Tarik Elsonni - Academia.edu (original) (raw)
Papers by Tarik Elsonni
International Conference on Aerospace Sciences & Aviation Technology, May 1, 2011
The wing of an UAV plays an important role in the vehicle behavior. In order to understand its ma... more The wing of an UAV plays an important role in the vehicle behavior. In order to understand its main influences, a dedicated test rig was designed and realized to load the composite wing in the bending configuration. This study describes the details of a numerical and an experimental investigation done with the aim to identify the stiffness characteristics of a composite wing structure of an Unmanned Aerial Vehicle (UAV). The wing was divided into discrete span-wise stations. Wooden bolted clamps were placed along the upper and lower surfaces of the wing at each station, to support the applied load and the displacement transducers. The wing was suspended and secured horizontally (at the wingfuselage connection base) in a rigid test stand in an orientation similar to the familiar cantilever beam. A single weight was applied individually, at each station to stress the wing in elastic yield, as in real conditions. Displacement transducers were installed to measure the vertical displacements of the entire wing, and monitor any motion of the overall airframe. During the measurement procedures (loading and unloading) were conducted on the specified stations, and repeated 10 times, the mean value of the measurements was obtained. A detailed numerical model of the composite wing was developed using of the finite element method in order to reproduce the experimental experiences. Numerical and experimental results were compared to validate the model of the composite wing. All the obtained parameters are mainly being used in a development process of UAV behavior.
International Conference on Aerospace Sciences & Aviation Technology, May 1, 2013
This paper describes the design cycle process as well as the manufacturing technique of a single ... more This paper describes the design cycle process as well as the manufacturing technique of a single engine Primary Trainer Airplane (PTA) designed in the Department of Aeronautical Engineering-Karary University. The PTA was specified to follow given specifications set by the customer and designed successfully to correspond to the specified mission profile. Statistical data was collected and the information used to calculate the weight fuel fraction and subsequently the preliminary weights for the airplane. The conceptual design of the airplane took into consideration the major attributes required of a PTA as well as the aesthetic desires of the designers. All modules of the airplane such as the aerodynamics, stability and performance, were intended to be taken into account. The fuselage was sized to incorporate a high wing, as well as to fit the tail and landing gears. The wings were sized using statistical data to suit the overall layout of the airplane. Likewise, the conventional tail was selected for the low level of weight which it added to the design. To conclude the conceptual design phase, a tricycle landing gear was selected with a fixed mechanism incorporated. The landing gear was designed to be mounted on the wings. Weight and balance analysis were also undertaken to ensure an airplane which is stable and relatively well balanced in flight. In order to demonstrate its performance and stability, a scale model of the PTA was fabricated and has successful flights in April 2012.
INCAS BULLETIN, 2021
In this study the procedures of structural analysis of a typical transport aircraft wing has been... more In this study the procedures of structural analysis of a typical transport aircraft wing has been followed. The wing model has been drawn using CATIA® V5; this model consists of several structural components such as spars, ribs and skin. The model has been exported into structural analysis software ANSYS® 2016. Stresses, strains, deformations and safety factors were obtained for the model. It is found that the obtained stresses caused by the aerodynamic loads on the wing are within the design structural limits where the failure by yield or buckling has not been occurred
International Conference on Aerospace Sciences and Aviation Technology, 2011
The wing of an UAV plays an important role in the vehicle behavior. In order to understand its ma... more The wing of an UAV plays an important role in the vehicle behavior. In order to understand its main influences, a dedicated test rig was designed and realized to load the composite wing in the bending configuration. This study describes the details of a numerical and an experimental investigation done with the aim to identify the stiffness characteristics of a composite wing structure of an Unmanned Aerial Vehicle (UAV). The wing was divided into discrete span-wise stations. Wooden bolted clamps were placed along the upper and lower surfaces of the wing at each station, to support the applied load and the displacement transducers. The wing was suspended and secured horizontally (at the wingfuselage connection base) in a rigid test stand in an orientation similar to the familiar cantilever beam. A single weight was applied individually, at each station to stress the wing in elastic yield, as in real conditions. Displacement transducers were installed to measure the vertical displacements of the entire wing, and monitor any motion of the overall airframe. During the measurement procedures (loading and unloading) were conducted on the specified stations, and repeated 10 times, the mean value of the measurements was obtained. A detailed numerical model of the composite wing was developed using of the finite element method in order to reproduce the experimental experiences. Numerical and experimental results were compared to validate the model of the composite wing. All the obtained parameters are mainly being used in a development process of UAV behavior.
