Pub Date : 2024-06-10DOI: 10.13111/2066-8201.2024.16.2.7
Marilena D. Pavel
Advanced nonlinear controllers are a desirable solution to rotorcraft flight control as they can solve the system high nonlinear dynamic behavior. However, conventional nonlinear controllers such as Nonlinear Dynamic Inversion (NDI) controller heavily rely on the availability of accurate model knowledge and this can be problematic for rotorcraft. Therefore, incremental control theory can solve the modelling errors sensitivity by relying on the information obtained from the sensors instead. The paper applied the Incremental Nonlinear Dynamic Inversion (INDI) controller to rotorcraft case. It will be demonstrated that, for rotorcraft, the incremental nonlinear controllers depend on the delays introduced in the controller by the rotor dynamics. To correct this behaviour, residualization and synchronization methods need to be applied accordingly in order to remove the effects of rotor flapping (disctilt) dynamics from the controller. These particularities of rotorcraft in dealing with advanced controllers shows that incremental nonlinear controllers can have relatively small stability robustness margin and careful controller design is needed in order to account properly for rotorcraft time delays and unmodelled dynamics.
{"title":"Particularities of Rotorcraft in Dealing with Advanced Controllers","authors":"Marilena D. Pavel","doi":"10.13111/2066-8201.2024.16.2.7","DOIUrl":"https://doi.org/10.13111/2066-8201.2024.16.2.7","url":null,"abstract":"Advanced nonlinear controllers are a desirable solution to rotorcraft flight control as they can solve the system high nonlinear dynamic behavior. However, conventional nonlinear controllers such as Nonlinear Dynamic Inversion (NDI) controller heavily rely on the availability of accurate model knowledge and this can be problematic for rotorcraft. Therefore, incremental control theory can solve the modelling errors sensitivity by relying on the information obtained from the sensors instead. The paper applied the Incremental Nonlinear Dynamic Inversion (INDI) controller to rotorcraft case. It will be demonstrated that, for rotorcraft, the incremental nonlinear controllers depend on the delays introduced in the controller by the rotor dynamics. To correct this behaviour, residualization and synchronization methods need to be applied accordingly in order to remove the effects of rotor flapping (disctilt) dynamics from the controller. These particularities of rotorcraft in dealing with advanced controllers shows that incremental nonlinear controllers can have relatively small stability robustness margin and careful controller design is needed in order to account properly for rotorcraft time delays and unmodelled dynamics.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-06-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141361400","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
The development of space launch systems requires rigorous testing and validation of safety mechanisms to ensure the protection of human life and mission-critical assets. One such safety mechanism is the Active Launch Escape/Abort System (ALEAS), designed to swiftly extract crew and spacecraft from a malfunctioning launch vehicle. To evaluate the performance of ALEAS, wind tunnel testing is indispensable. This paper presents the development of a specialized Jets Rig tailored for wind tunnel testing of an ALEAS model. The primary objectives of this research activity include the design, construction, and validation of a Jets Rig that can accurately simulate the propulsion dynamics of an ALEAS system within a wind tunnel environment. The Jets Rig incorporates a special instrumentation and control systems to replicate the complex operational conditions experienced during a launch abort scenario. By achieving this, it enables a comprehensive assessment of ALEAS performance, including thrust duration and plume interaction effects, among others. Key aspects of this study encompass the aerodynamic and structural considerations involved in designing the Jets Rig, the integration of high-fidelity sensors and data acquisition systems, and the development of advanced computational models for predictive analysis. Additionally, the research explores the challenges and solutions associated with the scalability of the Jets Rig to accommodate varying scales of ALEAS models. The findings from this project hold significant implications for advancing the safety and reliability of crewed space missions. A comprehensive understanding of ALEAS performance in a wind tunnel setting allows for the refinement of design parameters, algorithms, and the enhancement of abort system efficiency. Ultimately, the successful development of this dedicated Jets Rig contributes to the broader mission of ensuring the safe exploration of space and the protection of human life in the challenging and dynamic environment of space launch.
