Hamed Mohamed Ahmed Ali, Abdallah Almadani MuhammadAlhassan, Abdelrazig Abdelfadail Abdelrazig, Alla aldeen Ismail Massar, M. Haroun
This paper presents a design of centrifugal compressor and air intake for micro turbojet engine of 200 N thrust. Because of the small size of the micro turbine engines the air intake is designed in the form of bellmouth air intake in order to capture the needed amount of mass flow rate (0.45 kg/s). The function of the air intake is to deliver the air to the entry of the centrifugal compressor. The air intake has been drawn with start-up motor to take in the consideration the effect. The centrifugal compressor was designed to deliver 3.8 pressure ratio with efficiency about 77%. The compressor impeller was built with 7 main blades and 7 splitters in order to reduce the effect of slip at the exit of the impeller due to pressure difference between pressure and suction side of the main blade. Diffuser of 13 vanes also was designed to increase the static pressure, direct the flow to the combustion chamber and decrease the flow velocity before to enhance the combustion process. The structural integrity for impeller was validated using ANSYS software for aluminum alloy 7075-T6; 7075651. In addition, the aerodynamic analysis was investigated using NUMECA software. The most important findings of the extensive analysis were; the impact of air intake on compressor performance is very crucial. It add an increment in efficiency and pressure ratio, it should be taken in consideration in early design stage of the compressor. The highest performance characteristics of compressor were achieved by accurate design optimization of impeller-diffuser interaction.
{"title":"Centrifugal Compressor and Bell mouth Air Intake Preliminary Design for Micro Turbojet Engine","authors":"Hamed Mohamed Ahmed Ali, Abdallah Almadani MuhammadAlhassan, Abdelrazig Abdelfadail Abdelrazig, Alla aldeen Ismail Massar, M. Haroun","doi":"10.54388/jkues.v1i2.45","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.45","url":null,"abstract":"This paper presents a design of centrifugal compressor and air intake for micro turbojet engine of 200 N thrust. Because of the small size of the micro turbine engines the air intake is designed in the form of bellmouth air intake in order to capture the needed amount of mass flow rate (0.45 kg/s). The function of the air intake is to deliver the air to the entry of the centrifugal compressor. The air intake has been drawn with start-up motor to take in the consideration the effect. The centrifugal compressor was designed to deliver 3.8 pressure ratio with efficiency about 77%. The compressor impeller was built with 7 main blades and 7 splitters in order to reduce the effect of slip at the exit of the impeller due to pressure difference between pressure and suction side of the main blade. Diffuser of 13 vanes also was designed to increase the static pressure, direct the flow to the combustion chamber and decrease the flow velocity before to enhance the combustion process. The structural integrity for impeller was validated using ANSYS software for aluminum alloy 7075-T6; 7075651. In addition, the aerodynamic analysis was investigated using NUMECA software. The most important findings of the extensive analysis were; the impact of air intake on compressor performance is very crucial. It add an increment in efficiency and pressure ratio, it should be taken in consideration in early design stage of the compressor. The highest performance characteristics of compressor were achieved by accurate design optimization of impeller-diffuser interaction.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"53 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":"133894789","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 dividing 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 fabrication device for determine Mass and Center of gravity of GRAD rocket","authors":"Rami Abdalgadir Alneem, Mohamed Ali Omer","doi":"10.54388/jkues.v1i2.91","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.91","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 dividing 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":"105 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":"123976764","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}
Asaad musaab Ali yousif Asaad, Mohammed Alamein Taha Babker Ibrahim, Mahmoud Osman Suliman Omer, Marwa Mahmoud AbdAllatif Mohamed
This paper discussed the design and implementation of a Computer Numerical Control (CNC) machine for writing or sketch by employ parts of computer scraps (DVD-ROM). The Arduino Uno used as the controller for this project with using Inkscape program, which converts images and text into g- code format and then sends this g- code to the processing3 program which is an interface the connection between the arduino and the computer and the language of the CNC machine. The g-code includes a set of x y z coordinates that are sent to the motors, the Z coordinates are transmitted to the servo motor that directs the movement of the pen, the Y coordinates are sent to the stepper motor 1 that directs the horizontal movement of the DVD rail and the X coordinate is send to the Stepper motor 2 that directs the vertical movement of the DVD rail. This project can be used in logo Design. CNC machines can be utilized ceaselessly 24 hours every day, 365 days per year and just should be turned off for intermittent support.
