Hana Mohamed Almagzob, Tarik Hassan Elssoni, Abdulaziz AbdulMajid
The aim of this study is to perform structural design and analysis of a light aircraft wing. Both aerodynamic analysis and structural design of the wing are covered. The aerodynamic analysis is achieved by using Schrenks Approximation Method simulated in MATLAB to estimate the lift distribution. In addition, static stress analysis of the wing is carried out to compute the stresses at wing structure when subjected to the generated aerodynamic loads and thereby examine its structural reliability. The stresses are estimated by using the finite element software package MSC/NASTRAN/PATRAN. A maximum Von Mises stress of 135MPa is obtained which is less than the yield stress for aluminum alloy used in wing design. On the other hand, and based on the finite element model, a free-vibration analysis is performed for the whole model. The frequencies for the first three modes and the corresponding mode shapes are presented. The purpose of this study is to correlate and validate the finite element model against the modal test in preparation for further complex analysis. The finite element results have shown that the suggested wing configuration of the light aircraft is safe, with margins of safety equal to 1.33 which occurs at the root section.
{"title":"Structural Design and Analysis of a Light Aircraft Wing","authors":"Hana Mohamed Almagzob, Tarik Hassan Elssoni, Abdulaziz AbdulMajid","doi":"10.54388/jkues.v1i2.58","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.58","url":null,"abstract":"The aim of this study is to perform structural design and analysis of a light aircraft wing. Both aerodynamic analysis and structural design of the wing are covered. The aerodynamic analysis is achieved by using Schrenks Approximation Method simulated in MATLAB to estimate the lift distribution. In addition, static stress analysis of the wing is carried out to compute the stresses at wing structure when subjected to the generated aerodynamic loads and thereby examine its structural reliability. The stresses are estimated by using the finite element software package MSC/NASTRAN/PATRAN. A maximum Von Mises stress of 135MPa is obtained which is less than the yield stress for aluminum alloy used in wing design. On the other hand, and based on the finite element model, a free-vibration analysis is performed for the whole model. The frequencies for the first three modes and the corresponding mode shapes are presented. The purpose of this study is to correlate and validate the finite element model against the modal test in preparation for further complex analysis. The finite element results have shown that the suggested wing configuration of the light aircraft is safe, with margins of safety equal to 1.33 which occurs at the root section.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-12-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131307966","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}
In the present work, the PG-7 (40mm) anti-tank hollow charge has been developed to double (tandem) hollow charge warhead by using a simulation program. The interaction of the precursor warhead with the Explosive Reactive Armor ERA was studied and the delayed time between the precursor head and the main charge was found which about 50 µs is with 350 mm penetration depth. The effect of precursor charge on the main charge was also studied and this effect was isolated in the delay period, in addition to the effect of precursor warhead jetting on the rear warhead the optimum delay time was found. This study was carried out using the ANSYS AUTODYN simulation program. And the model worked in several ways to reach these goals.
{"title":"Analysis and Simulation of Tandem Charge","authors":"A. M. M. Zain, M. Abdelgadir, Nizar M. Ahmed","doi":"10.54388/jkues.v1i2.78","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.78","url":null,"abstract":"In the present work, the PG-7 (40mm) anti-tank hollow charge has been developed to double (tandem) hollow charge warhead by using a simulation program. The interaction of the precursor warhead with the Explosive Reactive Armor ERA was studied and the delayed time between the precursor head and the main charge was found which about 50 µs is with 350 mm penetration depth. The effect of precursor charge on the main charge was also studied and this effect was isolated in the delay period, in addition to the effect of precursor warhead jetting on the rear warhead the optimum delay time was found. This study was carried out using the ANSYS AUTODYN simulation program. And the model worked in several ways to reach these goals.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"108 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-12-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128162704","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}
This paper describes the design and fabrication of a device measuring mass properties include mass, the center of gravity, and moment of inertias properties by integrating three operations into one equipment device for the object GRAD rocket. This paper focuses only on measuring mass and center of gravity in a single setup. The design is divided into three steps. The first step is to explain how to measure the mass and center of gravity. The second step is the design and fabrication considerations of the equipment device. In the third step, the data acquisition systems for load cell using PLC. Test results of fabricated devices on a calibrated bar are homogeneity, and its center of gravity is also known. The mass and center of gravity of the GRAD rocket are a measure for three samples. And the results were within the required tolerance with high accuracy compared to CAD software, and the results achieved a percentage error rate of less than 5% for both the mass and center of gravity.