{"title":"Development of Jets rig dedicated for an Active Launch Escape Abort System Wind Tunnel Model","authors":"M. Stoican, Marina Andrei, Tiberiu Salaoru, Ionuț Bunescu, Mihai-Vlăduţ Hothazie, Mihai-Victor Pricop","doi":"10.13111/2066-8201.2024.16.2.10","DOIUrl":"https://doi.org/10.13111/2066-8201.2024.16.2.10","url":null,"abstract":"The development of space launch systems requires rigorous testing and validation of safety mechanisms to ensure the protection of human life and mission-critical assets. One such safety mechanism is the Active Launch Escape/Abort System (ALEAS), designed to swiftly extract crew and spacecraft from a malfunctioning launch vehicle. To evaluate the performance of ALEAS, wind tunnel testing is indispensable. This paper presents the development of a specialized Jets Rig tailored for wind tunnel testing of an ALEAS model. The primary objectives of this research activity include the design, construction, and validation of a Jets Rig that can accurately simulate the propulsion dynamics of an ALEAS system within a wind tunnel environment. The Jets Rig incorporates a special instrumentation and control systems to replicate the complex operational conditions experienced during a launch abort scenario. By achieving this, it enables a comprehensive assessment of ALEAS performance, including thrust duration and plume interaction effects, among others. Key aspects of this study encompass the aerodynamic and structural considerations involved in designing the Jets Rig, the integration of high-fidelity sensors and data acquisition systems, and the development of advanced computational models for predictive analysis. Additionally, the research explores the challenges and solutions associated with the scalability of the Jets Rig to accommodate varying scales of ALEAS models. The findings from this project hold significant implications for advancing the safety and reliability of crewed space missions. A comprehensive understanding of ALEAS performance in a wind tunnel setting allows for the refinement of design parameters, algorithms, and the enhancement of abort system efficiency. Ultimately, the successful development of this dedicated Jets Rig contributes to the broader mission of ensuring the safe exploration of space and the protection of human life in the challenging and dynamic environment of space launch.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-06-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141364592","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-06-10DOI: 10.13111/2066-8201.2024.16.2.6
Vibhanshu Dev Gaur, Mayur Pathak, Tejinder Kumar Jindal
Pulse Detonation Engine has been a point of interest in the propulsion industry for some time and the interest has been rising due to its better output and results. But any system can perform its task efficiently based on the efficiency of its control system. In this paper we have presented a comparative study between multiple control systems- one based on Bluetooth technology, the other based on infrared sensor technology and one based on wired electrical system. For the wireless system, the signal received from either of the media is passed to the various sensors and systems connected through an Arduino board that further controls the solenoid valves and ignition system. Primarily, a control system circuit is developed using Arduino board and different sensors to connect the fuel supply and ignition system. In the next stage, Bluetooth sensors are connected using an android app and then an infrared sensor based system is integrated with the Arduino to control the engine and the performance of the two systems are compared. Whereas for wired system, every sub system is controlled through optical wires including the solenoid valves, the injection system and the sensors.
