This article presents basic results from wing planform optimization for minimum drag with constraints on structural weight and maximum lift. Analyses in each of these disciplines are developed and integrated to yield successful optimization of wing planform shape. Results demonstrate the importance of weight constraints, compressibility drag, maximum lift, and static aeroelasticity on wing shape, and the necessity of modeling these effects to achieve realistic optimized planforms.
Nomenclature
A ,= rib boom cross-sectional area A c = area enclosed by structural box cross section A ,(. = rib web cross-sectional area
Multidisciplinary design optimization is considered in the context of designing a family of aircraft. A framework is developed in which multiple aircraft, each with different missions but sharing common parts, can be optimized simultaneously. The new framework is used to gain insight to the effect of design variable scaling on the optimization algorithm. Results are presented for a two-member family whose individual missions differ significantly. Both missions can be satisfied with common designs. Moreover, optimizing both planes simultaneously rather than following the traditional baseline plus derivative approach vastly improves the common solution. A cost modeling framework is outlined that allows the value of commonality to be quantified for design and manufacturing costs. A notional example is presented to show the cost benefit that may be achieved by designing a common family of aircraft.
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