This report objective is to showcase the research, design, and development<br>process of th... more This report objective is to showcase the research, design, and development<br>process of the Solar Composite UAV for the Aerospace department graduation project.<br>The project was initiated in 2019 and this is its second year in the Aerospace dept. and<br>for this year it successfully designed, optimized, manufactured and tested a solar<br>operating composite UAV that can operate at different conditions and for multiple<br>applications. This report will show the design procedure as well as the production<br>results of the UAV. This project started with basic research that aimed at collecting<br>previous work and provide a benchmark for similar UAVs to investigate the wider<br>potential of similar products and set industry- relevant objective for this year's UAV.<br>Followed by a detailed design aimed at building up on previous year work as well as<br>designing an infrastructure for some added elements to be manufacturi...
The aim of this technical report is to handle the Simulate to Innovate Award<br>provided by... more The aim of this technical report is to handle the Simulate to Innovate Award<br>provided by ALTAIR, the objective of this award is to provide and recognize the use<br>of CAE (Computer-Aided Engineering) simulation on Cairo university Team's Urban<br>Car. This report and the analysis were represented during Shell Eco-Marathon 2021.<br>As ALTAIR supported the teams participated in the marathon by providing not just<br>free Altair software, but also some important virtual learning sessions to help and aid<br>teams to improve their designs and performance. Simulation-driven design methods<br>will be included with all the steps and results, and how could Altair software products<br>help us to handle this improvement. Finite element analysis (FEA) is mandatory for<br>design stages for either the chassis or the body. Altair Hypermesh with Opti structure<br>solver ease the cycle of meshing and applying the basic analyses which ...
This technical report aims to design an axial flow compressor based<br>on mean-line analysi... more This technical report aims to design an axial flow compressor based<br>on mean-line analysis at sea level static conditions. We are willing to a design<br>leading to the highest stage pressure ratio and meanwhile maintaining<br>high stage efficiency. There are two problems to be cosidered, the first one is a<br>subsonic axial flow compressor with maximum relative inlet Mach number 0.75,<br>and the other one is supersonic axial flow compressor with maximum relative inlet<br>Mach number 1.35. We are going to use the optimization method to handle the<br>design of these two axial flow compressors using a built-in function in MATLAB<br>software called fmincon which is a gradient-based method, used to find a minimum<br>of constrained non-linear multivariable function. <br>
The aim of this technical report is to make a vibration analysis of an<br>aluminum cantilev... more The aim of this technical report is to make a vibration analysis of an<br>aluminum cantilever beam with solid rectangular cross-section under concentrated<br>load. The continuous systems' vibration analysis conduct partial differential equations<br>have to be solved; there are three options to solve the continuous system, which are,<br>Exact solution, Approximated solution, and Finite Element Method in which in this<br>report I will call the three of them to solve the main problem of the report. FEA in<br>Ansys software using the Finite Element Method concept will be used here to solve the<br>continuous system. Free Vibration in which a force applied initially and structure<br>vibrates at its natural frequencies on the other side Forced Vibration a force applied<br>repeatedly to a mechanical system. <br>
This technical report aims to model two different systems. The modern<br>system is aircraft... more This technical report aims to model two different systems. The modern<br>system is aircraft pitching control in state-space and design the aircraft pitch to desired<br>specifications to get the behavior and performance of the aircraft. To make this control<br>we have to do quite good mathematical modeling to the aircraft. As known, Motion of<br>aircraft described by three rotations, Rolling, Yawing, and Pitching, the Pitching<br>rotation as it is very important in control the whole aircraft and it can't be neglected.<br>We are going to control and stabilize the pitching rotation of the aircraft using some<br>assumptions to linearize the problem to be controllable and easy to complete the statespace modeling and time-domain solution of state equations using state-transition<br>matrix. Transferring state-space into transfer function to be used in the design of<br>pitching of aircraft using pole placement, observer design, and i...
The aim of this technical report is to make a vibration analysis of an aluminum cantilever beam w... more The aim of this technical report is to make a vibration analysis of an aluminum cantilever beam with solid rectangular cross-section under concentrated load. The continuous systems’ vibration analysis conduct partial differential equations have to be solved; there are three options to solve the continuous system, which are, Exact solution, Approximated solution, and Finite Element Method in which in this report I will call the three of them to solve the main problem of the report. FEA in Ansys software using the Finite Element Method concept will be used here to solve the continuous system. Free Vibration in which a force applied initially and structure vibrates at its natural frequencies on the other side Forced Vibration a force applied repeatedly to a mechanical system.
