Browsing by Author "Khardi, Salah"

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    An Efficient Non-Linear Application Algorithm Predictive Model for a Multi Aircraft Landing Dynamic System AIRLADYS R2019A+
    (Open Journal of Optimization, 2020) Nahayo, Fulgence; Khardi, Salah
    The aim of this paper is to set up an efficient nonlinear application algorithm predictive model for a multi aircraft landing dynamic system called “Aircraft Landing Dynamic System, Release 2019A+ version “AIRLADYS R2019A+”. This programming software combines dynamic programming technic for mathematical computing and optimisation run under AMPL and KNITRO Solver. It uses also a descriptive programming technic for software design. The user interfaces designed in Glade are saved as XML, and by using the GtkBuilder GTK+ object these can be loaded by applications dynamically as needed. By using GtkBuilder, Glade XML files can be used in numerous programming languages including C, C++, C#, Java, Perl, Python, AMPL, etc. Glade is Free Software released under the GNU GPL License. By these tools, the solved problem is a mathematical modelization problem as a non-convex optimal control governed by ordinary non-linear differential equations. The dynamic programming technic is applied because it is a sufficiently high order and it does not require computation of the partial derivatives of the aircraft dynamic. This application will be coded with Linux system on 64 bit operating system, but it can also be run on the windows system. High running performances are obtained with results giving feasible trajectories with a robust optimizing of the objective function.
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    Réduction du bruit de deux avions commerciaux en approche par une technique de commande optimale
    (Researchgate, 2010) Nahayo, Fulgence; Khardi, Salah; Hamadiche, Mahmoud; Et al.
    L’objectif de ce travail est le d´eveloppement d’un mod`ele d’optimisation acoustique de trajectoires de vol minimisant les bruits per¸cus au sol pour deux avions. Il s’agit de minimiser le bruit tenant compte des contraintes de vol. La dynamique de vol, associ´ee au crit`ere `a minimiser g´en`ere un probl`eme de commande optimale r´egi par des ´equations diff´erentielles ordiniaires non-lin´eaires. Le probl`eme est resolu `a l’aide d’une m´ethode newtonienne consid´erant les conditions d’optimalit´e de Karush-Kuhn-Tucker et une m´ethode SQP. Les r´esultats obtenus montrent des r´eductions significatives des niveaux de bruit. En fonction de la distance s´eparant les deux avions en vol, la trajectoire optimale d’approche est obtenue.
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    Two-Aircraft Dynamic System on Approach. Flight Path and noise Optimization
    (ResearchGate, 2012) Nahayo, Fulgence; Khardi, Salah; Haddou, Mounir
    The aim of this paper is to present and to solve a mathematical model of two-aircraft optimal control problem reducing noise during the approach. This is a non-convex optimal control problem governed by ordinary non-linear differential equations. A Symplectic Partitioned Runge-Kutta discretization and the Pontryaguin maximum principle are used. Discretization scheme provides a sufficiently high order requiring a computation of the partial derivatives of the aircraft dynamic parameters. The nonlinear interior point trust region optimization solver is applied. Numerical experiments and results are presented. They confirm the feasible optimized trajectories contributing to a significant noise reduction.
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    Two-Aircraft optimal control problem. The in-flight noise reduction
    (ResearchGate, 2012) Nahayo, Fulgence; Khardi, Salah; Haddou,Mounir; Et al.
    The aim of this paper is to present and solve a mathematical model of a two-aircraft optimal control problem reducing the noise on the ground during the approach. The mathematical modelization of this problem is a non-convex optimal control governed by ordinary non-linear differential equations. To solve this problem, A direct method and a Runge-Kutta RK4 discretization schema are used. This discretization schema is chosed because it is a sufficiently high order and it does-not require computation of the partial derivatives of the aircraft dynamic. The Nonlinear Interior point Trust Region Optimization solver KNITRO is applied. A large set of numerical experiments is presented. The obtained results give feasible trajectories with a significant noise reduction.