Design of a Fail-Safe Crack Arrested Test Specimen for Certification of Bonded Unitized Composite Structures

Action, Jason; Goyal, Vijay K.

doi:10.2514/6.2022-0105

Cited by 3 publications

(4 citation statements)

References 6 publications

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“…Moreover, Jones [43] concluded that multiple failure modes, including cracking in the adhesive or at the adhesive-metal interface, fiber fracture, and delamination, should be evaluated when performing damage tolerance assessments of layered structures. The progressive failure resultant from these damage mechanisms was subsequently investigated (e.g., [45][46][47][48][49][50][51]). For example, an aerospace application of composite/metal layered structures occurs at stiffener to skin bonding, i.e., Pi and T joints.…”

Section: Composite Overlay Backgroundmentioning

confidence: 99%

“…For example, an aerospace application of composite/metal layered structures occurs at stiffener to skin bonding, i.e., Pi and T joints. Action et al [50] investigated the fail-safe crack arrestment in a T -joint bonded to aircraft skin. They studied crack arrestment for a multi-loaded bonded T joint looking at strain energy to predict the delamination and crack propagation.…”

Section: Composite Overlay Backgroundmentioning

confidence: 99%

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Reduced-Dimension Surrogate Modeling to Characterize the Damage Tolerance of Composite/Metal Structures

Arndt,

Crusenberry,

Heng

et al. 2023

Modelling

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Complex engineering models are typically computationally demanding and defined by a high-dimensional parameter space challenging the comprehensive exploration of parameter effects and design optimization. To overcome this curse of dimensionality and to minimize computational resource requirements, this research demonstrates a user-friendly approach to formulating a reduced-dimension surrogate model that represents a high-dimensional, high-fidelity source model. This approach was developed specifically for a non-expert using commercially available tools. In this approach, the complex physical behavior of the high-fidelity source model is separated into individual, interacting physical behaviors. A separate reduced-dimension surrogate model is created for each behavior and then all are summed to formulate the reduced-dimension surrogate model representing the source model. In addition to a substantial reduction in computational resources and comparable accuracy, this method also provides a characterization of each individual behavior providing additional insight into the source model behavior. The approach encompasses experimental testing, finite element analysis, surrogate modeling, and sensitivity analysis and is demonstrated by formulating a reduced-dimension surrogate model for the damage tolerance of an aluminum plate reinforced with a co-cured bonded E-glass/epoxy composite laminate under four-point bending. It is concluded that this problem is difficult to characterize and breaking the problem into interacting mechanisms leads to improved information on influential parameters and efficient reduced-dimension surrogate modeling. The disbond damage at the interface between the resin and metal proved the most difficult mechanism for reduced-dimension surrogate modeling as it is only engaged in a small subspace of the full parameter space. A binary function was successful in engaging this damage mechanism when applicable based on the values of the most influential parameters.

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Section: Composite Overlay Backgroundmentioning

confidence: 99%

Section: Composite Overlay Backgroundmentioning

confidence: 99%

Reduced-Dimension Surrogate Modeling to Characterize the Damage Tolerance of Composite/Metal Structures

Arndt,

Crusenberry,

Heng

et al. 2023

Modelling

View full text Add to dashboard Cite

show abstract

“…This includes the complex progressive failure of the composite overlay and the interactions between the multiple damage mechanisms. This complex progressive failure of composite/metal hybrid structures has been investigated in its entirety, a necessary consideration when evaluating the structural performance of the hybrid structure [34][35][36][37][38][39][40]. An aerospace application of composite/metal hybrid structures occurs at stiffener to skin bonding, i.e.…”

mentioning

confidence: 99%

“…Action et al investigated the fail-safe crack arrestment in a T-joint bonded to the aircraft skin [39]. In their research they studied crack arrestment for a multi-loaded bonded T-joint looking at strain energy to predict the delamination and crack propagation.…”

mentioning

confidence: 99%

Nondeterministic Parameter Space Characterization of the Damage Tolerance of a Composite/Metal Structure

Arndt

TerMaath

2022

AIAA SCITECH 2022 Forum

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An integrated experimental, computational, and non-deterministic approach is demonstrated to predict the damage tolerance of an aluminum plate reinforced with a cocured bonded quasi-isotropic E-glass/epoxy composite overlay and to determine the most sensitive material parameters and their ranges of influence on the damage tolerance of the hybrid system. To simulate the complex progressive damage in the repaired structure, a high fidelity three-dimensional finite element model is developed and validated using four-point bend testing to investigate potential damage mechanisms. A surrogate model is then generated to explore the complex parameter space of this model. Global sensitivity analysis and uncertainty quantification are performed for non-deterministic analysis to characterize the energy absorption capability of the patched structure relative to these influential design properties. Additionally, correlating the data quality of the material parameters with the sensitivity analysis results provides practical guidelines for model improvement and the design optimization of the patched structure.

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Weak Bond Study of Adhesively Bonded Composites for Laser Bond Inspection

Barraza

Action

2023

AIAA SCITECH 2023 Forum

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Design of a Fail-Safe Crack Arrested Test Specimen for Certification of Bonded Unitized Composite Structures

Cited by 3 publications

References 6 publications

Reduced-Dimension Surrogate Modeling to Characterize the Damage Tolerance of Composite/Metal Structures

Reduced-Dimension Surrogate Modeling to Characterize the Damage Tolerance of Composite/Metal Structures

Nondeterministic Parameter Space Characterization of the Damage Tolerance of a Composite/Metal Structure

Weak Bond Study of Adhesively Bonded Composites for Laser Bond Inspection

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