This study focuses on the Arab literature published by researchers from all 22 members of the Ara... more This study focuses on the Arab literature published by researchers from all 22 members of the Arab League during the last 5 years before Arab Spring (2006–2010) and the 5 years after Arab Spring (2011–2015), in order to identify effects of the Arab Spring on research in the Arab world both performance and Productivity, based on bibliometrics analysis of the data extracted from Web of Science and InCites Essential Science Indicators provided by Thomson Reuters, and by using the statistical software package SPSS. The total productivity of Arab researchers before the Arab Spring was (103,917) document. Countries that witnessed revolution and government overthrown produced the largest productivity (42.5%). The Arab countries’ production doubled after the Arab Spring (214,864 document). Countries that witnessed Minor protests advanced to second place (30%) as a result of the leap that occurred in Saudi Arabia publications. The extent of collaboration among Arab countries before the Arab Spring was twice the number of publications in which they collaborated with the rest of the world. The number of citations was positive after the Arab Spring for 12 countries such as Saudi Arabia, Qatar, Iraq, Egypt and United Arab Emirates, while it was negative for 10 countries such as Tunisia, Algeria, Jordan, Kuwait and Lebanon. There is no significant difference between Arab countries exposed to different levels of protests of Arab Spring, and between Counties’ performance after and before Arab Spring. However, counties’ productivity after Arab Spring has increased higher than before Arab Spring.
The aim of this technical report is to handle the Simulate to Innovate Award provided by ALTAIR, ... more The aim of this technical report is to handle the Simulate to Innovate Award provided by ALTAIR, the objective of this award is to provide and recognize the use of CAE (Computer-Aided Engineering) simulation on Cairo university Team's Urban Car. This report and the analysis were represented during Shell Eco-Marathon 2021. As ALTAIR supported the teams participated in the marathon by providing not just free Altair software, but also some important virtual learning sessions to help and aid teams to improve their designs and performance. Simulation-driven design methods will be included with all the steps and results, and how could Altair software products help us to handle this improvement. Finite element analysis (FEA) is mandatory for design stages for either the chassis or the body. Altair Hypermesh with Opti structure solver ease the cycle of meshing and applying the basic analyses which applied to the car and applying a robust optimization to save some weight without decreasing the stiffness of the car with free sized optimization, with the aid of Hyperworks software for making some modifications on the CAD, like Snitching, suppress edges, or filling surfaces. Computational Fluid Dynamics (CFD) analysis is done using AcuSolve solver and visualized with the aid of AcuFieldView. [Simulate to Innovate Award Winner 2021]
This technical report aims to design an axial flow compressor based on mean-line analysis at sea ... more This technical report aims to design an axial flow compressor based on mean-line analysis at sea level static conditions. We are willing to a design leading to the highest stage pressure ratio and meanwhile maintaining high stage efficiency. There are two problems to be considered, the first one is a subsonic axial flow compressor with maximum relative inlet Mach number 0.75, and the other one is supersonic axial flow compressor with maximum relative inlet Mach number 1.35. We are going to use the optimization method to handle the design of these two axial flow compressors using a built-in function in MATLAB software called fmincon which is a gradient-based method, used to find a minimum of constrained non-linear multivariable function.
The aim of this project is to design a light Twin Engine propeller aircraft
that can cater to sma... more The aim of this project is to design a light Twin Engine propeller aircraft that can cater to small range about 450 miles and with a cruise speed 240 Knots. The project involves the design of light Twin Engine propeller aircraft which could accommodate about 6 passengers not including the pilot and co-pilot and considering no attendants involved providing a medium level of comfort that a twin propeller driven with small range is expected to provide. The aircraft design has been construct on some certain step processes. The processes that are applied in this project is goes like this; weight estimation, initial sizing, airfoil and geometry selection ,Thrust to weight and wing loading analysis, configuration layout, propulsion and fuel system analysis, aerodynamic analysis, stability and finally the cost analysis. Those processes has been implemented in this project and each and every study is applied by comply the methods and rules that are gathered from aircraft design books.