本文讨论了一种利用计算机废料(DVD-ROM)零件进行书写或绘图的计算机数控(CNC)机床的设计与实现。本项目采用Arduino Uno作为控制器，使用Inkscape程序，将图像和文本转换成g- code格式，然后将g- code发送给processing程序，processing程序是Arduino与计算机连接的接口，是CNC机床的语言。g代码包括一组发送给电机的x y z坐标，z坐标发送给指导笔运动的伺服电机，y坐标发送给指导DVD导轨水平运动的步进电机1,x坐标发送给指导DVD导轨垂直运动的步进电机2。这个项目可以在标志设计中使用。数控机床可以每天24小时不间断地使用，一年365天，只需要关闭间歇性支持。
{"title":"Design and Implementation of CNC Writing Machine Based on Arduino Micro-controller","authors":"Asaad musaab Ali yousif Asaad, Mohammed Alamein Taha Babker Ibrahim, Mahmoud Osman Suliman Omer, Marwa Mahmoud AbdAllatif Mohamed","doi":"10.54388/jkues.v1i2.53","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.53","url":null,"abstract":"This paper discussed the design and implementation of a Computer Numerical Control (CNC) machine for writing or sketch by employ parts of computer scraps (DVD-ROM). The Arduino Uno used as the controller for this project with using Inkscape program, which converts images and text into g- code format and then sends this g- code to the processing3 program which is an interface the connection between the arduino and the computer and the language of the CNC machine. The g-code includes a set of x y z coordinates that are sent to the motors, the Z coordinates are transmitted to the servo motor that directs the movement of the pen, the Y coordinates are sent to the stepper motor 1 that directs the horizontal movement of the DVD rail and the X coordinate is send to the Stepper motor 2 that directs the vertical movement of the DVD rail. This project can be used in logo Design. CNC machines can be utilized ceaselessly 24 hours every day, 365 days per year and just should be turned off for intermittent support.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"18 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":"116748738","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}
Adil Elrayah, Ausabah I.A. Ahmed, Abdlrasool Jabbar
Designing of mining exclusive electronic circuit, safety for work environment is vital and important. The system devices contained transmitter block, which are containing computer monitoring software and internet modem. The other one is receiver block which is included explosive circuit and their components (i.e., a digital component mobile phone, ICs, and detector). To control the operation steps process used software program written with C++ language. The system was successfully built and designed. Besides that, it could capabilities of components set in the designed circuit. Moreover, the circuit and their components were operated carefully according to program sequence. The results are achieved the general objectives of the research. Also, it was match standards, specified in national standards for performances and appearances of such devices.
{"title":"Design of Electronic Circuit for Mining Explosive Detonator","authors":"Adil Elrayah, Ausabah I.A. Ahmed, Abdlrasool Jabbar","doi":"10.54388/jkues.v1i2.85","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.85","url":null,"abstract":"Designing of mining exclusive electronic circuit, safety for work environment is vital and important. The system devices contained transmitter block, which are containing computer monitoring software and internet modem. The other one is receiver block which is included explosive circuit and their components (i.e., a digital component mobile phone, ICs, and detector). To control the operation steps process used software program written with C++ language. The system was successfully built and designed. Besides that, it could capabilities of components set in the designed circuit. Moreover, the circuit and their components were operated carefully according to program sequence. The results are achieved the general objectives of the research. Also, it was match standards, specified in national standards for performances and appearances of such devices.","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":"127253295","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}
Composite propellants are energetic materials have ability to ignite, burn fast and cause several simultaneous exothermic chemical reactions which produce huge amounts of gases under high pressures and temperatures which can spread spontaneously. 1n the present study, the explosive material hexogen (Cyclo tri-methylene tri-nitramine) was used to improve the performance properties of composite propellants, especially the specific impulse. For several formulations of hexogen at different added percentages, the specific impulse was calculated using thermodynamic calculations program of composite propellants. The results given were compared with those formulations not including hexogen. It was seen that; hexogen caused a significant positive effect in the specific impulse. Accordingly, the energy of composite propellant was improved positively in the samples containing hexogen till 40% of the oxidizer ratio. Also, it was noticed that the specific impulse began to decrease gradually for the oxidizers containing more than 40% of hexogen which caused in a decreasing of composite propellant energy. Finally, it was concluded that, the use of some amount of explosive materials like hexogen can improve composite propellants energy successfully.
