Browsing by Author "Bayoumy A.M."

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Fixed ground-target tracking control of satellites using a nonlinear model predictive control
(International Information and Engineering Technology Association, 2018) Elbeltagy A.E.H.M.; Youssef A.M.; Bayoumy A.M.; Elhalwagy Y.Z.; Aircraft Mechanics Dep.; MTC; Cairo; Egypt; Aircraft Electric Equipment Dep.; MTC; Cairo; Egypt; Mechanical Engineering Dep.; MSA; Cairo; Egypt; Navigation Dep.; MTC; Cairo; Egypt
This paper proposes a novel solution to the fixed-ground target tracking control problem of satellites utilizing a Nonlinear Model Predictive Control approach (NMPC). The Continuation / Generalized Minimal Residual (C/GMRES) algorithm is selected as a promising fast solver to an optimal control problem in real time. The algorithm could perfectly deal with the huge computational load of this approach, represented in solving Riccati differential equation, by simple and efficient approximations. A new control-oriented model converting the main tracking problem into a simple regulation problem is developed. This simple and easy traceable reformulated model has an advantage in dealing with modeling errors and unplanned external environmental disturbances. The update of the control input is obtained by integrating a deduced time-dependent inputs and Lagrange multipliers vector; representing the solution of a set of linear equations and corresponding to the optimality conditions. The proposed algorithm is simulated using real satellite parameters to track a fixed-ground target for reconnaissance purposes. The simulation results show that the algorithm of C/GMRES method can track a desired fixed ground target robustly, with precise tracking error and guaranteed safe stability limits for shooting activities throughout the overpass flight. � 2017 IIETA.
Inverse simulation of symmetric flight of a guided gliding subsonic flying body
(American Institute of Aeronautics and Astronautics Inc, AIAA, 2018) Elsherbiny A.M.; Bayoumy A.M.; Elshabka A.M.; Abdelrahman M.M.; Aeronautical Department; Military Technical College; Cairo; Egypt; Mechatronics Department; Aeronatuical department; MSA University; Giza; Egypt; Aeronautical Department; Cairo university; Cairo; Egypt
Guided and smart ammunitions are getting interest in the last decades. This paper aims to obtain the time history of control surfaces deflections of a subsonic guided gliding flying body using an inverse dynamics technique in vertical plane motion. This flying body has a standoff capability and designed to attack fixed targets. A 2D trajectory is designed to achieve two requirements. The first is to achieve the maximum range during glide phase subjected to maximum available angle of attack. The second is to achieve the maximum impact angle and impact velocity during terminal phase subjected to maximum available pitch deflection angle. Then a three degree of freedom inverse simulation is performed to obtain the deflection angles time history along the generated trajectory trajectory. Finally, a three degree of freedom direct simulation is performed using these deflection angles. Comparing the inverse and direct trajectories validates the inverse simulation equations, methodology, and results where the difference between the two trajectories time history data can be neglected. � 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
Modeling, simulation and hybrid optimization method as design tools for range extension kit of a subsonic flying body
(American Institute of Aeronautics and Astronautics Inc, AIAA, 2018) Elsherbiny A.M.; Bayoumy A.M.; Elshabka A.M.; Abdelrahman M.M.; Aeronautical Department; Military Technical College; Cairo; Egypt; Aeronatuical department; Mechatronics Department; MSA University; Giza; Egypt; Aeronautical Department; Cairo university; Cairo; Egypt
In this paper a hybrid optimization method is introduced to convert the aerodynamic shape of a conventional aerial subsonic flying body into a glide one by providing a range extension kit and fins. The selections of configuration and airfoils are described depending on the tactical requirements and flight regimes. The wing and fins sizing is obtained using four different methods subjected to geometric constraints. The first method is an iterative optimization method using linear aerodynamic coefficients and derivatives. The second method is a multi-objective function genetic algorithm aims to maximize stability, controllability and lift-drag ratio within certain weights using linear aerodynamic data. The third method is a genetic algorithm optimization function integrated with MISSILE DATCOM aims to maximize lift-drag ratio. The fourth method is a hybrid optimization method that integrate MISSILE DATCOM with both genetic algorithm and gradient-based optimization method. Then perform a direct uncontrolled six degree of freedom simulation for the four designs and the conventional flying body. Comparing the results of ranges for these bodies reveals that the hybrid optimization method has the best range over the other designs including the conventional flying body. � 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
Modelling and simulation of 3DOF parallel manipulator using artificial neural network
(Institute of Physics Publishing, 2019) Youssef A.; Bayoumy A.M.; Rostom M.; Tolbah F.A.; T.A at Mechatronics Dept.; Faculty of Engineering; MUST; Giza; Egypt; Mechatronics Dept.; Faculty of Engineering; MSA; Giza; Egypt; Mechatronics Dept.; Faculty of Engineering; AASMT; Cairo; Egypt; Mechatronics Dept.; Faculty of Engineering; ASU; Cairo; Egypt
Parallel Robot (PR) has shown its ability to be precise in its movement. Actuators move simultaneously to achieve the required target, on top of that its payload is much greater than what a serial robot can withstand. To determine workspace of the robot with known angles Forward kinematics has to be introduced which, bring a lot of difficulty as it requires the solution of multiple coupled nonlinear algebraic equations. Those equations bring multiple valid solutions. Those solutions could lead to different locations. As it is not going to make the pick and place for PR will be easier. This paper will discuss a numerical method that calculates the Forward Kinematics for PR. This method uses Artificial Neural Network which relay on training with a certain number of iterations. The set of data to be used in the training can be obtained from PR simulation. This method will serve to know workspace around PR as it will help it to pick the target object. � 2019 Published under licence by IOP Publishing Ltd.