This technical report aims to model two different systems. The modern
system is aircraft pitching... more This technical report aims to model two different systems. The modern system is aircraft pitching control in state-space and design the aircraft pitch to desired specifications to get the behavior and performance of the aircraft. To make this control we have to do quite good mathematical modeling to the aircraft. As known, Motion of aircraft described by three rotations, Rolling, Yawing, and Pitching, the Pitching rotation as it is very important in control the whole aircraft and it can't be neglected. We are going to control and stabilize the pitching rotation of the aircraft using some assumptions to linearize the problem to be controllable and easy to complete the statespace modeling and time-domain solution of state equations using state-transition matrix. Transferring state-space into transfer function to be used in the design of pitching of aircraft using pole placement, observer design, and integral control techniques. All these techniques we are going to apply them to The commercial system which is the Oven system.
The most important goal for structural study is evaluation deformations and stresses on the struc... more The most important goal for structural study is evaluation deformations and stresses on the structural body. In this paper, a comparison between structure analysis of different wings in past-which uses less technology and many assumptions to obtain a solution-and in the present-which uses a very high technology with nearly no assumptions to obtain the exact solution. So we will solve aircraft's wing as a cantilever beam by using Matlab software which gives approximated results compared to the exact solution depends on the assumptions used and this approximations is non-acceptable anymore. In addition, modeling and structural analysis on Real aircraft's wing using finite Element Method (FEM) and finite Volume Method (FVM) that gives exact solution. Also illustrate Fluid Structure interaction (FSI) and how to connect between them on Ansys with System coupling to make Stress analysis and see the deformation on wing due to the fluid.
This technical report aims to Study and Analyze the Attitude Determination and Control Subsystem ... more This technical report aims to Study and Analyze the Attitude Determination and Control Subsystem ADCS of a Small Remote Sensing Satellite, beginning with Describing the ADCS system of small satellites, its components and the function of each component, classifications of ADCS for small satellites and give some actual example of these satellites. Secondly describing the attitude control system actuators, Studying, analyzing the performance of actuators in real life, and Describing the different types of sensors used in a small satellite control system. In System Operation we have to Describe technically how the system will perform a maneuver, Describe the modes of operation of the ADCS of a small satellite, and Describe in detail the operational steps of ADCS and the satellite for moving the satellite through a typical maneuver.
This technical report aims to define academic and technical writing, describes the importance of ... more This technical report aims to define academic and technical writing, describes the importance of it, and classify the technical writing, showing their types and importance of each type. Talking deeply about how can anyone write a proper Technical Writing which is formal and follow the instructions of Consistent Stylistic Approach like MLA, APA, and Chicago Manual which are the standards that you have to follow. Talking about Report writing and specify what it deals with, what is its importance of it, and list the sequence of headings and outlines you have to follow. Declaring the academic writing skills and how anyone can improve it to be a quite good writer or researcher.
This report objective is to showcase the research, design, and development<br>process of th... more This report objective is to showcase the research, design, and development<br>process of the Solar Composite UAV for the Aerospace department graduation project.<br>The project was initiated in 2019 and this is its second year in the Aerospace dept. and<br>for this year it successfully designed, optimized, manufactured and tested a solar<br>operating composite UAV that can operate at different conditions and for multiple<br>applications. This report will show the design procedure as well as the production<br>results of the UAV. This project started with basic research that aimed at collecting<br>previous work and provide a benchmark for similar UAVs to investigate the wider<br>potential of similar products and set industry- relevant objective for this year's UAV.<br>Followed by a detailed design aimed at building up on previous year work as well as<br>designing an infrastructure for some added elements to be manufacturi...
The aim of this technical report is to handle the Simulate to Innovate Award<br>provided by... more The aim of this technical report is to handle the Simulate to Innovate Award<br>provided by ALTAIR, the objective of this award is to provide and recognize the use<br>of CAE (Computer-Aided Engineering) simulation on Cairo university Team's Urban<br>Car. This report and the analysis were represented during Shell Eco-Marathon 2021.<br>As ALTAIR supported the teams participated in the marathon by providing not just<br>free Altair software, but also some important virtual learning sessions to help and aid<br>teams to improve their designs and performance. Simulation-driven design methods<br>will be included with all the steps and results, and how could Altair software products<br>help us to handle this improvement. Finite element analysis (FEA) is mandatory for<br>design stages for either the chassis or the body. Altair Hypermesh with Opti structure<br>solver ease the cycle of meshing and applying the basic analyses which ...