{"title":"Improvement of Composite Propellants Energy Using Explosive Materials","authors":"Amjad O. Saeed, Nagmeldin M. Elamin","doi":"10.54388/jkues.v1i2.88","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.88","url":null,"abstract":"Composite propellants are energetic materials have ability to ignite, burn fast and cause several simultaneous exothermic chemical reactions which produce huge amounts of gases under high pressures and temperatures which can spread spontaneously. 1n the present study, the explosive material hexogen (Cyclo tri-methylene tri-nitramine) was used to improve the performance properties of composite propellants, especially the specific impulse. For several formulations of hexogen at different added percentages, the specific impulse was calculated using thermodynamic calculations program of composite propellants. The results given were compared with those formulations not including hexogen. It was seen that; hexogen caused a significant positive effect in the specific impulse. Accordingly, the energy of composite propellant was improved positively in the samples containing hexogen till 40% of the oxidizer ratio. Also, it was noticed that the specific impulse began to decrease gradually for the oxidizers containing more than 40% of hexogen which caused in a decreasing of composite propellant energy. Finally, it was concluded that, the use of some amount of explosive materials like hexogen can improve composite propellants energy successfully.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"396 ","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-12-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133817641","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 some communication systems, it is desirable for the receiver to synchronize to the received signal and to adjust the equalizer without having knowledge of a training sequence. Blind equalization uses the initial adjustment of the coefficients without making use of a training sequence. Different adaptive blind equalization algorithms have been developed over the past four decades. In this paper, we investigate the effect of blind equalization on space communication channels. The space channel under investigation is considered to be a multipath frequency selective channel having four paths. The channel is subjected to the phenomenon of InterSymbol Interference (ISI) which severely degrades the performance of the space communication system. Two blind algorithms are used in equalizer adjustment. The impulse responses of the space channel, the blind equalizer and the combination of channel and equalizer for QPSK and 16-QAM transmission are shown. The scatter diagrams for the transmitted sequence, received sequence, and the output of the equalizer using two of the blind algorithms are shown.
{"title":"Blind Adaptive Equalization for Aerospace Communication Channels","authors":"Elessaid S. Saad","doi":"10.54388/jkues.v1i2.137","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.137","url":null,"abstract":"In some communication systems, it is desirable for the receiver to synchronize to the received signal and to adjust the equalizer without having knowledge of a training sequence. Blind equalization uses the initial adjustment of the coefficients without making use of a training sequence. Different adaptive blind equalization algorithms have been developed over the past four decades. In this paper, we investigate the effect of blind equalization on space communication channels. The space channel under investigation is considered to be a multipath frequency selective channel having four paths. The channel is subjected to the phenomenon of InterSymbol Interference (ISI) which severely degrades the performance of the space communication system. Two blind algorithms are used in equalizer adjustment. The impulse responses of the space channel, the blind equalizer and the combination of channel and equalizer for QPSK and 16-QAM transmission are shown. The scatter diagrams for the transmitted sequence, received sequence, and the output of the equalizer using two of the blind algorithms are shown.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"48 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":"132800575","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}
Abdelnasir Mohammed, Abdelateef Altaher Abdelateef Mohammed
This paper is devoted to show the effect of changing the design of the first punch on the wear consumption of the second punch by redesigning, simulating and manufacturing of the first punch for 107 mm warhead in order to reduce the consumption in the second punch, increase the productivity and also produce the product with high quality. SOLIDWORKS software for design and simufact forming for analysis has been used to design and manufacturing the first punch. Simufact forming has been used to study the die wear to determine the consumption rate of the second punch. The effective stress that affect the properties of the final product has been calculated by simufact. A comparison between the second punch which has been used after using the designed first punch and after using the old first punch shows that the wear in the second punch after using the new design is less than the wear in the second punch after using the old one, which means the life time of the second punch after using the new designed first punch will be longer than using it after using the old first punch. The various machining processes which is required for producing the punch are done, beside heat treatments. Final results of this work show that it is possible to improve the dies and use it in the optimal way also it prove the possibility of manufacturing dies locally instead of importing it from outside Sudan.
