Advanced Composite Materials Technology for Rotorcraft through the Use of Nanoadditives

Makeev, Andrew; Bakis, Charles E.; Strauch, Eric; Chris, Mark; Holemans, Peter; Miller, G.P.; Nguyen, Dean; Spencer, Don; Patz, Nicolas

doi:10.4050/jahs.60.032008

Cited by 7 publications

(7 citation statements)

References 7 publications

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“…As damage observations could only be conducted on the microscale, the underlying mechanisms (most likely plastic-void growth and particle debonding) of the fatigue strength increase could not be identified. Compared with results from literature (mainly 3-to 10-fold increases) [13,[16][17][18][19][20][21], the achieved lifetime increase can be considered low but acceptable. It has to be pointed out that the effect on fatigue life crucially depends on particle type, constituents, laminate configuration and load ratio.…”

Section: Discussioncontrasting

confidence: 53%

“…In regards to the effect of load level, average fatigue life enhancements decrease with load level from 263% (at 70% UTS) to 220% (at 28% UTS) meaning a slight increase of the S-N curve slope. The reason for this could not be clarified, however, results in the literature range from slope increases [13,20,22,23] to slope decreases [17,21,27]. With regard to the significance of the results, it must be kept in mind that they refer to autoclave-processed laminates with only a low content of manufacturing-related voids.…”

Section: Discussionmentioning

confidence: 96%

“…Reported results range from decreasing fatigue life [14] up to 100-fold extension [15]. Most results show a 3-to 10-fold increase [13,[16][17][18][19][20][21]. Some authors have also compared the failure mechanisms of particle-modified and unfilled fibre-reinforced plastics.…”

Section: Introductionmentioning

confidence: 99%

“…This is different for ceramic fillers which are available as spherical nanoscale particles with a high modulus. There are several publications in the literature that report improvements in fatigue strength by integrating silica or alumina nanoparticles [13,17,18,20,21,25,26]. Tate et al [13] demonstrate a 3-to 10-fold improvement of fatigue life under tension-tension loading for a GFRP wind energy material containing 6 wt.% of nanosilica particles.…”

Section: Introductionmentioning

confidence: 99%

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Taurine-Modified Boehmite Nanoparticles for GFRP Wind Turbine Rotor Blade Fatigue Life Enhancement

2021

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Advanced nanoparticle-reinforced glass fibre composites represent a promising approach to improving the service life of fatigue-loaded structures such as wind turbine rotor blades. However, processing particle-reinforced resins using advanced infusion techniques is problematic due to, for example, higher viscosity as well as filtering effects. In this work, the effects of boehmite nanoparticles on viscosity, static properties and fatigue life are investigated experimentally. Whereas rheological analysis reveals a significant increase of viscosity in the case of pristine boehmite particles, an additional taurine surface modification of the particles can effectively reduce viscosity increase. As regards mechanical properties, significant improvements of both static as well as fatigue properties are found. The addition of 15 wt.% of boehmite particles increases fatigue life by a maximum of 270% compared to the unmodified fibre-reinforced epoxy. Transmitted light-based investigation of the damage mechanisms shows delayed initiation and smaller growth rates for laminates containing boehmite particles. At the same time, the observed mechanisms and their accumulation along the relative cycle number do not change significantly. In addition, by characterising autonomous heating, the so-called Risitano fatigue limit is determined. The results reveal that with increasing particle content there is an increase in the fatigue limit.

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Section: Discussioncontrasting

confidence: 53%

Section: Discussionmentioning

confidence: 96%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Taurine-Modified Boehmite Nanoparticles for GFRP Wind Turbine Rotor Blade Fatigue Life Enhancement

2021

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“…In this work, we will employ an untoughened IM7/PMT-F7 low-viscosity 350º F curing composite material system developed by Patz Materials and Technologies (PMT) as a basis for nanosilica reinforcement of the epoxy matrix throughout the composite material designed for improving fiber-direction compression and interlaminar strength and fatigue material performance compared to the legacy systems such as IM7/8552 (Ref. 12). Manufacturability has been an important role in engineering the PMT-F7 epoxy resin.…”

Section: Introductionmentioning

confidence: 99%

Analysis Methods for Improving Confidence in Material Qualification for Laminated Composites