This technical report aims to design an axial flow compressor based<br>on mean-line analysi... more This technical report aims to design an axial flow compressor based<br>on mean-line analysis at sea level static conditions. We are willing to a design<br>leading to the highest stage pressure ratio and meanwhile maintaining<br>high stage efficiency. There are two problems to be cosidered, the first one is a<br>subsonic axial flow compressor with maximum relative inlet Mach number 0.75,<br>and the other one is supersonic axial flow compressor with maximum relative inlet<br>Mach number 1.35. We are going to use the optimization method to handle the<br>design of these two axial flow compressors using a built-in function in MATLAB<br>software called fmincon which is a gradient-based method, used to find a minimum<br>of constrained non-linear multivariable function. <br>
The aim of this technical report is to make a vibration analysis of an<br>aluminum cantilev... more The aim of this technical report is to make a vibration analysis of an<br>aluminum cantilever beam with solid rectangular cross-section under concentrated<br>load. The continuous systems' vibration analysis conduct partial differential equations<br>have to be solved; there are three options to solve the continuous system, which are,<br>Exact solution, Approximated solution, and Finite Element Method in which in this<br>report I will call the three of them to solve the main problem of the report. FEA in<br>Ansys software using the Finite Element Method concept will be used here to solve the<br>continuous system. Free Vibration in which a force applied initially and structure<br>vibrates at its natural frequencies on the other side Forced Vibration a force applied<br>repeatedly to a mechanical system. <br>
This technical report aims to model two different systems. The modern<br>system is aircraft... more This technical report aims to model two different systems. The modern<br>system is aircraft pitching control in state-space and design the aircraft pitch to desired<br>specifications to get the behavior and performance of the aircraft. To make this control<br>we have to do quite good mathematical modeling to the aircraft. As known, Motion of<br>aircraft described by three rotations, Rolling, Yawing, and Pitching, the Pitching<br>rotation as it is very important in control the whole aircraft and it can't be neglected.<br>We are going to control and stabilize the pitching rotation of the aircraft using some<br>assumptions to linearize the problem to be controllable and easy to complete the statespace modeling and time-domain solution of state equations using state-transition<br>matrix. Transferring state-space into transfer function to be used in the design of<br>pitching of aircraft using pole placement, observer design, and i...
The aim of this technical report is to make a vibration analysis of an aluminum cantilever beam w... more The aim of this technical report is to make a vibration analysis of an aluminum cantilever beam with solid rectangular cross-section under concentrated load. The continuous systems’ vibration analysis conduct partial differential equations have to be solved; there are three options to solve the continuous system, which are, Exact solution, Approximated solution, and Finite Element Method in which in this report I will call the three of them to solve the main problem of the report. FEA in Ansys software using the Finite Element Method concept will be used here to solve the continuous system. Free Vibration in which a force applied initially and structure vibrates at its natural frequencies on the other side Forced Vibration a force applied repeatedly to a mechanical system.
This study focuses on the Arab literature published by researchers from all 22 members of the Ara... more This study focuses on the Arab literature published by researchers from all 22 members of the Arab League during the last 5 years before Arab Spring (2006–2010) and the 5 years after Arab Spring (2011–2015), in order to identify effects of the Arab Spring on research in the Arab world both performance and Productivity, based on bibliometrics analysis of the data extracted from Web of Science and InCites Essential Science Indicators provided by Thomson Reuters, and by using the statistical software package SPSS. The total productivity of Arab researchers before the Arab Spring was (103,917) document. Countries that witnessed revolution and government overthrown produced the largest productivity (42.5%). The Arab countries’ production doubled after the Arab Spring (214,864 document). Countries that witnessed Minor protests advanced to second place (30%) as a result of the leap that occurred in Saudi Arabia publications. The extent of collaboration among Arab countries before the Arab Spring was twice the number of publications in which they collaborated with the rest of the world. The number of citations was positive after the Arab Spring for 12 countries such as Saudi Arabia, Qatar, Iraq, Egypt and United Arab Emirates, while it was negative for 10 countries such as Tunisia, Algeria, Jordan, Kuwait and Lebanon. There is no significant difference between Arab countries exposed to different levels of protests of Arab Spring, and between Counties’ performance after and before Arab Spring. However, counties’ productivity after Arab Spring has increased higher than before Arab Spring.