{"title":"Design and Optimization of Low speed wind tunnel Contraction Using CFD","authors":"Rami Abdalgadir Alneem, Eimad Eldin Elhadi Musa","doi":"10.54388/jkues.v1i2.71","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.71","url":null,"abstract":"This paper describes the design and fabrication of a device measuring mass properties include mass, the center of gravity, and moment of inertias properties by integrating three operations into one equipment device for the object GRAD rocket. This paper focuses only on measuring mass and center of gravity in a single setup. The design is divided into three steps. The first step is to explain how to measure the mass and center of gravity. The second step is the design and fabrication considerations of the equipment device. In the third step, the data acquisition systems for load cell using PLC. Test results of fabricated devices on a calibrated bar are homogeneity, and its center of gravity is also known. The mass and center of gravity of the GRAD rocket are a measure for three samples. And the results were within the required tolerance with high accuracy compared to CAD software, and the results achieved a percentage error rate of less than 5% for both the mass and center of gravity.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"2007 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-12-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116902004","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}
A. M. M. Zain, Mohammed A. Abdalla, M. F. M. Ahmed, Salaheldin A.M. Badreldin, Mouhamed Montaga
The air force is the most important weapon during wars and battles. Through it, armies can control and isolate enemy territory, carry out their own operations and missions, allow for the increased bombing, tactical air support for ground forces, parachuting, airdrops, and the passage of cargo planes. Countries are working to enhance their air force by increasing the number of their aircraft and providing them with the latest modern technologies in monitoring targets, accurate and efficient missiles. This paper will present a completely new design of 80 mm controlled fragmentation warhead for air to surface missile has been designed and tested, the results of the experiment showed a good performance for tactical characteristics such as lethal range which is about 19 meters.
{"title":"The Lethal Range Testing of Effective 80mm Air to Ground Warhead","authors":"A. M. M. Zain, Mohammed A. Abdalla, M. F. M. Ahmed, Salaheldin A.M. Badreldin, Mouhamed Montaga","doi":"10.54388/jkues.v1i2.84","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.84","url":null,"abstract":"The air force is the most important weapon during wars and battles. Through it, armies can control and isolate enemy territory, carry out their own operations and missions, allow for the increased bombing, tactical air support for ground forces, parachuting, airdrops, and the passage of cargo planes. Countries are working to enhance their air force by increasing the number of their aircraft and providing them with the latest modern technologies in monitoring targets, accurate and efficient missiles. This paper will present a completely new design of 80 mm controlled fragmentation warhead for air to surface missile has been designed and tested, the results of the experiment showed a good performance for tactical characteristics such as lethal range which is about 19 meters.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-12-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115402331","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}
In recent years, the use of Flying drones and modern Unmanned aerial vehicles (UAVs) with the latest techniques and capabilities for both civilian and military applications growing sustainably on a large scope, Drones could autonomously fly in several environments and locations and could perform various missions, providing a system for UAV detection and tracking represent crucial importance. This paper discusses Designing Detection and Tracking method as a part of Aero-vehicle Defense System (ADS) for UAVs using Deep learning algorithms. The small Radar cross-section (RCS) foot-print makes a problem for Traditional methods and Aero-vehicle Defense systems to distinguish between birds, stealth fighters, and UAVs incomparable of size and RCS characteristics, the detection is a challenge in low RCS targets because the chance of detection is incredibly less moreover, in the existence of interference and clutter which reduce the performance of detection process rapidly.
{"title":"Detection and Tracking of UAV Targets Using Deep Learning","authors":"Mohamed Khedir Noraldain Alamin","doi":"10.54388/jkues.v1i2.51","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.51","url":null,"abstract":"In recent years, the use of Flying drones and modern Unmanned aerial vehicles (UAVs) with the latest techniques and capabilities for both civilian and military applications growing sustainably on a large scope, Drones could autonomously fly in several environments and locations and could perform various missions, providing a system for UAV detection and tracking represent crucial importance. This paper discusses Designing Detection and Tracking method as a part of Aero-vehicle Defense System (ADS) for UAVs using Deep learning algorithms. The small Radar cross-section (RCS) foot-print makes a problem for Traditional methods and Aero-vehicle Defense systems to distinguish between birds, stealth fighters, and UAVs incomparable of size and RCS characteristics, the detection is a challenge in low RCS targets because the chance of detection is incredibly less moreover, in the existence of interference and clutter which reduce the performance of detection process rapidly. ","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-12-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115786144","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}
This paper represented a result of several visions of chemical phenomenon and several extractions and extrapolations of experimental works which included a relationship between energy related to a chemical process and the relevant time which is required to achieve this process, but it must be taken into account that those mentioned experimental works hadn’t aimed substantially to study and state this relationship neither implicitly nor explicitly, but the results of those works have been exploited for another field after being compared with the relevant thermodynamic calculations. The selected case study for this paper was the relation between the burning time of Hydroxyl terminated poly butadiene propellant ( HTPB) and the caloric value of this material. The results reflected some relationship between the burning time and the change of the system energy during the burning process.
