Browse Topic: Computed tomography (CT)
ABSTRACT
The digital twin (DT) refers to a digital replica or virtual model of actual physical product or process that can be applicable for various purposes. In this study, a digital reproduction of the next generation active twist blade, meeting superior durability characteristics and high strength requirements under severe operating environments of a helicopter rotor, is attempted using the up-to-date computed tomography (CT) scheme combined with modern digital image processing technique. The CT scan covers much portion of the blade root, transition, and tip regions where substantial variations in external geometries and/or interior structural layouts are present while limited zones in the airfoil blade region being considered as nonuniform. A three-dimensional (3D) finite element-based DT simulation model is constructed using the high-resolution CT-scan images. The detailed lamination geometries and sequences of layered composites in the blade skin and spar are implemented in the DT model which can be exploited further for durability study or strength analysis. The reconstructed 3D analysis model is used to determine the structural properties of the blade. In parallel, either mechanical or optical measurement methods along with two-dimensional (2D) blade sectional analysis are carried out to cross validate their predictions. Overall, fair to good correlation is obtained between the different set of results. The agreement is good for mass, elastic axis, and flap bending while less satisfactory results are obtained with the torsion rigidity. A sensitivity analysis is also conducted to clarify the impact of modeling cables, nose weight, and manufacturing imperfections on the structural property evaluation of the blade.
We are living in a digitally integrated and connected world. Evidenced by the use of smartphones, smartwatches, and other smart devices, there is no ending this trend. This holds true across many industries and applications, but is especially prevalent within medtech devices — a market that’s predicted to reach $432.6 billion by 2025.1
Metal additive manufacturing (AM) has become increasingly popular to fabricate complex, light-weight, and high- efficiency components for use in the aerospace industry; however, there are inherent limitations in existing AM processes that have delayed widespread implementation for aviation applications. Porosity is just one example of the key characteristics that can impact the mechanical strength of an AM part. This research focuses on a real-time feedback system to detect and correct defects during the powder bed fusion process of aluminum alloys. In this study, AlSi10Mg coupons were built using various AM parameters. The build process was continuously monitored via a high-frequency in-situ infrared camera which had been integrated into a commercial metal powder bed fusion machine. Porosity information (pore location and size) of the as-built AM coupons were characterized using x-ray computed tomography. The monitoring results were post processed and correlated with porosity location, indicating a strong relationship between abnormal sensing signal and pore formation. This demonstrates that the real-time abnormal sensing signal can be a good indicator for identifying pore formation during the AM process. Additionally, Sentient Science Corporation (Sentient) used its advanced modeling technique to simulate the AM build process regarding the melt pool geometry, porosity, and microstructure. Prediction of porosity level at different AM parameters aligned well with the experimental results. Advanced modeling results showed that careful selection of AM settings is required to correct in-process defects. Repair parameters must be tailored to achieve satisfactory correction of individual defects. Combining the in-situ defect monitoring and advanced simulation capabilities enables the creation of a closed-loop feedback control system that provides automatic defect detection and correction action in powder bed additive manufacturing process.
ABSTRACT Voids and ply waviness are the most common types of fabrication process induced defects in composite structures that can have detrimental effects on their load bearing capacity. To date, extensive works have been done on the characterization of fabrication induced defects on the mechanical properties of composites but less study has been performed to determine the effects of defects on the failure progression. Given the durability and damage tolerance requirements for certification and design of composite structures, it is important to evaluate the effects of these defects on the damage initiation and failure progression of a loaded composite structure. In this study, void and ply waviness information are extracted from X-ray computed tomography (CT) and optical microscopy and an efficient image-to-numerical solution is developed to map the detected voids and ply waviness into a finite element based progressive failure analysis model. An interlaminar tensile (ILT) test specimen under four point bending is used to demonstrate the capability of our response and progressive damage prediction.
ABSTRACT Composite helicopter rotor components are typically thick and often have areas with a tight radius of curvature, which make them especially prone to process-induced defects, including wrinkles and voids at ply interfaces. Such flaws cause high rejection rates in production of flight-critical components and structure. This work seeks to fill the gaps in understanding generation of the noted defects in contoured polymer-matrix composite (PMC) laminates. In particular, understanding and modelling defect formation at the early stages of the manufacturing process might be the missing link to enable the development of practical engineering solutions allowing for better control of the manufacturing process of contoured composite parts. In this work, an approach based on a continuum description of the uncured prepreg material, including the initial bulk or void content, and finite element modelling (FEM) is used to simulate the consolidation process at the early stages of manufacturing of contoured laminates. The simulation predicts instabilities leading to formation of both wrinkles and voids at ply interfaces during laminate debulking or vacuum consolidation. Applicability of the method to consolidation in both closed-cavity and open-face tooling is also demonstrated. FEM results show good correlation with X-ray Computed Tomography data. This work also introduces a new simulation concept based on finite element and discrete modelling of voids at ply interfaces to improve accuracy of predicting their evolution during the debulking operations.
In response to the need for lightweight design in industries, composite materials are increasingly used to replace traditional metal tubes. However, subsurface defects such as voids, delaminations, and microcracks are still remaining common issues in composite pressure tubes. This paper introduces an application of Digital Shearography method in the Non-Destructive Testing (NDT) of high-pressure composite tubes. A new prototype high-pressure composite tube with a working pressure of 1000 psi range is tested using the digital Shearography method. To detect the sub-surface defects, a reference Shearographic phase map is created at 0 psi state, after that the composite tube is pressured using an oil pump, then the second Shearographic phase map is created at the pressured state. By subtracting the two shearographic phase maps created in different pressure state, the sub-surface defects can be identified clearly. The Shearographic NDT result is then compared with CT scan result. The Shearographic NDT fundamentals, optimization of Shearographic NDT setup for high rigidity objects, experiment setup, and testing results are shown in detail in this paper.
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