The aim of this technical report is to handle the Simulate to Innovate Award provided by ALTAIR, ... more The aim of this technical report is to handle the Simulate to Innovate Award provided by ALTAIR, the objective of this award is to provide and recognize the use of CAE (Computer-Aided Engineering) simulation on Cairo university Team's Urban Car. This report and the analysis were represented during Shell Eco-Marathon 2021. As ALTAIR supported the teams participated in the marathon by providing not just free Altair software, but also some important virtual learning sessions to help and aid teams to improve their designs and performance. Simulation-driven design methods will be included with all the steps and results, and how could Altair software products help us to handle this improvement. Finite element analysis (FEA) is mandatory for design stages for either the chassis or the body. Altair Hypermesh with Opti structure solver ease the cycle of meshing and applying the basic analyses which applied to the car and applying a robust optimization to save some weight without decreasing the stiffness of the car with free sized optimization, with the aid of Hyperworks software for making some modifications on the CAD, like Snitching, suppress edges, or filling surfaces. Computational Fluid Dynamics (CFD) analysis is done using AcuSolve solver and visualized with the aid of AcuFieldView. [Simulate to Innovate Award Winner 2021]
This technical report aims to design an axial flow compressor based on mean-line analysis at sea ... more This technical report aims to design an axial flow compressor based on mean-line analysis at sea level static conditions. We are willing to a design leading to the highest stage pressure ratio and meanwhile maintaining high stage efficiency. There are two problems to be considered, the first one is a subsonic axial flow compressor with maximum relative inlet Mach number 0.75, and the other one is supersonic axial flow compressor with maximum relative inlet Mach number 1.35. We are going to use the optimization method to handle the design of these two axial flow compressors using a built-in function in MATLAB software called fmincon which is a gradient-based method, used to find a minimum of constrained non-linear multivariable function.
The aim of this project is to design a light Twin Engine propeller aircraft
that can cater to sma... more The aim of this project is to design a light Twin Engine propeller aircraft that can cater to small range about 450 miles and with a cruise speed 240 Knots. The project involves the design of light Twin Engine propeller aircraft which could accommodate about 6 passengers not including the pilot and co-pilot and considering no attendants involved providing a medium level of comfort that a twin propeller driven with small range is expected to provide. The aircraft design has been construct on some certain step processes. The processes that are applied in this project is goes like this; weight estimation, initial sizing, airfoil and geometry selection ,Thrust to weight and wing loading analysis, configuration layout, propulsion and fuel system analysis, aerodynamic analysis, stability and finally the cost analysis. Those processes has been implemented in this project and each and every study is applied by comply the methods and rules that are gathered from aircraft design books.
This technical report aims to model two different systems. The modern
system is aircraft pitching... more This technical report aims to model two different systems. The modern system is aircraft pitching control in state-space and design the aircraft pitch to desired specifications to get the behavior and performance of the aircraft. To make this control we have to do quite good mathematical modeling to the aircraft. As known, Motion of aircraft described by three rotations, Rolling, Yawing, and Pitching, the Pitching rotation as it is very important in control the whole aircraft and it can't be neglected. We are going to control and stabilize the pitching rotation of the aircraft using some assumptions to linearize the problem to be controllable and easy to complete the statespace modeling and time-domain solution of state equations using state-transition matrix. Transferring state-space into transfer function to be used in the design of pitching of aircraft using pole placement, observer design, and integral control techniques. All these techniques we are going to apply them to The commercial system which is the Oven system.
The most important goal for structural study is evaluation deformations and stresses on the struc... more The most important goal for structural study is evaluation deformations and stresses on the structural body. In this paper, a comparison between structure analysis of different wings in past-which uses less technology and many assumptions to obtain a solution-and in the present-which uses a very high technology with nearly no assumptions to obtain the exact solution. So we will solve aircraft's wing as a cantilever beam by using Matlab software which gives approximated results compared to the exact solution depends on the assumptions used and this approximations is non-acceptable anymore. In addition, modeling and structural analysis on Real aircraft's wing using finite Element Method (FEM) and finite Volume Method (FVM) that gives exact solution. Also illustrate Fluid Structure interaction (FSI) and how to connect between them on Ansys with System coupling to make Stress analysis and see the deformation on wing due to the fluid.
This technical report aims to Study and Analyze the Attitude Determination and Control Subsystem ... more This technical report aims to Study and Analyze the Attitude Determination and Control Subsystem ADCS of a Small Remote Sensing Satellite, beginning with Describing the ADCS system of small satellites, its components and the function of each component, classifications of ADCS for small satellites and give some actual example of these satellites. Secondly describing the attitude control system actuators, Studying, analyzing the performance of actuators in real life, and Describing the different types of sensors used in a small satellite control system. In System Operation we have to Describe technically how the system will perform a maneuver, Describe the modes of operation of the ADCS of a small satellite, and Describe in detail the operational steps of ADCS and the satellite for moving the satellite through a typical maneuver.
