Browsing by Author "Abdelrahman M.M."

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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.