Optimum alternate material selection methodology for an aircraft skin

Ahmad, Fareed; Awadh, Mohammed Al; Noor, Sahar

doi:10.1016/j.cja.2023.05.019

Cited by 14 publications

(2 citation statements)

References 34 publications

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“…Whereas existing literature primarily focuses on corrosion in overlapping zones related to conventional aluminium-to-aluminium configurations combined with fasteners of different materials, it is crucial to recognize that contemporary designs incorporate an even more extensive array of materials. The integration of carbon fibre-reinforced polymer (CFRP) with aluminium alloys intensifies the overall susceptibility to corrosion [16]. Empirical evidence derived from corrosion tests [17,18] supports the susceptibility for corrosion in these cases, whereas a limited number of case studies demonstrate their vulnerability in aircraft during service [19].…”

Section: Introductionmentioning

confidence: 99%

Unravelling Corrosion Degradation of Aged Aircraft Components Protected by Chromate-Based Coatings

Mol,

Homborg,

't Hoen-Velterop

et al. 2024

Preprint

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Section: Introductionmentioning

confidence: 99%

Unravelling Corrosion Degradation of Aged Aircraft Components Protected by Chromate-Based Coatings

Mol,

Homborg,

't Hoen-Velterop

et al. 2024

Preprint

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“…Lightweight design and manufacturing are the development direction of aerospace, transportation, and other fields, which can realize performance improvement, energy saving, and emission reduction [1,2]. Carbon fiber reinforced polymer composites have the advantages of high specific strength, high specific stiffness, designable properties, and integral fabrication of components, making them the preferred materials for reducing weight and improving performance [3,4]. Depending on the polymer matrix, such composites can be divided into thermosetting and thermoplastic.…”

Section: Introductionmentioning

confidence: 99%

Effect of Temperature Distribution on Interfacial Bonding Process between CFRTP Composite and Aluminum Alloy during Laser Direct Joining

Wang,

Fu,

Wang

et al. 2023

Applied Sciences

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Laser direct joining enables non-destructive and lightweight joining of carbon fiber reinforced thermoplastic (CFRTP) composites and aluminum alloys. The interfacial bonding process determines the joint performance and is influenced by the time-varying temperature distribution. However, the interfacial bonding process occurs inside the joint, making it difficult to study the effect of temperature distribution. To resolve this issue, a novel online observation device for the interfacial bonding process between CFRTP composites and aluminum alloys is design, and the polymer melting, flowing, and bonding with metal during laser direct joining are observed. Further, temperature field simulation models for laser direct joining are established, and temperature distribution and gradient are calculated. The results show that the temperature distribution determines the melting of CFRTP composites, and bubbles generated by the thermal decomposition of the polymer hinder the melting. The temperature gradient is related to the movement of the molten matrix and fibers, and the movement towards the aluminum alloy induces cracking and delamination. Once the interface is filled with polymer, the motion changes to along the laser scanning direction and the joining defects are reduced. The study can provide a foundation for promoting interfacial bonding and reducing the defects of laser direct joining.

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Analysis of Deformation in Aircraft Skin Vacuum Adsorption Clamping

Xing,

Wang,

et al. 2024

Lecture Notes in Mechanical Engineering

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Large lightweight alloy skin panels are extensively utilized in the aerospace industry and serve as crucial components constituting the outer shells of aircraft, launch vehicles, manned spacecraft, and other equipment. However, due to their thin-walled nature and limited stiffness, they are susceptible to clamping deformation and machining-induced deformations. Vacuum adsorption technology is widely employed in aircraft manufacturing to mitigate part deformation during machining through the utilization of profiling molds. However, to achieve the milling and drilling tasks in a single clamping process, it is necessary to reserve drilling positions in the vacuum adsorption mold. Unfortunately, this leads to significant deformation of the aircraft skin at the reserved drilling positions during processing. This article utilizes finite element simulation technology to analyze the deformation of the aircraft skin during the vacuum adsorption clamping process. The simulation results indicate that the maximum deformation reaches 5.602 mm, which primarily occurs at the middle hole of the vacuum adsorption mold. To address this issue, the article proposes a solution of adding sealing strips around the reserved holes. This solution effectively reduces the deformation of the skin during the processing stage.

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Optimum alternate material selection methodology for an aircraft skin

Cited by 14 publications

References 34 publications

Unravelling Corrosion Degradation of Aged Aircraft Components Protected by Chromate-Based Coatings

Unravelling Corrosion Degradation of Aged Aircraft Components Protected by Chromate-Based Coatings

Effect of Temperature Distribution on Interfacial Bonding Process between CFRTP Composite and Aluminum Alloy during Laser Direct Joining

Analysis of Deformation in Aircraft Skin Vacuum Adsorption Clamping

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