{"title":"A comparative study based on control system for a pulse detonation engine","authors":"Vibhanshu Dev Gaur, Mayur Pathak, Tejinder Kumar Jindal","doi":"10.13111/2066-8201.2024.16.2.6","DOIUrl":"https://doi.org/10.13111/2066-8201.2024.16.2.6","url":null,"abstract":"Pulse Detonation Engine has been a point of interest in the propulsion industry for some time and the interest has been rising due to its better output and results. But any system can perform its task efficiently based on the efficiency of its control system. In this paper we have presented a comparative study between multiple control systems- one based on Bluetooth technology, the other based on infrared sensor technology and one based on wired electrical system. For the wireless system, the signal received from either of the media is passed to the various sensors and systems connected through an Arduino board that further controls the solenoid valves and ignition system. Primarily, a control system circuit is developed using Arduino board and different sensors to connect the fuel supply and ignition system. In the next stage, Bluetooth sensors are connected using an android app and then an infrared sensor based system is integrated with the Arduino to control the engine and the performance of the two systems are compared. Whereas for wired system, every sub system is controlled through optical wires including the solenoid valves, the injection system and the sensors.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-06-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141366037","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-06-10DOI: 10.13111/2066-8201.2024.16.2.1
O. Abada, H. Kbab, S. Haif
The aim of this paper is to develop a profile of axisymmetric minimum length nozzle giving a uniform and parallel flow at the exit section. The study is done at high temperature, lower than the dissociation threshold of the molecules. The design is made by the method of characteristics (MOC). The variation of the specific heats with the temperature is considered. The numerical results have been validated with CFD simulation Ansys-Fluent software. The second part of this study is to calculate and analyze the transonic flow field of this supersonic nozzle. The computation of the flow field characteristics at the throat is thus essential to the nozzle developed thrust value and therefore to the aircraft or rocket it propels. An investigation was conducted to analyze the effects of parameters on the position of the sonic line. These parameters include stagnation temperature T0, radius of the nozzle, types of gases, and exit Mach number ME.
{"title":"Transonic Flow Field Analysis of a Minimum Nozzle Length Rocket Engine","authors":"O. Abada, H. Kbab, S. Haif","doi":"10.13111/2066-8201.2024.16.2.1","DOIUrl":"https://doi.org/10.13111/2066-8201.2024.16.2.1","url":null,"abstract":"The aim of this paper is to develop a profile of axisymmetric minimum length nozzle giving a uniform and parallel flow at the exit section. The study is done at high temperature, lower than the dissociation threshold of the molecules. The design is made by the method of characteristics (MOC). The variation of the specific heats with the temperature is considered. The numerical results have been validated with CFD simulation Ansys-Fluent software. The second part of this study is to calculate and analyze the transonic flow field of this supersonic nozzle. The computation of the flow field characteristics at the throat is thus essential to the nozzle developed thrust value and therefore to the aircraft or rocket it propels. An investigation was conducted to analyze the effects of parameters on the position of the sonic line. These parameters include stagnation temperature T0, radius of the nozzle, types of gases, and exit Mach number ME.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-06-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141363668","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-06-10DOI: 10.13111/2066-8201.2024.16.2.3
Mircea Bocioaga, Cristian Moisei, Octavian Nistor, Ciprian Bacria, Denise Nitescu, Daniela Baran
The purpose of this paper is to extend structural optimization capabilities of some FEA softs (NASTRAN/PATRAN, MARC-MENTAT) by coupling them with MATLAB codes in order to develop light weight design based on machine learning principles. We apply these ideas to some composite material with gyroid structure. The obtained results are interesting from both a theoretical and a practical point of view, shortening the design cycle for this type of materials.
{"title":"Extending structural optimization capabilities of FEA softs according to machine learning principles","authors":"Mircea Bocioaga, Cristian Moisei, Octavian Nistor, Ciprian Bacria, Denise Nitescu, Daniela Baran","doi":"10.13111/2066-8201.2024.16.2.3","DOIUrl":"https://doi.org/10.13111/2066-8201.2024.16.2.3","url":null,"abstract":"The purpose of this paper is to extend structural optimization capabilities of some FEA softs (NASTRAN/PATRAN, MARC-MENTAT) by coupling them with MATLAB codes in order to develop light weight design based on machine learning principles. We apply these ideas to some composite material with gyroid structure. The obtained results are interesting from both a theoretical and a practical point of view, shortening the design cycle for this type of materials.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-06-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141362785","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-06-10DOI: 10.13111/2066-8201.2024.16.2.4
Nabila Dellal, M. Merzoug, Abdelatif Mimmi, Nabil Benamara
The friction stir welding (FSW) procedure is the main topic of this research study among the various welding techniques. The study focuses on the interaction between the mechanical properties of 3003 aluminum alloy and the process parameters (rotation speed, welding speed, and dwell time) in the form of rolled plates of 2 mm thickness, end-to-end and welded at 90° and 45°. The welds were made by varying the speed of rotation (1000, 2000 rpm) and setting the tool feed at 500 mm/min. This experimental approach is also based on varying the tilt of the welding tool from 0° to 2°. It has been shown that the studied parameters play an important role in the characterization and optimization of the above mentioned weld joints. Therefore, and based on the results obtained, the use of the 90° joint remains the best in terms of strength.
