International Scientific Journals
of Scientific Technical Union of Mechanical Engineering "Industry 4.0"

Recent researches have shown that Nano-coating materials play a vital role in improving the performance of the PV cell operation, enhancing the life span and reducing its surface temperature. In addition to that, the Nano-coating can achieve many benefits such as making a smoother surface, stronger and less adhesive of externous on the surface of PV panel. In this work, the effect of nanomaterials coating using Titanium dioxide, silicon dioxide and Nano fluid Titanium dioxide on performance and temperature of PV cell when coated by these Nano particles separately with different thicknesses (0.5μm, 50μm,100μm and 300μm). To achieve these objectives ANSYS software technology (version.1) was used. The results showed that there is a significant effect specifically when using TiO2 Nano fluid. The maximum improvements were when using Nano coating TiO2 and SiO2 which are (0.62%) and (0.135%), respectively, at thickness 300μm and ambient temperature16 ͦ C in case without externous particles. But the minimum improvement was with TiO2 and SiO2 of coating thickness 0.5μm which are (0.0937%) and (0.0937%), respectively, at ambient temperature 23 ͦ C in presence of dust. The results of TiO2 Nano fluid with concentration and flow rate which are (5%and 0.01 kg/s), respectively, showed that the maximum improvement was (39.88%) in case without externous particles at ambient temperature 23 ͦ C, but the minimum improvement was (37.84%) in case with dust at ambient temperature 16 ͦ C.

The article presents a comprehensive study on the enhancement of ballistic protection for the consumption fuel tank of the Mi-171 transport helicopter, which is deployed in conflict zones across various countries. The study examines the helicopter’s critical areas, evaluates the levels of ballistic protection, and proposes solutions for augmenting the consumption fuel tank’s protection against firing. Three variants of potential ballistic protection are suggested, utilizing commercially available armours: steel Hardox 450, aluminium alloy Al 7039, and titanium alloy Ti-6AL-4V. The analysis is conducted using the Ansys Workbench software, aiming to determine the required thickness of homogeneous armour to achieve ballistic level 2 according STANAG 4569, capable of withstanding penetration by 7.62 39 API BZ ammunition. The study estimates the ballistic limit thickness necessary to prevent perforation of the ballistic protection panel. The simulation procedure and the material models of the armours employed are thoroughly described. Additionally, the study evaluates the weight of the protection system to identify the material with the minimum weight, thereby preserving aircraft performance. Notably, the use of titanium alloy and steel results in the greatest reduction in the weight of the protective system, with their masses being nearly identical. In contrast, the aluminum alloy exhibits a mass that is approximately 11% higher. A method for installing the armours on the helicopter is also proposed. The findings of this study are valuable for analysing airframe structures that face ballistic threats during military operations or terrorist attacks. Proposals for further refinement and a shooting experiment are discussed to enhance the accuracy and effectiveness of the protection solutions.

The article proposes a cost-effective and rapid method for the preliminary verification of an optimized metal air brake bracket using a 3D-printed polymer model. The original bracket, used in light jet aircraft, is made of the aluminium alloy Al 2024 T351 and manufactured using conventional CNC machining technology. The study presents a structural optimized bracket, intended to be produced using 3D printing technology with AlSi10Mg material to reduce weight. The bracket is presented along with its static load, stress-strain analysis, and the weight structural optimization procedure using ANSYS Workbench. Modifications to the bracket’s shape were made to meet the static stress-strain and buckling characteristics of the original bracket, resulting in a 32% weight reduction. The complex model of the optimized bracket was verified both numerically using ANSYS Workbench and experimentally using 3D-printed bracket models made from substitute polymer ASA material, printed with the Prusa Mk3 printer. The article also presents the results of basic tensile material tests on ASA material coupons printed in various positions to determine the semi-isotropic characteristics necessary for numerical analysis. The substitute material bracket provides potential for indicative verification of the numerically optimized model, though its usage is limited. Finally, the article offers recommendations for further research.

Laser Powder Bed Fusion (LPBF) is a prominent additive manufacturing process used for fabricating complex metallic structures, but it often encounters challenges related to thermal distortions and residual stresses, particularly in thin-walled structures. These issues compromise the integrity and dimensional accuracy of the parts. Finite Element Analysis (FEA) has been essential in simulating and understanding the thermal and mechanical behaviors during the LPBF process. This study focuses on validating a refined FEA model developed using ANSYS Additive Print (AAP) to predict the thermal distortions in CoCr thin-wall structures. The validation involves comparing simulation results with experimental data to verify the model’s effectiveness. The study demonstrates the integration of advanced simulation techniques in predicting distortions and stresses, thereby enhancing the reliability and accuracy of the manufacturing process.

This scientific report focuses on investigating the influence of geometric design on ship ventilation flow efficiency through numerical simulation with ANSYS. Many sources on the subject state that in a ship’s ventilation system, the flowing fluid encounters various devices and fixtures such as valves, fans, and bends that can cause sudden expansions or contractions of the flow. These geometric factors cause energy loss, which can be of importance to the efficiency of the ship’s ventilation system, especially in the complex conditions of power generation. Such energy losses are considered significant in these industries and are the subject of serious design and optimization of flow systems. Using engineering simulations, this report investigates steady laminar flow through a pipe with sudden expansion in order to understand and predict the energy losses resulting from the expansion. The practical example of application can be the analysis of the ventilation system of a ship, where such geometric designs can affect the efficiency of the ventilation and therefore the performance and safety of the crew and passengers. Such research is essential to improve the manufacturing and operational processes of ships and to ensure their optimal working conditions.

This study presents to determine the contact stress in rolling bearings by using analytical and numerical method. Analytical solution is obtained by using Hertizan contact theory. Obtained analytical solution by this theory require comparison with the numerical calculations to obtain more accurate results for contact problems. Because of that the same problems are also examined by using finite element method. The geometry of the model being studied gives different type of contact configurations such as a point or line of contact. In cylindrical roller bearing the contact form is line contact and for the ball bearing the contact characteristic is point contact. High stress occurs on both of these two contact areas. Contact stress causes elastic or plastic deformation and the contact area will change depending on the magnitude of the contact stress. Therefore, it is really important to calculate more accurate stress at the contact area.

The aim of this work is to extract modal parameters of a light aircraft wing. Modal parameters like natural frequencies, and mode shapes characterise the dynamic response of a structure and can be used for determining of the wing divergence and flutter. The CAD (Computer-Aided Design) model plays a pivot role in the design and development phases of an aircraft. Creating drawings, preparing reports of assembly and part drawings, preparing bill of materials, the aircraft design becomes easier and faster with the use of CAD system.
CAD model has to be imported in FEM (Finite Element Method) software, and so it can do FE model, which have to be solved. In this work a light aircraft wing is modelled by SolidWorks software. After that the CAD model is imported in ANSYS Workbench. The FE model is generated and solved by using ANSYS Workbench. The first six natural frequencies and mode shapes are shown for the proposed light aircraft wing.