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- 주제어 : 항공기 날개 설계(Aircraft Wing Design) (검색결과 6 건)
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항공기날개형상설계를 위한 distributed design의 적용
김태희,최성임 한국항공우주학회 2013 한국항공우주학회 학술발표회 논문집 Vol.2013 No.11
항공기는 연관된 매우 많은 하위 시스템들로 이루어져 있기 때문에 이에 대한 설계는 매우 어려운 일이다. 그러므로 항공기 설계에 있어 각 분야들을 따로 생각하는 것은 의미가 없으며 이들에 대한 연관성을 고려하여 통합적인 해석이 매우 중요하다. 다분야 최적설계는 이러한 문제들을 해결하는 방법론으로서 최근 많은 연구가 진행되고 있다. 본 연구의 목적은 다분야 최적설계 방법론을 항공기 날개 설계에 적용해 보는 것이다. Distributed design은 다분야 최적설계의 한 방법으로서 전체 문제를 상위수준과 하위수준으로 나누어 각 분야에 독립적인 역할을 부여하는 방법이다. Collaborative Optimization(CO)와 Concurrent Sub-Space Optimization(CSSO)는 distributed design의 일종으로 서로 다른 형태와 특성을 가지고 있다. 본 연구에서는 간단한 예제를 통해 CO와 CSSO의 장단점을 알아보고 이를 항공기 날개 형상 설계에 적용해보기로 한다. Aircraft design needs considerable effect because aircraft is composed of many subsystem which are highly coupled. Therefore, decoupled analysis of an aircraft design is meaningless and it is important to perform an integrated analysis. A multidisciplinary Design Optimization(MDO) is methodology that tries to solve those issues and many researches are performed recently. The purpose of this study is application of MDO to aircraft wing design. A distributed design which is one of MDO divides the aircraft system into system and subspace levels and distributes independent role to each discipline. Collaborative Optimization(CO) and Concurrent Sub-Space Optimization(CSSO) are kinds of distributed design which have different formulations and characteristics. In current study, we compare CO and CSSO about their advantages and weakness through analytic function and they are applied to aircraft wing shape design.
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박국진,박용진,강희진,김승조 한국항공우주학회 2012 한국항공우주학회 학술발표회 논문집 Vol.2012 No.4
본 논문에서는 항공기 날개의 설계를 위한 구조형상 최적설계 툴의 개발에 대하여 기술하였다. 항공기 날개의 익폭, 시위길이, 뒤제침 등의 형상과 스파, 리브의 위치를 설계변수로 선정하였다. 또한 이러한 설계변수를 고려한 날개의 격자 생성 툴을 구성하였다. 최적화 인터페이스는 DIAMOND/IPSAP 의 GUI 환경에서 개발되었으며, 최적화 알고리즘은 PSO(Particle Swarm Optimization)을 사용하여 유한요소 해석 결과를 이용하여 효과적으로 최적화를 수행할 수 있도록 구성하였다. 목적함수로는 구조해석 툴인 IPSAP 을 활용하여 응력해석에서의 최대 응력과 진동해석의 고유진동수 등을 활용하였다. 최종적으로 구조 해석툴, 최적화 알고리즘 및 격자 생성 툴을 연계하여 최적화 모듈인 DIAMOND/ASD 를 구성하였다. In this paper, development of optimal design tool for wing structure is described. Wing span, chord length, sweep back angle, position of spar, rib and thickness of each shell ware selected as design variables. At first, mesh generation tool of aircraft wing, which is tool for generating full meshes of aircraft wing, was developed. We developed optimization toolbox with PSO algorithm so that it can easily treat hundreds of simulation jobs in efficient way. IPSAP, which is structural analysis tool including vibration, stress, and buckling analysis module, is used for calculating object function. Finally, by integrating IPSAP, PSO algorithm and re-meshing tool, Aircraft optimization module was composed.
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항공기 날개 형상 최적화를 위한 distributed design의 적용
김태희(TaeHee Kim),최성임(Seongim Choi) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.5
Aircraft design is very difficult because aircraft is composed of many subsystems which are highly coupled. Therefore, aircraft design with decoupled analysis at subsystems is meaningless and it is important to perform an integrated analysis. Designers revise existing design methods or find a new design method for satisfying the complex design requirement, one of them is a Multidisciplinary Design Optimization(MDO) which is methodology that tries to slove those issues and many study is performed recently. A distributed design divides the aircraft system into system and subspace levels and distributes independent role to each discipline. Collaborative Optimization(CO) and Concurrent Sub-Space Optimization(CSSO) are kinds of distributed design which have different formulations and different characteristics. CSSO carries out system analysis and solves a series of sensitivity equations. Also CSSO contains concept of responsible coefficient and trade-off coefficient. In contrast, CO doesn’t has system analysis and sensitivity equation and uses concept of auxiliary variables and compatibility condition. In current study, we compare Collaborative Optimization(CO) and Concurrent Sub-Space Optimization(CSSO) methods about their advantages and weaknesses through their application to aircraft wing shape design problem.
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Optimum Design of Composite Wing Structure Using Bolted Joint Stress Field Model
장준환(Jun Hwan Jang),안상호(Sang Ho Ahn) Korean Society for Precision Engineering 2019 한국정밀공학회지 Vol.36 No.7
Major aerospace developers continue to push for new structural composite applications to reduce the environmental impact of greenhouse gas emissions, improve both aircraft performance and costs. In this study, the parts that carry the load in the regions where mechanical joints are applied, require whole processing to tighten and identify stress concentration points. In addition, failure modes caused by bearing and by-pass loads were set as the main design factors. Optimum sizing was performed through the application of factors taken into account in the buckling failure mode and production using the preliminary design analysis model of the composite wing structure. In the area where the fuselage is joined with the fuselage, bearing and bypass load were considered important design factors.
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김태희(T.H. Kim),권형일(H.I. Kwon),최성임(S.I Choi) 한국전산유체공학회 2012 한국전산유체공학회 학술대회논문집 Vol.2012 No.11
Collaborative optimization is a multi-level methodology for multidisciplinary optimization. The collaborative optimization does not require direct communication between each discipline and secures a disciplinary autonomy. But the collaborative optimization has problem at convergence of objective function and computational cost. In this paper, for better convergence, GA(Genetic Algorithm) is used as both system level optimizer and subspace level optimizer of the Collaborative optimization. In doing so, the performance of Collaborative Optimization is discussed by applying two example problems and aircraft wing design problem.
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