{"title":"Relationship between mechanical behavior and process factors in friction stir welding aluminum alloys","authors":"Nabila Dellal, M. Merzoug, Abdelatif Mimmi, Nabil Benamara","doi":"10.13111/2066-8201.2024.16.2.4","DOIUrl":"https://doi.org/10.13111/2066-8201.2024.16.2.4","url":null,"abstract":"The friction stir welding (FSW) procedure is the main topic of this research study among the various welding techniques. The study focuses on the interaction between the mechanical properties of 3003 aluminum alloy and the process parameters (rotation speed, welding speed, and dwell time) in the form of rolled plates of 2 mm thickness, end-to-end and welded at 90° and 45°. The welds were made by varying the speed of rotation (1000, 2000 rpm) and setting the tool feed at 500 mm/min. This experimental approach is also based on varying the tilt of the welding tool from 0° to 2°. It has been shown that the studied parameters play an important role in the characterization and optimization of the above mentioned weld joints. Therefore, and based on the results obtained, the use of the 90° joint remains the best in terms of strength.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-06-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141362599","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-06-10DOI: 10.13111/2066-8201.2024.16.2.9
V. Prisacariu, Irina Andrei, Eduard Mihai
The properties of the fuels determine the quality of the combustion process and implicitly the performance of the turbojet engine. The optimal heterogeneous combustion process of an aviation fuel is ensured by a stoichiometric ratio (fuel/fuel), a combustion temperature and a maximum loading degree of the combustion chamber. The article includes a numerical analysis instrumented with Gasturb software that highlights the influence of fuel quality and combustion process characteristics of a Rolls Royce Viper turbojet engine on its performance.
{"title":"Analyzes regarding aviation fuels parameters use on jet engines","authors":"V. Prisacariu, Irina Andrei, Eduard Mihai","doi":"10.13111/2066-8201.2024.16.2.9","DOIUrl":"https://doi.org/10.13111/2066-8201.2024.16.2.9","url":null,"abstract":"The properties of the fuels determine the quality of the combustion process and implicitly the performance of the turbojet engine. The optimal heterogeneous combustion process of an aviation fuel is ensured by a stoichiometric ratio (fuel/fuel), a combustion temperature and a maximum loading degree of the combustion chamber.\u0000The article includes a numerical analysis instrumented with Gasturb software that highlights the influence of fuel quality and combustion process characteristics of a Rolls Royce Viper turbojet engine on its performance.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-06-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141363179","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-06-10DOI: 10.13111/2066-8201.2024.16.2.5
H. Dumitrescu, V. Cardoş, Radu Bogateanu
The Euler’s holomorphic regenerative universe is a quantum-gravitational theory of Earth development recognizing that oxygen, hydrogen, nitrogen and carbon dioxide in the Earth’s hydrosphere engender biological processes along with living organisms able to reshape the planet as surely as any physical force, but with delayed effects, the so-called torsional/gravitational buckling lag. Herein, the environmental sciences as a Vernadsky’s hypothesis precursor to these, become vital for preserving biological recurrent cycles, their nature being artificially changed by a vicious human intervention. The present paper describes the thermal gravitational mechanism of a solar system associated with the regenerative processes of molecular structures (in biology called metabolism or growth) at the quantum-gravitational scale, too slow to be perceived. The term “morph” (or the concept of “morphing” in aeronautics, in mathematics called topological holomorphism) originates from ancient Greeks and refers to the shape, figure, or other related aspects of an evolving entity. Therefore, morphing/morphism pertains to the process of modifying the original form or appearance of a particular object or system. The planets of solar system like “cosmic organisms” can manipulate the curvature and twist of their surfaces to maintain precise control over their recurrent cyclical complex motions (double, orbital and sideral rotations) by the thermal gravitational waves. The out of order function of the thermal gravitational mechanism can lead to the global warming effects associated with both reshaping (earthquakes, fires, floods) surfaces and morphing (as a whole energy metabolism) mutations, crucial for perpetuity of human beings. At the same time, the concept of quantum-gravity light with a topological dual isomorphic structure solves the fundamental problem of a unified theory of physical forces, as kinematic fast dynamo electromagnetic forces for splitting quanta bonded into atomic structures, and persistent (long time) gravitational forces for non-splitting quanta bonded into thermomolecular morphing structures. The only problem remains to gauge such multiple cooperative physical phenomena induced by light, which is solved by diverse reciprocity/equivalence theorems and corresponding conversion factors.
