External geometry and flight performance optimization of turbojet propelled air to ground missiles

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Date

2011

Author

Dede, Emre

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The primary goal for the conceptual design phase of a generic air-to-ground missile is to reach an optimal external configuration which satisfies the flight performance requirements such as flight range and time, launch mass, stability, control effectiveness as well as geometric constraints imposed by the designer. This activity is quite laborious and requires the examination and selection among huge numbers of design alternatives. This thesis is mainly focused on multi objective optimization techniques for an air to-ground missile design by using heuristics methods namely as Non Dominated Sorting Genetic Algorithm and Multiple Cooling Multi Objective Simulated Annealing Algorithm. Futhermore, a new hybrid algorithm is also introduced using Simulated Annealing cascaded with the Genetic Algorithm in which the optimized solutions are passed to the Genetic Algorithm as the intial population. A trade off study is conducted for the three optimization algorithm alternatives in terms of accuracy and quality metrics of the optimized Pareto fronts.

Subject Keywords

Vehicles, Remotely piloted., Aerospace engineering., Aeronautics.

URI

http://etd.lib.metu.edu.tr/upload/12613953/index.pdf
https://hdl.handle.net/11511/20974

Collections

Graduate School of Natural and Applied Sciences, Thesis

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Citation Formats

E. Dede, “External geometry and flight performance optimization of turbojet propelled air to ground missiles,” M.S. - Master of Science, Middle East Technical University, 2011.