Results 1 to 10 of about 508 (224)

Buckling and Post-buckling Performance of Advanced Composite Stiffened Panel Under Compression

Journal of Aeronautical Materials, 2016
The axial compressive experiment was conducted on the domestic advanced composite stiffened panel, and its buckling and post-buckling performance was analyzed by monitoring strain and out-of-plane displacement of typical positions.
ZHANG Haoyu, HE Yuting, FENG Yu, TAN Xiangfei, ZHENG Jie   +4 more
doaj   +1 more source

Post-buckling analysis method of stiffened composite panels and test verification

Journal of Aeronautical Materials, 2021
Post-buckling analysis methods of fiber-reinforced T section stiffened composite panels were investigated. In this paper, the Finite Element Model was presented.
LIN Guowei, LI Xinxiang
doaj   +1 more source

Cohesive Zone Model Modification Techniques According to the Mesh Size in Finite Element Models of Stiffened Panels with Debonding

Computation, 2022
When catastrophic failure phenomena in aircraft structures, such as debonding, are numerically analyzed during their design process in the frame of “Damage Tolerance” philosophy, extreme requirements in terms of time and computational resources arise ...
Vasileios K. Mantzaroudis, Dimitrios G. Stamatelos   +1 more
doaj   +1 more source

COMPOSITE SANDWICH OPTIMIZATION OF A STIFFENED PANEL STRUCTURE

, 2019
Optimization strategy for sandwich composites based on lamination parameters, applied to a stiffened panel problem.
Meddaikar, Muhammad Yasser, Silva Caprio, Gustavo, Dillinger, Johannes, De Breuker, Roeland, Prado, Alex   +4 more
openaire   +3 more sources

Study on the Post-impact Damage Tolerance of Composite Stiffened Plates

Hangkong gongcheng jinzhan, 2019
Study on the post-impact damage evolution of composite stiffened panels is of highly value in engineering application. First, take a type of UAV as a research subject, in which the stiffened composite panels(T300/BA9913) are applied.
Li Gang, Wang Shengnan, Li Wei
doaj   +1 more source

A simple closed-form analytical model for the column buckling of omega-stinger-stiffened panels with periodic boundary conditions

Results in Engineering, 2020
During the preliminary design of stiffened panels, the stability behaviour is critical and both buckling modes, global and local, have to be considered in order to avoid panel configurations in which the minimum stiffness of the stringers is not achieved.
Jakob C. Schilling, Christian Mittelstedt   +1 more
doaj   +1 more source

Axial compressive performances of stiffened composite panels: Experimental and numerical study

Alexandria Engineering Journal, 2023
Axial compressive performances of stiffened composite panel were studied in this manuscript. In experimental study, buckling phenomenon of three specimens appear at 413kN, 403kN and 403kN respectively while catastrophic failure appears at 964kN, 934kN ...
Yu Feng, Wenqian Wang, Song Lu, Songjing Liu, Binlin Ma   +4 more
doaj   +1 more source

Post-Buckling Failure Mechanism and Optimal Tapered Termination Design for Composite Hat-Stiffened Panels

Aerospace
Composite hat-stiffened panels are widely used in civil aircraft structural design as typical closed-section stiffened components with high load-carrying efficiency.
Guofan Zhang, Chunhua Wan, Liang Chang, Xiaohua Nie   +3 more
doaj   +1 more source

FABRICATION OF COMPOSITE STIFFENED PANEL

INTERANTIONAL JOURNAL OF SCIENTIFIC RESEARCH IN ENGINEERING AND MANAGEMENT
A Composite materials are widely used in aerospace structures due to their high strength-to weight ratio and high stiffness-to-weight ratio as compared to conventional materials.Well-judged combination of materials along with the specific type of engineering structures, stiffened structures, provide tailored properties for aircraft structural ...
Syed Masood, DR.K JAGATH
openaire   +1 more source

Parametric study on average stress-average strain curve of composite stiffened plates using progressive failure method

Latin American Journal of Solids and Structures
The post-buckling behavior of composite ships' stiffened plate panels has been studied. In this study, the average strain- average stress curves for these panels are derived using progressive failure method as well as nonlinear finite element method. The
Fattaneh Morshedsolouk, Mohammad Reza Khedmati   +1 more
doaj   +1 more source