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Impact of Carbon Nanotubes on the Mechanical and Electrical Properties of Silicone

Sałaciński Michał, Dydek Kamil, Leski Andrzej, Kozera Rafał, Mucha Mateusz, Karczmarz Wojciech

Fatigue of Aircraft Structures

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2022

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Iss. 14

135--153

EN

This paper presents the results of a structure study of a dispersion composite on a silicone matrix with a filler in the form of multi-walled carbon nanotubes (MWCNTs). The study aims to determine the effect of the filler on the composite mechanical properties and electrical conductivity. Materials that are electrically conductive and exhibit high mechanical properties can find applications in high-strain sensors. During the study, the characteristic properties of the susceptible materials, silicone alone and silicone with different filler contents (4%, 6%, and 8% by weight), were determined after curing. Microscopic observations were performed to assess the influence of carbon fillers on the material structure and to determine the level of homogeneity of the material. Examination of mechanical properties facilitated the determination of the Shor A hardness (ShA), stiffness, and Poisson’s ratio of the cured composites, depending on the nanotubes’ content. In parallel with the study of mechanical properties, the effect of loading, and the associated deformation of the samples, on the conductivity of the composite was investigated. Based on the results obtained, a discussion was carried out on the type of conductivity characteristic of silicone with different filler content as well as depending on the level of deformation of the samples.

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Analysis of bonding layer quality in repair process of aircraft composite structure after impact damage

Sałaciński Michał, Orzechowski Paweł, Chalimoniuk Marek, Leski Andrzej

Composites Theory and Practice

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2020

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R. 20, nr 3-4

134--141

EN

Aircraft composite structures made in autoclave prepreg technology are characterized by low porosity and high strength. Unfortunately, composite structures are susceptible to impact damage. Therefore in order to repair this type of structures, an advantageous method of structure restoration is the use of the two-step bonding method. This method relies on creating a composite patch cured in an autoclave and then bonding it into a previously prepared repair area in the repaired structure, created by removing the damaged layers. Thanks to this approach, the patch is produced in accordance with the production process of the repaired element and has similar properties including low porosity. A critical element of repair is the bonding layer between the patch and repaired structure. Difficulties in obtaining an appropriate consolidation pressure (compression) using a vacuum bag can cause local disbonding of the composite patch as well as porosity in the bonding layer. Porosity reduces the strength properties of the joint, and it also reduces its weather resistance, which may contribute to its gradual degradation. The article focuses on analysis of the influence of compression obtained by a vacuum bag on the porosity and thickness of the bonding layer. A professional line for the production of aircraft composites and a mobile system for composite repairs of aircraft structures were used to produce the samples. The computed tomography method was used to measure the porosity and thickness of the bonding layer.

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A New Approach to Modelling and Testing the Fatigue Strength of Helicopter Rotor Blades during Repair Process

Sałaciński Michał, Kowalski Rafał, Szmidt Michał, Augustyn Sławomir

Fatigue of Aircraft Structures

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2019

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Iss. 11

56--67

EN

The fatigue test was carried out on an element of a rotor blade removed from the Mi-2 helicopter. The purpose of the test was to check the fatigue strength of the repaired rotor blade. Metal composite rotor blades have a metal spar in the form of a box and the trailing sections in the form of metallic honeycomb sandwich panels. The trailing sections are bonded to the spar. The repair had been carried out at the point where the trailing section became debonded from the spar at the Air Force Institute of Technology in Warsaw using a methodology developed for carrying out repairs of rotor blades’ damage. All types of the Mi family helicopters are equipped with metal composite rotors blades. Depending on MTOW (Maximum Take-Off Weight) and destination of helicopters, blades differ in dimensions, but their design solutions are practically the same. For this reason, the developed repair methodology can be used for all characteristic rotor blades structures for Mi helicopters. The fatigue test was performed at the Łukasiewicz - Institute of Aviation in Warsaw, using a hydraulically driven fatigue machine. The fatigue test was carried out by performing over 1.1 million load cycles. In repair places, upon completion of fatigue testing, no damage was found.