Makeev¹,

Seon²,

Nikishkov³

et al. 2019

j am helicopter soc

Self Cite

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Fiber-reinforced composite materials are increasingly used in rotorcraft structures to reduce weight and improve efficiency. A major challenge, delaying the implementation of recently developed higher-performance materials that offer improved mechanical strength and stiffness at a lower weight, is the lack of efficient common material qualification. The current standard practices are too costly and time-consuming. Due to low confidence in material allowables, the entire material qualification process, including numerous test methods and large test matrices, must be repeated for every seemingly minute change in the composite system. This work presents initial results of research activities under the National Rotorcraft Technology Center, focused on utilizing recent advances in understanding complex deformation and failure mechanisms of polymer-matrix composites towards the development of consolidated common analysis processes. These common processes will enable reduced material qualification test matrices potentially accommodating substitution of resin types and other modifications of the material systems. In particular, analysis methods, developed at the University of Texas Arlington Advanced Materials and Structures Lab, are verified on carbon-fiber reinforced / untoughened and toughened polymer-matrix composite material systems. Due to well-recognized susceptibility of polymeric composites to matrix-dominated failures, thorough verification of the analysis methods using a range of the matrix types is required for improving confidence in the analysis-based material allowables accelerating material qualification.

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Mechanical response and damage evolution of CF/PEEK‐reinforced Al metal‐composite hybrid structure at high strain rate

Nie,

Wang,

Chen

et al. 2024

Polymer Composites

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A CF/PEEK‐reinforced Al metal‐composite hybrid structure (CF/PEEK/Al) and CF/PEEK bar were subjected to high strain rate compression tests with a split Hopkinson pressure bar (SHPB). With the increase in strain rates, both CF/PEEK and CF/PEEK/Al showed the strain rate strengthening effect, and the microscopic fracture surface of CF/PEEK changes from rough to smooth. In the plastic rheological stage of stress–strain curve, CF/PEEK shows a plateau effect, while CF/PEEK/Al shows the strain weakening effect. When the strain rate exceeds 3800 s−1, the stress–strain curve exhibits a secondary wave peak. The peak values of the secondary peak in CF/PEEK/Al are larger than CF/PEEK. In terms of peak stress, yield stress, and specific energy absorption, CF/PEEK/Al outperforms CF/PEEK. Compared with other structures, the CF/PEEK/Al metal‐composite hybrid structure has certain advantages in terms of yield strength and yield strain. The finite element method (FEM) and DIC system were applied to observe the dynamic damage process in the compression impact test. It was found that in CF/PEEK/A1, the Al thin‐walled tube was damaged and cracked at the contact interface, and the inner CF/PEEK began to be damaged at the contact center with the input bar. And at 335 μs after contact began, the shear band ran through to the side of the samples.Highlights A CF/PEEK‐reinforced Al metal‐composite hybrid structure (CF/PEEK/Al) was proposed, which is superior to CF/PEEK. When the strain rate exceeds 3800 s−1, the stress–strain curves of CF/PEEK and CF/PEEK/Al exhibit a secondary wave peak. The peak values of the secondary peak in CF/PEEK/Al are larger than CF/PEEK. With the increase in strain rates, both CF/PEEK and CF/PEEK/Al showed the strain rate strengthening effect, and the microscopic fracture surface of CF/PEEK changes from rough to smooth. In CF/PEEK/A1, the Al thin‐walled tube was damaged and cracked at the contact interface, and the inner CF/PEEK began to be damaged at the contact center with the input bar. And at 335 μs after contact began, the shear band ran through to the side of the samples.

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Advanced Composite Materials Technology for Rotorcraft through the Use of Nanoadditives

Cited by 7 publications

References 7 publications

Taurine-Modified Boehmite Nanoparticles for GFRP Wind Turbine Rotor Blade Fatigue Life Enhancement

Taurine-Modified Boehmite Nanoparticles for GFRP Wind Turbine Rotor Blade Fatigue Life Enhancement

Analysis Methods for Improving Confidence in Material Qualification for Laminated Composites

Mechanical response and damage evolution of CF/PEEK‐reinforced Al metal‐composite hybrid structure at high strain rate

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