AERO-STRUCTURAL MDO OF A SPAR-TANK-TYPE WING FOR AIRCRAFT CONCEPTUAL DESIGN

摘要

A study on a multidisciplinary design optimization tool for aircraft conceptual design is proposed. The wing of a conceptual aircraft is the baseline of this work. A tubular spar instead of a typical wing box structure is used to support the loads and to work as fuel tank. The aerodynamic analysis uses the Weissinger method, classic closed thin walled tubes stress analysis is employed to the structural evaluation and as the optimization code, a genetic algorithm was implemented. The aim of this study is to optimize the aerodynamics of the wing, minimize its structural weight and maximize the fuel volume, considering four basic flight conditions that are take off, climb, cruise and loiter.