a thick hoop layer of a filament-wound rocket motor case with long cylindrical portion analytically and numerically. The hoop-wound fibers at the cylindrical portion was slightly inclined from the circumferential direction as a finite width prepreg tape was wound without overlapping or gap by alternately feeding in forward and backward direction. Fiber stress concentration in the hoop layer due to possible damage states was assessed through analytical studies and a rough estimate of the stress concentration was given by explicit functions. The possible damage consisted of transverse cracks slightly inclined from each other and debonding of the interface between the hoop layer and the base layer. The approximate analytical solution agreed well with the numerical results in spite of simplification. The results could show the possibility of stress enhancement due to damage in the thick hoop layer made of two slight inclined fibers and important guideline for the design of filament winding pressure vessels.

show abstract

Analysis of orthotropic composite cylinders

Cited by 6 publications

References 5 publications

Continuous Curing and Induced Thermal Stresses of a Thick Filament Wound Composite Cylinder

Continuous Curing and Induced Thermal Stresses of a Thick Filament Wound Composite Cylinder

Residual Stress of Hoop-Wound CFRP Composites Manufactured with Simultaneous Heating

A Failure Mechanism of Pressure Vessels from Filament-wound Hoop Layer

Contact Info

Product

Resources

About