The development of a biologically inspired methodology for topology, shape, sizing, and control surface optimization of aircraft lifting surfaces is presented. The methodology is based on the map L-systems modeling of cellular division to generate the substructure topology. This is combined with variables for aerodynamic shape, structural sizing, and control surfaces (number, size, location, and aeroelastic trimmed settings) and constraints on stiffness, strength, local skin panel buckling, static aeroelastic response (roll performance, pitch rate, trimmed angle of attack), and flutter requirements. A dual-objective function is formulated with weight and and is solved with a bilevel optimization algorithm. The map -system rules that develop the topology are evolved using a genetic algorithm in the outer optimization loop on and weight, which obtains the optimal parameter settings for topology, shape, and control surfaces, whereas the inner loop performs weight minimization with the structural sizing variables. The methodology is demonstrated on the design of a generic fighter aircraft wing.
Optimization of Aircraft Lifting Surfaces Using a Cellular Division Method
Journal of Aircraft ; 52 , 6 ; 2051-2063
01.11.2015
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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