Stress Analysis of Cracked Metallic Aircraft Structure Adhesively Repaired with Composite Patch

2014 ◽  
pp. 369-377
Author(s):  
Weiguo Su ◽  
Lan Zou ◽  
Zhitao Mu ◽  
Xudong Li
Keyword(s):  
Stress Analysis ◽  
Aircraft Structure ◽  
Composite Patch

Performance assessment and optimization of hybrid composite patch repair of aircraft structure

2020 ◽  
Vol 16 (5) ◽  
pp. 887-913
Author(s):  
Alpesh H. Makwana ◽  
A.A. Shaikh
Keyword(s):  
Glass Fiber ◽  
Hybrid Composite ◽  
Volume Fraction ◽  
Patch Repair ◽  
Design Parameters ◽  
Aircraft Structure ◽  
Content Type ◽  
Composite Patch ◽  
Peel Stress ◽  
Selection Of

PurposeIn this article, a novel hybrid composite patch consisting of unidirectional carbon fiber and glass fiber is considered for repair of the aircraft structure. The purpose of this paper is to assess the performance of hybrid composite patch repair of cracked structure and propose an optimized solution to a designer for selection of the appropriate level of a parameter to ensure effective repair solution.Design/methodology/approachElastic properties of the hybrid composites are estimated by micromechanical modeling. Performance of hybrid composite patch repair is evaluated by numerical analysis of stress intensity factor (SIF), shear stress, and peel stress. Design of experiment is used to determine responses for a different combination of design parameters. The second-order mathematical model is suggested for SIF and peel stress. Adequacy of the model is checked by ANOVA and used as a fitness function. Multiobjective optimization is carried out with a genetic algorithm to arrive at the optimal solution.FindingsThe hybrid composite patch has maintained equilibrium between the SIF reduction and rise of the peel stress. The repair efficiency and repair durability can be ensured by selection of an optimum value of volume fraction of glass fiber, applied stress, and adhesive thickness.Originality/valueThe composite patch with varying stiffness is realized by hybridization with different volume fraction of fibers. Analysis and identification of optimum parameter to reduce the SIF and peel stress for hybrid composite patch repair are presented in this article.

Three dimensional stress analysis of a composite patch using stress functions

2010 ◽  
Vol 52 (12) ◽  
pp. 1646-1659 ◽  
Author(s):  
Heung Soo Kim ◽  
Maenghyo Cho ◽  
Jaehun Lee ◽  
Antoine Deheeger ◽  
Michel Grédiac ◽  
...  
Keyword(s):  
Stress Analysis ◽  
Three Dimensional ◽  
Composite Patch ◽  
Stress Functions

scholarly journals Use of a composite repair patches to repair the upper air intake flap for the MiG-29 aircraft engine

2017 ◽  
Vol 40 (2) ◽  
pp. 101-127
Author(s):  
Michał Sałaciński ◽  
Michał Stefaniuk ◽  
Piotr Synaszko ◽  
Janusz Lisiecki
Keyword(s):  
Epoxy Composite ◽  
Aircraft Engine ◽  
Aircraft Structure ◽  
Composite Repair ◽  
Comparative Tests ◽  
Composite Patch ◽  
Bonded Repair ◽  
Air Intake ◽  
Welding Joints ◽  
Cost Efficient

AbstractThe Composite Patch Bonded Repair (CPBR) is one of the most cost-efficient types of aircraft structure repair. In the CPBR, the damaged structure is reinforced by applying a composite patch. The boron-epoxy composite (BFRP) is a popular choice for these types of repair. The BFRP was utilized to repair the cracked resistance welding joints in the upper flap of the MiG-29’s RD-33 engine intake. In the present paper, the numerical results are shown, along with the comparative tests of the undamaged inlet flap, the damaged inlet flap and of the CPBR repaired inlet flap.

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