Aircraft Trim Analysis by Particle Swarm Optimization
Keywords:
Trim Analysis, Particle Swarm Optimization, Steady-State Flight, F-16 Nonlinear Dynamic ModelAbstract
In this work, a detailed nonlinear model for the full dynamics of the F-16 aircraft is first developed and coded in MATLAB. This model includes the gravity model, variable atmospheric parameters, tabular aerodynamic functions, propulsion model, nonlinear control surface actuation models, and six degrees of freedom equations of motion. A numerical tool for computing all possible trim values, using the aforementioned model, is then developed. This tool can calculate the trim values at different operating points. In the developed algorithms, particle swarm optimization (PSO) method, which is a meta-heuristic method with a high convergence rate over a continuous search space, is used. Simulations around the calculated trim values are then made using the developed model. Simulation results confirm that the PSO based trim algorithm can find all the trim values with a high accuracy.
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The manuscript with title and authors is being submitted for publication in Journal of Aeronautics and Space Technologies. This article or a major portion of it was not published, not accepted and not submitted for publication elsewhere. If accepted for publication, I hereby grant the unlimited and all copyright privileges to Journal of Aeronautics and Space Technologies.
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