항공기 날개 스파의 단면적과 위치를 설계변수로 하는 중량 최적화 연구 = Aircraft Wing Box Weight Optimization by Adjusting Spar Cross-section Area and Location

다국어 초록 (Multilingual Abstract)

In this paper, the optimization is performed to find a more efficient aircraft wing box structure. A less weight aircraft wing box while satisfying required constraints is found by adjusting the wing spar cross-section area and location. Every optimization problem is constituted by an object function, design variables and constraints. In this thesis, stress conditions at each spar are used as constraints. In the case of the spar cross-section area optimization, two cases are handled. First, the spar cross-section area is assumed same at all span and there is one design variable for a spar. Secondly, the spar cross-section area is different by span direction and there are several design variables for a spar. In the case of spar location optimization, end positions of the each spar are selected as design variables. The reasonableness and accuracy of the optimization result is verified by comparing stress distributions and deformations before and after optimization.
MSC/NASTRAN is used for the finite element analysis and the optimization.

목차 (Table of Contents)

• 1.서론
• 2.날개의 유한요소 이상화
• 3.최적화 문제의 정식화
• 3.1 스파 단면적 최적화 문제
• 3.2 스파 배치 최적화
• 4.최적화 결과 분석
• 5.결론