International Conference on Aerospace Sciences and Aviation Technology, 2013
This paper describes the design cycle process as well as the manufacturing technique of a single ... more This paper describes the design cycle process as well as the manufacturing technique of a single engine Primary Trainer Airplane (PTA) designed in the Department of Aeronautical Engineering-Karary University. The PTA was specified to follow given specifications set by the customer and designed successfully to correspond to the specified mission profile. Statistical data was collected and the information used to calculate the weight fuel fraction and subsequently the preliminary weights for the airplane. The conceptual design of the airplane took into consideration the major attributes required of a PTA as well as the aesthetic desires of the designers. All modules of the airplane such as the aerodynamics, stability and performance, were intended to be taken into account. The fuselage was sized to incorporate a high wing, as well as to fit the tail and landing gears. The wings were sized using statistical data to suit the overall layout of the airplane. Likewise, the conventional tail was selected for the low level of weight which it added to the design. To conclude the conceptual design phase, a tricycle landing gear was selected with a fixed mechanism incorporated. The landing gear was designed to be mounted on the wings. Weight and balance analysis were also undertaken to ensure an airplane which is stable and relatively well balanced in flight. In order to demonstrate its performance and stability, a scale model of the PTA was fabricated and has successful flights in April 2012.
International Conference on Aerospace Sciences and Aviation Technology, 2013
The aim of this paper is to determine and study the aerodynamics characteristics of an Agricultur... more The aim of this paper is to determine and study the aerodynamics characteristics of an Agricultural Spraying Unmanned Air Vehicle (ASUAV) that designed in the Faculty of Engineering-Omdurman Islamic University. Since flight testing can be expensive and dangerous, other methods are required to simulate flight test conditions for low subsonic vehicle system. In this research, Computational Fluids Dynamics (CFD) was used to simulate the flight test and determine the aerodynamic characteristics such as lift and drag coefficients at various angles of attack. The quality of flow pattern around the ASUAV was clearly observed. Generally, the current approach shows that the proposed configuration has suitable aerodynamic characteristics. The promising results of this study opened the door for developing and manufacturing the ASUAV which have been successfully flight in June 2012.
Electronics
Drones are increasingly vital in numerous fields, such as commerce, delivery services, and milita... more Drones are increasingly vital in numerous fields, such as commerce, delivery services, and military operations. Therefore, it is essential to develop advanced systems for detecting and recognizing drones to ensure the safety and security of airspace. This paper aimed to develop a robust solution for detecting and recognizing drones and birds in airspace by combining a radar system and a visual imaging system, and contributed to this effort by demonstrating the potential of combining the two systems for drone detection and recognition. The results showed that this approach was highly effective, with a high overall precision and accuracy of 88.82% and 71.43%, respectively, and the high F1 score of 76.27% indicates that the proposed combination approach has great effectiveness in the performance. The outcome of this study has significant practical implications for developing more advanced and effective drone and bird detection systems. The proposed algorithm is benchmarked with other r...
International Conference on Aerospace Sciences & Aviation Technology, May 1, 2011
The wing of an UAV plays an important role in the vehicle behavior. In order to understand its ma... more The wing of an UAV plays an important role in the vehicle behavior. In order to understand its main influences, a dedicated test rig was designed and realized to load the composite wing in the bending configuration. This study describes the details of a numerical and an experimental investigation done with the aim to identify the stiffness characteristics of a composite wing structure of an Unmanned Aerial Vehicle (UAV). The wing was divided into discrete span-wise stations. Wooden bolted clamps were placed along the upper and lower surfaces of the wing at each station, to support the applied load and the displacement transducers. The wing was suspended and secured horizontally (at the wingfuselage connection base) in a rigid test stand in an orientation similar to the familiar cantilever beam. A single weight was applied individually, at each station to stress the wing in elastic yield, as in real conditions. Displacement transducers were installed to measure the vertical displacements of the entire wing, and monitor any motion of the overall airframe. During the measurement procedures (loading and unloading) were conducted on the specified stations, and repeated 10 times, the mean value of the measurements was obtained. A detailed numerical model of the composite wing was developed using of the finite element method in order to reproduce the experimental experiences. Numerical and experimental results were compared to validate the model of the composite wing. All the obtained parameters are mainly being used in a development process of UAV behavior.
International Conference on Aerospace Sciences & Aviation Technology, May 1, 2013
This paper describes the design cycle process as well as the manufacturing technique of a single ... more This paper describes the design cycle process as well as the manufacturing technique of a single engine Primary Trainer Airplane (PTA) designed in the Department of Aeronautical Engineering-Karary University. The PTA was specified to follow given specifications set by the customer and designed successfully to correspond to the specified mission profile. Statistical data was collected and the information used to calculate the weight fuel fraction and subsequently the preliminary weights for the airplane. The conceptual design of the airplane took into consideration the major attributes required of a PTA as well as the aesthetic desires of the designers. All modules of the airplane such as the aerodynamics, stability and performance, were intended to be taken into account. The fuselage was sized to incorporate a high wing, as well as to fit the tail and landing gears. The wings were sized using statistical data to suit the overall layout of the airplane. Likewise, the conventional tail was selected for the low level of weight which it added to the design. To conclude the conceptual design phase, a tricycle landing gear was selected with a fixed mechanism incorporated. The landing gear was designed to be mounted on the wings. Weight and balance analysis were also undertaken to ensure an airplane which is stable and relatively well balanced in flight. In order to demonstrate its performance and stability, a scale model of the PTA was fabricated and has successful flights in April 2012.
