Optimization of A Simple Aircraft Wing
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In this parametric study the aircraft wing model was designed to a light weight, comfortable model which is also cost effective than the some of the existing models around the world. On testing the wing by applying uniformly distributed load, the Equivalent Stresses and the Total Deformations are calculated.The design of experiments was generated using central composite design method and subsequent optimization is carried out using screening method. Duly considered Aluminium material has the values of weight as 1050kg, 25985384.62 equivalent stresses. Now these values are optimized by 10% to t...
In this parametric study the aircraft wing model was designed to a light weight, comfortable model which is also cost effective than the some of the existing models around the world. On testing the wing by applying uniformly distributed load, the Equivalent Stresses and the Total Deformations are calculated.The design of experiments was generated using central composite design method and subsequent optimization is carried out using screening method. Duly considered Aluminium material has the values of weight as 1050kg, 25985384.62 equivalent stresses. Now these values are optimized by 10% to the originally obtained values. The optimized values are, weight of leg is 948.2 kg, equivalent stresses are 2.8163E+07 and deformation is 0.81606m.Optimization problem was investigated in this paper. It is noticed that even though the basic geometry and the same sets of design variables are used, problem has radicaldifference with respect to design sensitivity. Optimized Problem possesses high sensitivity with respect to sizing design variables. Generally, it is not possible to determine beforehand which subset of design variables will be dominant in terms of sensitivity.
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