{"title":"The Relation between Burning Time and Burning Energy of HTPB - Based Composite Propellant","authors":"Ameer Awad Ebrahim Osman","doi":"10.54388/jkues.v1i2.77","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.77","url":null,"abstract":"This paper represented a result of several visions of chemical phenomenon and several extractions and extrapolations of experimental works which included a relationship between energy related to a chemical process and the relevant time which is required to achieve this process, but it must be taken into account that those mentioned experimental works hadn’t aimed substantially to study and state this relationship neither implicitly nor explicitly, but the results of those works have been exploited for another field after being compared with the relevant thermodynamic calculations. The selected case study for this paper was the relation between the burning time of Hydroxyl terminated poly butadiene propellant ( HTPB) and the caloric value of this material. The results reflected some relationship between the burning time and the change of the system energy during the burning process.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"146 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-12-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126917617","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}
Mohammed Balla Abdelwahid, H. M. Taha, Amar Mustafa Suliman, Hozaifa Mohammed Nazir, A. Ali
The design of high-performance combustion chambers for gas turbine engines is considered one of the difficult tasks for engineers. This study presents the design of a can-type combustion chamber. The parametric cycle analysis of a low bypass turbofan engine (AL-31F) was provided to obtain the air properties at the combustor inlet. Empirical equations are used to determine the dimensions of the combustion chamber. GAMBIT software was used to create the combustor model and the simulation was accomplished using ANSYS software. This CFD code is a steady, quasi-three-dimensional Reynolds Averaged Navier-Stokes (RANS) solver. K-w viscous model and non-premixed combustion model are used. Presented the results of cycle analysis of the turbofan engine and the dimensions of combustor components and cooling holes. An analysis of the distribution of temperature, pressure, and velocity throughout the combustion chamber is provided. The obtained results were compared for analytical and computational approaches and suggested with previous studies.
{"title":"Design and Simulation of a CAN Type Combustion Chamber","authors":"Mohammed Balla Abdelwahid, H. M. Taha, Amar Mustafa Suliman, Hozaifa Mohammed Nazir, A. Ali","doi":"10.54388/jkues.v1i2.95","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.95","url":null,"abstract":"The design of high-performance combustion chambers for gas turbine engines is considered one of the difficult tasks for engineers. This study presents the design of a can-type combustion chamber. The parametric cycle analysis of a low bypass turbofan engine (AL-31F) was provided to obtain the air properties at the combustor inlet. Empirical equations are used to determine the dimensions of the combustion chamber. GAMBIT software was used to create the combustor model and the simulation was accomplished using ANSYS software. This CFD code is a steady, quasi-three-dimensional Reynolds Averaged Navier-Stokes (RANS) solver. K-w viscous model and non-premixed combustion model are used. Presented the results of cycle analysis of the turbofan engine and the dimensions of combustor components and cooling holes. An analysis of the distribution of temperature, pressure, and velocity throughout the combustion chamber is provided. The obtained results were compared for analytical and computational approaches and suggested with previous studies.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-12-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124162832","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}
Structural optimization is one of the most important tasks during the airplane structural design and yet there is a lack of well established procedures to determine the optimum design of aerospace structures. This paper represents development of structural optimization code based on genetic algorithm, and results for light aircraft aft fuselage optimal design using the optimization code. We have developed a MATLAB code according to the genetic algorithm and FE model for the composite light aircraft aft fuselage using MSC PATRAN to generate NASTRAN input file; the MATLAB code was coupled with MSC NASTRAN which used to perform linear static and buckling analysis. we obtained the minimum weight of the aft fuselage with a linear static and buckling constraints; the minimum weight is 21.6 kg; it has been obtained after 43 iterations; the margin of safety is of the optimum design is 1.22 and the buckling factor is 1.24 and hence the structure is free of static failure and buckling. The code is efficient in the conceptual and preliminary structural design phases to obtain the optimal aft fuselage weight.