This technical report aims to define academic and technical writing, describes the importance of ... more This technical report aims to define academic and technical writing, describes the importance of it, and classify the technical writing, showing their types and importance of each type. Talking deeply about how can anyone write a proper Technical Writing which is formal and follow the instructions of Consistent Stylistic Approach like MLA, APA, and Chicago Manual which are the standards that you have to follow. Talking about Report writing and specify what it deals with, what is its importance of it, and list the sequence of headings and outlines you have to follow. Declaring the academic writing skills and how anyone can improve it to be a quite good writer or researcher.
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Papers by Bahaa Ibrahim
high stage efficiency. There are two problems to be considered, the first one is a subsonic axial flow compressor with maximum relative inlet Mach number 0.75, and the other one is supersonic axial flow compressor with maximum relative inlet Mach number 1.35. We are going to use the optimization method to handle the design of these two axial flow compressors using a built-in function in MATLAB software called fmincon which is a gradient-based method, used to find a minimum of constrained non-linear multivariable function.
that can cater to small range about 450 miles and with a cruise speed 240 Knots. The project involves the design of light Twin Engine propeller aircraft which could accommodate about 6 passengers not including the pilot and co-pilot and considering no attendants involved providing a medium level of comfort that a twin propeller driven with small range is expected to provide. The aircraft design has been construct on some certain step processes. The processes that are applied in this project is goes like this; weight estimation, initial sizing, airfoil and geometry selection ,Thrust to weight and wing loading analysis, configuration layout, propulsion and fuel system analysis, aerodynamic analysis, stability and finally the cost analysis. Those processes has been implemented in this project and each and every study is applied by comply the methods and rules that are gathered from aircraft design books.
system is aircraft pitching control in state-space and design the aircraft pitch to desired
specifications to get the behavior and performance of the aircraft. To make this control
we have to do quite good mathematical modeling to the aircraft. As known, Motion of
aircraft described by three rotations, Rolling, Yawing, and Pitching, the Pitching
rotation as it is very important in control the whole aircraft and it can't be neglected.
We are going to control and stabilize the pitching rotation of the aircraft using some
assumptions to linearize the problem to be controllable and easy to complete the statespace modeling and time-domain solution of state equations using state-transition
matrix. Transferring state-space into transfer function to be used in the design of
pitching of aircraft using pole placement, observer design, and integral control
techniques. All these techniques we are going to apply them to The commercial system
which is the Oven system.
high stage efficiency. There are two problems to be considered, the first one is a subsonic axial flow compressor with maximum relative inlet Mach number 0.75, and the other one is supersonic axial flow compressor with maximum relative inlet Mach number 1.35. We are going to use the optimization method to handle the design of these two axial flow compressors using a built-in function in MATLAB software called fmincon which is a gradient-based method, used to find a minimum of constrained non-linear multivariable function.
that can cater to small range about 450 miles and with a cruise speed 240 Knots. The project involves the design of light Twin Engine propeller aircraft which could accommodate about 6 passengers not including the pilot and co-pilot and considering no attendants involved providing a medium level of comfort that a twin propeller driven with small range is expected to provide. The aircraft design has been construct on some certain step processes. The processes that are applied in this project is goes like this; weight estimation, initial sizing, airfoil and geometry selection ,Thrust to weight and wing loading analysis, configuration layout, propulsion and fuel system analysis, aerodynamic analysis, stability and finally the cost analysis. Those processes has been implemented in this project and each and every study is applied by comply the methods and rules that are gathered from aircraft design books.
system is aircraft pitching control in state-space and design the aircraft pitch to desired
specifications to get the behavior and performance of the aircraft. To make this control
we have to do quite good mathematical modeling to the aircraft. As known, Motion of
aircraft described by three rotations, Rolling, Yawing, and Pitching, the Pitching
rotation as it is very important in control the whole aircraft and it can't be neglected.
We are going to control and stabilize the pitching rotation of the aircraft using some
assumptions to linearize the problem to be controllable and easy to complete the statespace modeling and time-domain solution of state equations using state-transition
matrix. Transferring state-space into transfer function to be used in the design of
pitching of aircraft using pole placement, observer design, and integral control
techniques. All these techniques we are going to apply them to The commercial system
which is the Oven system.