{"title":"Redesigning and Manufacturing the First Punch for 107 mm Warhead","authors":"Abdelnasir Mohammed, Abdelateef Altaher Abdelateef Mohammed","doi":"10.54388/jkues.v1i2.109","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.109","url":null,"abstract":"This paper is devoted to show the effect of changing the design of the first punch on the wear consumption of the second punch by redesigning, simulating and manufacturing of the first punch for 107 mm warhead in order to reduce the consumption in the second punch, increase the productivity and also produce the product with high quality. SOLIDWORKS software for design and simufact forming for analysis has been used to design and manufacturing the first punch. Simufact forming has been used to study the die wear to determine the consumption rate of the second punch. The effective stress that affect the properties of the final product has been calculated by simufact. A comparison between the second punch which has been used after using the designed first punch and after using the old first punch shows that the wear in the second punch after using the new design is less than the wear in the second punch after using the old one, which means the life time of the second punch after using the new designed first punch will be longer than using it after using the old first punch. The various machining processes which is required for producing the punch are done, beside heat treatments. Final results of this work show that it is possible to improve the dies and use it in the optimal way also it prove the possibility of manufacturing dies locally instead of importing it from outside Sudan.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"16 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":"122083121","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}
Hassan Abdo Hassan, Ibrahim Merghni, Mahmoud Elemam
This paper aims to determine and study the effect of applying a lean manufacturing approach on reducing cycle time in producing tube cases of the product Sh-3 missile. Since the tube case is the critical part of the sh-3 missiles set and it represents the bottleneck of a Sh-3 missile, the overall cycle time & increasing productivity is depending on it. Lean manufacturing is used to obtain the best resource utilization in various fields, in military manufacturing case, there are special conditions of operation and manufacturing which need a special deal and solutions, using the same tools of approach. In this article, waste analysis,waste identification, and waste elimination were applied using (PDSA approach, 5s, 8 wastes, PokaYoka, visual management, Kaizen, SMED) tools, the optimum cycle time will be determined after applying this study and will be presented in terms of hours and percentage of the previous situation. Generally, the current situation shows that the tube case of the product sh-3 missile is produced in 51 working days with 8 working days between each product and other. The predicted results of this study giving about 10% reduction in the cycle time of the target product.
{"title":"Product improvement by cycle time reduction through Lean Methodology (Product Sh-3 as Case Study)","authors":"Hassan Abdo Hassan, Ibrahim Merghni, Mahmoud Elemam","doi":"10.54388/jkues.v1i2.30","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.30","url":null,"abstract":"This paper aims to determine and study the effect of applying a lean manufacturing approach on reducing cycle time in producing tube cases of the product Sh-3 missile. Since the tube case is the critical part of the sh-3 missiles set and it represents the bottleneck of a Sh-3 missile, the overall cycle time & increasing productivity is depending on it. Lean manufacturing is used to obtain the best resource utilization in various fields, in military manufacturing case, there are special conditions of operation and manufacturing which need a special deal and solutions, using the same tools of approach. In this article, waste analysis,waste identification, and waste elimination were applied using (PDSA approach, 5s, 8 wastes, PokaYoka, visual management, Kaizen, SMED) tools, the optimum cycle time will be determined after applying this study and will be presented in terms of hours and percentage of the previous situation. Generally, the current situation shows that the tube case of the product sh-3 missile is produced in 51 working days with 8 working days between each product and other. The predicted results of this study giving about 10% reduction in the cycle time of the target product.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"97 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":"122015583","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}
Ebrahim Ayoup Mohamed Salih, Mohamed Abdelazim Abdalla Mohamed, Mohammed Mahdi Abdulla Mohammed Ahmed
This study shows the importance of re-engining a light aircraft operating with engines have old technologies consume much fuel and with fuel type harms the environment, which affecting the economic situation represented by specific fuel consumption (SFC) resulted in increasing the direct operating cost (DOC). In this paper, an analytical approach has been followed, the performance evaluation and the Weight and balance calculation have been calculated using Advanced Aircraft Analysis (AAA) and MATLAB based on the available data for the aircraft and engine. The selected engine was AUSTRO AE 300, a turbocharged four cylinders geared diesel piston engine equipped with a fuel injection system. This work gives a predictable result.