{"title":"The regenerative solar system. Unified theory of physics","authors":"H. Dumitrescu, V. Cardoş, Radu Bogateanu","doi":"10.13111/2066-8201.2024.16.2.5","DOIUrl":"https://doi.org/10.13111/2066-8201.2024.16.2.5","url":null,"abstract":"The Euler’s holomorphic regenerative universe is a quantum-gravitational theory of Earth development recognizing that oxygen, hydrogen, nitrogen and carbon dioxide in the Earth’s hydrosphere engender biological processes along with living organisms able to reshape the planet as surely as any physical force, but with delayed effects, the so-called torsional/gravitational buckling lag. Herein, the environmental sciences as a Vernadsky’s hypothesis precursor to these, become vital for preserving biological recurrent cycles, their nature being artificially changed by a vicious human intervention. The present paper describes the thermal gravitational mechanism of a solar system associated with the regenerative processes of molecular structures (in biology called metabolism or growth) at the quantum-gravitational scale, too slow to be perceived. The term “morph” (or the concept of “morphing” in aeronautics, in mathematics called topological holomorphism) originates from ancient Greeks and refers to the shape, figure, or other related aspects of an evolving entity. Therefore, morphing/morphism pertains to the process of modifying the original form or appearance of a particular object or system. The planets of solar system like “cosmic organisms” can manipulate the curvature and twist of their surfaces to maintain precise control over their recurrent cyclical complex motions (double, orbital and sideral rotations) by the thermal gravitational waves. The out of order function of the thermal gravitational mechanism can lead to the global warming effects associated with both reshaping (earthquakes, fires, floods) surfaces and morphing (as a whole energy metabolism) mutations, crucial for perpetuity of human beings. At the same time, the concept of quantum-gravity light with a topological dual isomorphic structure solves the fundamental problem of a unified theory of physical forces, as kinematic fast dynamo electromagnetic forces for splitting quanta bonded into atomic structures, and persistent (long time) gravitational forces for non-splitting quanta bonded into thermomolecular morphing structures. The only problem remains to gauge such multiple cooperative physical phenomena induced by light, which is solved by diverse reciprocity/equivalence theorems and corresponding conversion factors.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-06-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141366527","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-06-10DOI: 10.13111/2066-8201.2024.16.2.8
Cristina-Elisabeta Pelin, G. Pelin
This paper presents a study regarding the obtaining, characterizing and mechanically testing a new laminar composite material, consisting of epoxy resin reinforced with basalt plain fabric. The composites were obtained by manual lay-up, cross-link stage being developed by pressure molding in a hydraulic press. Rectangular plates were obtained and cut into samples with specific shapes, for the mechanical tests (tensile, three-point bending and compression). After testing, the fracture zone was analyzed using optical microscopy to observe the behavior of the composite following the mechanical stresses applied (fracture mechanism, voids presence and fiber delamination identification). Due to the low costs and non-hazardous nature, basalt fibers can be a serious competitor in the production of laminar composites that could successfully replace ordinary glass fiber composites. The mechanical properties in tensile, three-point bending, and compression of epoxy-resin-impregnated basalt fiber composites are comparable and even exceed those of widely used epoxy-resin-impregnated fiberglass composites.
