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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal Basic Information
Journal DOI :
The Korean Society for Composite Materials
Editor in Chief :
Volume & Issues
Volume 14, Issue 6 - Dec 2001
Volume 14, Issue 5 - Oct 2001
Volume 14, Issue 4 - Aug 2001
Volume 14, Issue 3 - Jun 2001
Volume 14, Issue 2 - Apr 2001
Volume 14, Issue 1 - Feb 2001
Selecting the target year
A Study on the Curing Properties of Kevlar/Epoxy Prepreg
Composites Research, volume 14, issue 2, 2001, Pages 1~7
The studies on the formulation and curing behaviors of Kevlar/Epoxy prepreg for NOSE CONE of aircraft were presented in this paper. Dielectrometer and differential scanning calorimeter were used in order to check the curing behaviors. This prepreg showed the lowest ionic viscosity around
, and then the ionic viscosity was gradually increased up to
. This indicated that the curing reaction of this prepreg started at
and the molecular weight was increased by the accelerated thermal cross-linking reaction. The loss factor and tan
values were also measured and discussed. The loss factor behaviors of Kevlar/Epoxy prepreg, which is related to the fluidity of matrix, were fecund to be similar with that of ionic viscosity. The thermal reaction properties of this prepreg were also studied by differential scanning calorimeter.
A Study on the Optimum Evaluation Method for Tensile NOL Ring Specimen Manufactured by Filament Winding Process
Composites Research, volume 14, issue 2, 2001, Pages 8~12
Filament Winding Process is a comparatively simple operation in which continuous reinforcements in the form of roving are wound over a rotating mandrel. It is well established and versatile method for storage tanks and pipes for the chemical and other industries. In this study, tensile strength of a filament wound ring specimens were evaluated by a split disk test fixture and a dress disk test fixture. The results obtained from experiments were compared with the theoretical values from the rule of mixtures. The purpose of this paper is the suggestion of an appropriate test method for the evaluation of tensile properties of filament wound structures. The tensile strength of a ring specimen tested by the dress disk test showed better agreement with the theoretical values than those tested by the split disk test because of higher stress concentration in edges of a split disk test fixture. The results showed that the tensile strength of a ring specimen was influenced by the geometry of test fixture, the continuity of fibers, fiber-tension, fiber-end and stress concentration in specimen.
A Study on Adhesive Joints for Composite Driveshafts
Composites Research, volume 14, issue 2, 2001, Pages 13~21
Substituting composite structures for conventional metallic structures has many advantages because of higher specific stiffness and specific strength of composite materials. In this work, one-piece driveshafts composed of carbon/epoxy and glass/epoxy composites were designed and manufactured for a rear wheel drive automobile satisfying three design specifications, such as static torque transmission capability, torsional buckling and the fundamental natural bending frequency. Single lap adhesive joint was used to join the composite shaft and the aluminum yoke. The torque transmission capability of the adhesively bonded composite shaft was calculated with respect to bonding length and yoke thickness by finite element analysis and compared with the experimental result. Torque transmission capability was based on the Tsai-Wu failure index fur composite shaft and the failure model which incorporated the nonlinear mechanical behavior of aluminum yoke and epoxy adhesive. From the experiments and the finite element analyses, it was found that the static torque transmission capability of the composite driveshaft was highest at the critical yoke thickness, and saturated beyond the critical length. Also, it was found that the one-piece composite driveshaft had 40% weight saving effect compared with a conventional two-piece steel driveshaft.
Damage Assessment of Curved Composite Laminate Structures Subjected to Low-Velocity Impact
Composites Research, volume 14, issue 2, 2001, Pages 22~32
Damage induced by low-velocity impact on the curved composite laminates was experimentally evaluated for CFRP cylindrical shells with the radius of curvatures of 50, 150, 300, and 500 mm. The result was then compared with that of flat laminates and with the results by nonlinear finite-element analysis. The radius of curvatures and the effective shell stiffness appeared to considerably affect the dynamic impact response of curved shells. Under the same impact energy level, the maximum contact force increased with the decreasing radius of curvatures, with reaching 1.5 times that for plates at the radius of curvature of 50 mm. Since the maximum contact farce is directly related to the impact damage, curved laminates can be more susceptible to delamination and less resistant to the low-velocity impact damage. Delamination was distributed rather evenly at each interface along the thickness direction of curved laminates on the contrary to the case of flat laminates, where delamination is typically concentrated at the interfaces away from the impact point. This implies that the effect of curvatures has to be considered for the design of a curved composite laminate.
Cure Cycle for Thick Glass/Polyester Composites
Composites Research, volume 14, issue 2, 2001, Pages 33~42
The cure kinetic equation fur 52-glass/polyester prepreg composites was established through DSC (differential scanning calorimetry). Using the established kinetic equation, the temperature distribution of the thick composite was calculated considering the change of heat transfer resistance due to resin impregnation of bleeder plies used. In order to reduce the overheat during cure of thick glass fiber composites, the cure cycle was modified by introducing the cooling and reheating steps. Then the thick glass composites were cured both by the conventional cycle without any cooling or reheating step and the modified cure cycle. The mechanical properties of the thick composites cured by the both cycles were tested by the short beam shear test and the Barcol hardness test, and then their results were compared.
Characteristics of Smart Skin for Wireless LAN system under Buckling Load
Composites Research, volume 14, issue 2, 2001, Pages 43~49
The characteristics of smart skin for wireless LAN system under compression load are investigated. The smart skin structure is composed of 3 layers of face material and 2 layers of core material. Theoretical formula for determining buckling load is derived by Rayleigh-Ritz method and compared with experimental result. The maximum length of specimen that buckling does not occur is determined by assuming that the compression load is sustained by only face material. In the experiment, if buckling occurs obviously then it follows the theoretical result well. In the process of buckling, the load supporting capability and the antenna property such as radiation pattern and reflection coefficient were examined.
Prediction of Fatigue Life for Composite Rotor Blade of Multipurpose Helicopter Using Strength Degradation Model
Composites Research, volume 14, issue 2, 2001, Pages 50~59
The predictions of residual strength evolution and fatigue life of full scale composite rotor blade for multipurpose helicopter were studied using a strength degradation model. Flight-by-flight load spectrum was developed on the basis of FELIX standard spectrum data. The laminated structural analysis was also performed to obtain corresponding local stress and/or strain spectra for each ply of laminate skin and glass roving spar structures around the blade root where fatigue damage was severely anticipated.
(주)아이세스 부설 첨단계측시스템연구소
Composites Research, volume 14, issue 2, 2001, Pages 60~63
대한항공의 항공기용 복합재료 부품 생산 및 연구개발 현황
Composites Research, volume 14, issue 2, 2001, Pages 64~72