{"title":"Rear Fuselage Structural Optimization Using Genetic Algorithm","authors":"Mutwakil Elmshaikhi, Abdalmaged Abdallah","doi":"10.54388/jkues.v1i2.61","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.61","url":null,"abstract":"Structural optimization is one of the most important tasks during the airplane structural design and yet there is a lack of well established procedures to determine the optimum design of aerospace structures. This paper represents development of structural optimization code based on genetic algorithm, and results for light aircraft aft fuselage optimal design using the optimization code. We have developed a MATLAB code according to the genetic algorithm and FE model for the composite light aircraft aft fuselage using MSC PATRAN to generate NASTRAN input file; the MATLAB code was coupled with MSC NASTRAN which used to perform linear static and buckling analysis. we obtained the minimum weight of the aft fuselage with a linear static and buckling constraints; the minimum weight is 21.6 kg; it has been obtained after 43 iterations; the margin of safety is of the optimum design is 1.22 and the buckling factor is 1.24 and hence the structure is free of static failure and buckling. The code is efficient in the conceptual and preliminary structural design phases to obtain the optimal aft fuselage weight.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"56 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-12-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124167037","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}
Flight simulator is a virtual reality system capable of simulating an environment of a flying machine for a pilot. This work presented a simulation and implementation example of a six degree of freedom moving platform as a part of a flight simulator, most flight simulators adopted the Stewart platform as a moving platform. Therefore, a mathematical model of the Stewart platform is derived by solving inverse kinematics problem, to find the length of all legs for a given desired position and orientation. The mathematical model is verified and simulated using MATLAB software. Low-cost commercially available components are provided for the constructed prototype. Additionally, interfacing between hardware and software components is accomplished by Arduino Uno. Obtained results showed that the range of translational motion is and cm along x, y, and z respectively, as well as, the rotational range is +_5,+-3 and +-10 about the mentioned three axes.
{"title":"Simulation and Implementation of Moving Platform for Flight Simulator","authors":"E. T. Yousif, AbdElbagi Omer Eldany","doi":"10.54388/jkues.v2i1.48","DOIUrl":"https://doi.org/10.54388/jkues.v2i1.48","url":null,"abstract":"Flight simulator is a virtual reality system capable of simulating an environment of a flying machine for a pilot. This work presented a simulation and implementation example of a six degree of freedom moving platform as a part of a flight simulator, most flight simulators adopted the Stewart platform as a moving platform. Therefore, a mathematical model of the Stewart platform is derived by solving inverse kinematics problem, to find the length of all legs for a given desired position and orientation. The mathematical model is verified and simulated using MATLAB software. Low-cost commercially available components are provided for the constructed prototype. Additionally, interfacing between hardware and software components is accomplished by Arduino Uno. Obtained results showed that the range of translational motion is and cm along x, y, and z respectively, as well as, the rotational range is +_5,+-3 and +-10 about the mentioned three axes.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"82 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-12-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132730707","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}
This paper proposes a design of high directivity directional coupler (D.C) based on grounding composed of strip lines for high power Radar transmitter at Very High Frequency (VHF), (150 – 200 MHz). The directional coupler is used to check and verify the transmitter output high power, frequency, and reflected signal from an antenna connected with the Radar transmitter. The performance requirements of directional couplers are a strong coupling to reduce the effect on the transmitted output power and high directivity to suppress the interference of the reflected signal from the antenna. So far, various architectures have been proposed to gain high directivity, and there have been many studies used to obtain a strong coupling and higher directivity. However, the conventional architecture of the directional coupler has a directivity of only about 20 dB, and there have been difficulties to achieve the higher directivity of more than 20 dB. In this paper, the proposed architecture of directional coupler based on grounding composed of strip lines is discussed and compares the test results of the proposed directional coupler with the conventional one. The high directivity directional coupler is designed using a computer-aided design Simulation program; Advance Design System (ADS 2016), using Rogers 4003 substrate. The directional coupler was fabricated on printed circuit board (PCB) technology and measured using a vector network analyzer (VNA). The results show that the proposed directional coupler has directivity between -25 to -24 dB inside the working bandwidth and is adequate for a high-power radar transmitter.
{"title":"Design and Implementation of High Directivity Directional Coupler at VHF Band Using Grounding Composed of Strip Lines Technics","authors":"Atef Merghani Abdallah Abdalmagd","doi":"10.54388/jkues.v1i2.38","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.38","url":null,"abstract":"This paper proposes a design of high directivity directional coupler (D.C) based on grounding composed of strip lines for high power Radar transmitter at Very High Frequency (VHF), (150 – 200 MHz). The directional coupler is used to check and verify the transmitter output high power, frequency, and reflected signal from an antenna connected with the Radar transmitter. The performance requirements of directional couplers are a strong coupling to reduce the effect on the transmitted output power and high directivity to suppress the interference of the reflected signal from the antenna. So far, various architectures have been proposed to gain high directivity, and there have been many studies used to obtain a strong coupling and higher directivity. However, the conventional architecture of the directional coupler has a directivity of only about 20 dB, and there have been difficulties to achieve the higher directivity of more than 20 dB. In this paper, the proposed architecture of directional coupler based on grounding composed of strip lines is discussed and compares the test results of the proposed directional coupler with the conventional one. The high directivity directional coupler is designed using a computer-aided design Simulation program; Advance Design System (ADS 2016), using Rogers 4003 substrate. The directional coupler was fabricated on printed circuit board (PCB) technology and measured using a vector network analyzer (VNA). The results show that the proposed directional coupler has directivity between -25 to -24 dB inside the working bandwidth and is adequate for a high-power radar transmitter.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"104 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-12-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132564109","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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