{"title":"Mechanical properties of basalt fiber/ epoxy resin composites","authors":"Cristina-Elisabeta Pelin, G. Pelin","doi":"10.13111/2066-8201.2024.16.2.8","DOIUrl":"https://doi.org/10.13111/2066-8201.2024.16.2.8","url":null,"abstract":"This paper presents a study regarding the obtaining, characterizing and mechanically testing a new laminar composite material, consisting of epoxy resin reinforced with basalt plain fabric.\u0000The composites were obtained by manual lay-up, cross-link stage being developed by pressure molding in a hydraulic press. Rectangular plates were obtained and cut into samples with specific shapes, for the mechanical tests (tensile, three-point bending and compression). After testing, the fracture zone was analyzed using optical microscopy to observe the behavior of the composite following the mechanical stresses applied (fracture mechanism, voids presence and fiber delamination identification).\u0000Due to the low costs and non-hazardous nature, basalt fibers can be a serious competitor in the production of laminar composites that could successfully replace ordinary glass fiber composites. The mechanical properties in tensile, three-point bending, and compression of epoxy-resin-impregnated basalt fiber composites are comparable and even exceed those of widely used epoxy-resin-impregnated fiberglass composites.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-06-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141365037","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-06-10DOI: 10.13111/2066-8201.2024.16.2.2
Mohamed H. Abougabal, Mohammad K. Gamal, Mohamed T. MOHAMED AMIEN, Shehab O. Mohamed, Ayman H. Kassem
This paper explores the development of a Quadcopter-Rover System specifically designed for environmental survey applications. The system combines the capabilities of a quadcopter and a rover to provide a comprehensive and versatile solution for data collection and analysis. The paper presents a detailed overview of the system's modelling, design, and manufacturing of the two main components: the quadcopter and the differential wheel robot (the rover). The quadcopter’s main task is to carry the rover to/from the ground destination and collect aerial data while the rover`s main task is ground exploration and data collection. The paper discusses the development of a robust and efficient control algorithm that enables autonomous and coordinated operation between the quadcopter and the rover. Experimental results demonstrate the system's effectiveness in conducting environmental surveys, showcasing its ability to accurately navigate challenging terrains, and collect valuable data for environmental analysis. The Quadcopter-Rover System offers significant potential in applications such as ecological monitoring, disaster management, and precision agriculture, where comprehensive and efficient data collection is crucial for informed decision-making.
{"title":"Quadcopter-Rover System for Environmental Survey Applications","authors":"Mohamed H. Abougabal, Mohammad K. Gamal, Mohamed T. MOHAMED AMIEN, Shehab O. Mohamed, Ayman H. Kassem","doi":"10.13111/2066-8201.2024.16.2.2","DOIUrl":"https://doi.org/10.13111/2066-8201.2024.16.2.2","url":null,"abstract":"This paper explores the development of a Quadcopter-Rover System specifically designed for environmental survey applications. The system combines the capabilities of a quadcopter and a rover to provide a comprehensive and versatile solution for data collection and analysis. The paper presents a detailed overview of the system's modelling, design, and manufacturing of the two main components: the quadcopter and the differential wheel robot (the rover). The quadcopter’s main task is to carry the rover to/from the ground destination and collect aerial data while the rover`s main task is ground exploration and data collection. The paper discusses the development of a robust and efficient control algorithm that enables autonomous and coordinated operation between the quadcopter and the rover. Experimental results demonstrate the system's effectiveness in conducting environmental surveys, showcasing its ability to accurately navigate challenging terrains, and collect valuable data for environmental analysis. The Quadcopter-Rover System offers significant potential in applications such as ecological monitoring, disaster management, and precision agriculture, where comprehensive and efficient data collection is crucial for informed decision-making.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-06-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141361125","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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