INCAS BULLETIN, 2021
In this study the procedures of structural analysis of a typical transport aircraft wing has been... more In this study the procedures of structural analysis of a typical transport aircraft wing has been followed. The wing model has been drawn using CATIA® V5; this model consists of several structural components such as spars, ribs and skin. The model has been exported into structural analysis software ANSYS® 2016. Stresses, strains, deformations and safety factors were obtained for the model. It is found that the obtained stresses caused by the aerodynamic loads on the wing are within the design structural limits where the failure by yield or buckling has not been occurred
International Conference on Aerospace Sciences and Aviation Technology, 2011
The wing of an UAV plays an important role in the vehicle behavior. In order to understand its ma... more The wing of an UAV plays an important role in the vehicle behavior. In order to understand its main influences, a dedicated test rig was designed and realized to load the composite wing in the bending configuration. This study describes the details of a numerical and an experimental investigation done with the aim to identify the stiffness characteristics of a composite wing structure of an Unmanned Aerial Vehicle (UAV). The wing was divided into discrete span-wise stations. Wooden bolted clamps were placed along the upper and lower surfaces of the wing at each station, to support the applied load and the displacement transducers. The wing was suspended and secured horizontally (at the wingfuselage connection base) in a rigid test stand in an orientation similar to the familiar cantilever beam. A single weight was applied individually, at each station to stress the wing in elastic yield, as in real conditions. Displacement transducers were installed to measure the vertical displacements of the entire wing, and monitor any motion of the overall airframe. During the measurement procedures (loading and unloading) were conducted on the specified stations, and repeated 10 times, the mean value of the measurements was obtained. A detailed numerical model of the composite wing was developed using of the finite element method in order to reproduce the experimental experiences. Numerical and experimental results were compared to validate the model of the composite wing. All the obtained parameters are mainly being used in a development process of UAV behavior.
International Conference on Aerospace Sciences and Aviation Technology, 2013
This paper describes the design cycle process as well as the manufacturing technique of a single ... more This paper describes the design cycle process as well as the manufacturing technique of a single engine Primary Trainer Airplane (PTA) designed in the Department of Aeronautical Engineering-Karary University. The PTA was specified to follow given specifications set by the customer and designed successfully to correspond to the specified mission profile. Statistical data was collected and the information used to calculate the weight fuel fraction and subsequently the preliminary weights for the airplane. The conceptual design of the airplane took into consideration the major attributes required of a PTA as well as the aesthetic desires of the designers. All modules of the airplane such as the aerodynamics, stability and performance, were intended to be taken into account. The fuselage was sized to incorporate a high wing, as well as to fit the tail and landing gears. The wings were sized using statistical data to suit the overall layout of the airplane. Likewise, the conventional tail was selected for the low level of weight which it added to the design. To conclude the conceptual design phase, a tricycle landing gear was selected with a fixed mechanism incorporated. The landing gear was designed to be mounted on the wings. Weight and balance analysis were also undertaken to ensure an airplane which is stable and relatively well balanced in flight. In order to demonstrate its performance and stability, a scale model of the PTA was fabricated and has successful flights in April 2012.
International Conference on Aerospace Sciences and Aviation Technology, 2013
The aim of this paper is to determine and study the aerodynamics characteristics of an Agricultur... more The aim of this paper is to determine and study the aerodynamics characteristics of an Agricultural Spraying Unmanned Air Vehicle (ASUAV) that designed in the Faculty of Engineering-Omdurman Islamic University. Since flight testing can be expensive and dangerous, other methods are required to simulate flight test conditions for low subsonic vehicle system. In this research, Computational Fluids Dynamics (CFD) was used to simulate the flight test and determine the aerodynamic characteristics such as lift and drag coefficients at various angles of attack. The quality of flow pattern around the ASUAV was clearly observed. Generally, the current approach shows that the proposed configuration has suitable aerodynamic characteristics. The promising results of this study opened the door for developing and manufacturing the ASUAV which have been successfully flight in June 2012.
Electronics
Drones are increasingly vital in numerous fields, such as commerce, delivery services, and milita... more Drones are increasingly vital in numerous fields, such as commerce, delivery services, and military operations. Therefore, it is essential to develop advanced systems for detecting and recognizing drones to ensure the safety and security of airspace. This paper aimed to develop a robust solution for detecting and recognizing drones and birds in airspace by combining a radar system and a visual imaging system, and contributed to this effort by demonstrating the potential of combining the two systems for drone detection and recognition. The results showed that this approach was highly effective, with a high overall precision and accuracy of 88.82% and 71.43%, respectively, and the high F1 score of 76.27% indicates that the proposed combination approach has great effectiveness in the performance. The outcome of this study has significant practical implications for developing more advanced and effective drone and bird detection systems. The proposed algorithm is benchmarked with other r...