Static and dynamic validations of a refined thin-walled composite beam model

AIAA Journal ◽  
2001 ◽  
Vol 39 ◽  
pp. 2422-2424
Author(s):  
Z. Qin ◽  
L. Librescu
Keyword(s):  
Composite Beam ◽  
Beam Model ◽  
Thin Walled

Static and Dynamic Validations of a Refined Thin-Walled Composite Beam Model

AIAA Journal ◽  
2001 ◽  
Vol 39 (12) ◽  
pp. 2422-2424 ◽  
Author(s):  
Zhanming Qin ◽  
Liviu Librescu
Keyword(s):  
Composite Beam ◽  
Beam Model ◽  
Thin Walled

scholarly journals A thin-walled composite beam model for light-weighted structures interacting with fluids

2020 ◽  
Vol 95 ◽  
pp. 102968
Author(s):  
Trung Bao Le ◽  
Ariel Christenson ◽  
Toni Calderer ◽  
Henryk Stolarski ◽  
Fotis Sotiropoulos
Keyword(s):  
Composite Beam ◽  
Beam Model ◽  
Thin Walled

Aeroelastic Response of an Aircraft Wing Modeled as a Thin-Walled Composite Beam

2013 ◽  
Author(s):  
Seher Durmaz ◽  
Metin O. Kaya
Keyword(s):  
Transverse Shear ◽  
Composite Beam ◽  
Structural Model ◽  
Beam Model ◽  
Aircraft Wing ◽  
Sweep Angle ◽  
Aeroelastic Response ◽  
Aerodynamic Loads ◽  
Thin Walled ◽  
The Time Domain

This study reports static and dynamic aeroelastic analyses of an aircraft wing in an incompressible flow. A swept thin-walled composite beam with a biconvex cross-section is used as the structural model that incorporates a number of non-classical effects such as material anisotropy, transverse shear deformation and warping restraint. A symmetric lay-up configuration i.e. circumferentially asymmetric stiffness (CAS) is further adapted to this model to generate the coupled motion of flap-wise bending-torsion-transverse shear. For this beam model, the unsteady aerodynamic loads are expressed using Wagners function in the time-domain as well as using Theodorsen function in the frequency-domain. The divergence and the flutter speeds are evaluated for several ply angles and the aeroelastic response of an aircraft wing exposed to gust load is examined. The effects of transverse shear, fiber-orientation and sweep angle on the aeroelastic instabilities and the aeroelastic response of the beam are further discussed.

A generalized Vlasov theory for thin-walled composite beam structures

1994 ◽  
Vol 30 (1) ◽  
pp. 43-54 ◽  
Author(s):  
J. Altenbach ◽  
H. Altenbach ◽  
V. Matzdorf
Keyword(s):  
Composite Beam ◽  
Beam Structures ◽  
Thin Walled ◽  
Vlasov Theory

Vibration Response of a Thin-Walled Cylindrical Pipe with Liquid

2012 ◽  
Vol 189 ◽  
pp. 345-349
Author(s):  
Yu Lan Wei ◽  
Bing Li ◽  
Li Gao ◽  
Ying Jun Dai
Keyword(s):  
Finite Element ◽  
Natural Frequencies ◽  
Element Model ◽  
Beam Model ◽  
Vibration Modes ◽  
Timoshenko Beam Model ◽  
Cylindrical Pipe ◽  
Bending Vibration ◽  
Beam Bending ◽  
Thin Walled

Vibration characteristics of the thin-walled cylindrical pipe are affected by the liquid within the pipe. The natural frequencies and vibration modes of the pipe without liquid are analyzed by the theory of beam bending vibration and finite element model, which is based on the Timoshenko beam model. The first three natural frequencies and vibration modes of the pipe with or without liquid are acquired by experiments. As shown in the experiment results, the natural frequencies of the containing liquid pipe are lower than the natural frequencies of the pipe without liquid.

A FEA Simulation Model for Thin-Walled C-Section Composite Beam Assembling With R-Angle Deviation

2014 ◽  
Author(s):  
Hua Wang ◽  
Suo Si
Keyword(s):  
Numerical Model ◽  
Composite Beam ◽  
Failure Modes ◽  
Mechanical Performance ◽  
Element Model ◽  
Load Level ◽  
Compression Tests ◽  
Accurate Analysis ◽  
Angle Deviation ◽  
Thin Walled

There are unavoidable deviations, such as shrinkage and distortions, in the composite detail parts production due to the complexity of composites fabrication. Interests in the assembly analysis of composite beams have led to a need for more accurate analysis especially in the case of fabrication deviations. This work proposes a numerical finite element model of thin-walled C-section composite beam with R-angle deviation for assembling. The rule of Hashin failure combined with cohesive element is applied to study the mechanical performance of the fiber and matrix (implemented as user subroutine UMAT in ABAQUS) while positioning and clamping. Tension and compression tests are carried out based on available standards to determine the C-section beam behavior under load. The testing data validates the proposed numerical model. The numerical model captures the experimentally obtained results with minimal error, and predicts the failure modes successfully. The proposed model allows to determine accurately the first failure location and the associated load level. It will enhance the understanding of the composite components pre-loading analysis, and help systematically improving the composites assembling efficiency in civil aircraft industry.

Tolerance Simulation of Thin-Walled C-Section Composite Beam in Wingbox Assembly Under Preloading

2015 ◽  
Author(s):  
Hua Wang ◽  
Jun Liu
Keyword(s):  
Probability Distribution ◽  
Composite Beam ◽  
Composite Structures ◽  
Simulation Method ◽  
Simulation Software ◽  
Fea Model ◽  
Final Assembly ◽  
Thin Walled ◽  
Thickness Variations ◽  
Induced Changes

Tolerance simulation’s reliability depends on the concordance between the input probability distribution and the practical situation. Pre-loading induced changes in the probability distribution should be considered in the structure’s tolerance simulation, especially for composite structures. The paper presents a tolerance simulation method for the thin-walled C-section composite beam (TC2B) assembling under preloading, that is prescribed clamping force. Based on FEA model of TC2B, the preloading-modified probability distribution function of the R angle spring-in deviation is proposed. Thickness variations of the TC2B are obtained from the data of the downscaled composite wingbox. These parts’ variations are input to the tolerance simulation software, and the final assembly variations are obtained. The assembly of the downscaled wingbox illustrates the effect of preloading on the probability distribution of the R angle spring-in deviation. The results have shown that tolerance simulation with the modified probability distribution is more accurate than the initial normal distribution. The tolerance simulation work presented in the paper will enhance the understanding of the composite parts assembling with spring-in deviations, and help systematically improving the precision control efficiency in civil aircraft industry.

A composite beam model including variable warping effects derived from a generalized Saint Venant solution

2014 ◽  
Vol 110 ◽  
pp. 140-151 ◽  
Author(s):  
Andrea Genoese ◽  
Alessandra Genoese ◽  
Antonio Bilotta ◽  
Giovanni Garcea
Keyword(s):  
Composite Beam ◽  
Beam Model
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