{"title":"A re-engining approach for light aircraft applied to SAFAT-03","authors":"Ebrahim Ayoup Mohamed Salih, Mohamed Abdelazim Abdalla Mohamed, Mohammed Mahdi Abdulla Mohammed Ahmed","doi":"10.54388/jkues.v1i2.31","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.31","url":null,"abstract":"This study shows the importance of re-engining a light aircraft operating with engines have old technologies consume much fuel and with fuel type harms the environment, which affecting the economic situation represented by specific fuel consumption (SFC) resulted in increasing the direct operating cost (DOC). In this paper, an analytical approach has been followed, the performance evaluation and the Weight and balance calculation have been calculated using Advanced Aircraft Analysis (AAA) and MATLAB based on the available data for the aircraft and engine. The selected engine was AUSTRO AE 300, a turbocharged four cylinders geared diesel piston engine equipped with a fuel injection system. This work gives a predictable result.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"240 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":"122986985","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}
One of the standard conditions for solidifying composite propellants consist of hydroxyl terminated poly-butadiene as a binder and ammonium perchlorate as oxidizer, is the curing process for certain time in a certain temperature. On this paper, the motives and reasons for the decreasing of this curing time were studied and discussed. The study and discussion include the productivity, cost, delivery, manpower, and maintenance points of view. By experiments and questionnaire work, it was seen that, all the previous points of view were affected positively. Generally, the productivity of the propellant was increased by 100%, the cost of curing process was decreased by 25% of the previous cost, the man power needed for the process of waiting and recording the readings was decreased by 50%, customer delivery process was fasted by 50% of the previous delivery time, and finally the maintenance processes due to equipment depreciation were improved by 50% from the previous. From the whole point of view, it was seen that, the decreasing of the curing time is very useful for the production of the propellant. Finally, it is observed that the decreasing of the curing time to the half time brought the same properties of the standard curing time, and then it is concluded that the deceasing of the curing time can be applied safely and usefully in the casting production line.
{"title":"Motives for Decreasing the Curing Time of HTPB-AP Composite Propellants","authors":"Nagmeldin Elamin, Ahemed.M. Bashir","doi":"10.54388/jkues.v1i2.64","DOIUrl":"https://doi.org/10.54388/jkues.v1i2.64","url":null,"abstract":"One of the standard conditions for solidifying composite propellants consist of hydroxyl terminated poly-butadiene as a binder and ammonium perchlorate as oxidizer, is the curing process for certain time in a certain temperature. On this paper, the motives and reasons for the decreasing of this curing time were studied and discussed. The study and discussion include the productivity, cost, delivery, manpower, and maintenance points of view. By experiments and questionnaire work, it was seen that, all the previous points of view were affected positively. Generally, the productivity of the propellant was increased by 100%, the cost of curing process was decreased by 25% of the previous cost, the man power needed for the process of waiting and recording the readings was decreased by 50%, customer delivery process was fasted by 50% of the previous delivery time, and finally the maintenance processes due to equipment depreciation were improved by 50% from the previous. From the whole point of view, it was seen that, the decreasing of the curing time is very useful for the production of the propellant. Finally, it is observed that the decreasing of the curing time to the half time brought the same properties of the standard curing time, and then it is concluded that the deceasing of the curing time can be applied safely and usefully in the casting production line.","PeriodicalId":129247,"journal":{"name":"Journal of Karary University for Engineering and Science","volume":"139 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":"115990768","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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