한국전산유체공학회:학술대회논문집
- 한국전산유체공학회 2000년도 추계 학술대회논문집
- /
- Pages.46-53
- /
- 2000
반응면 기법을 이용한 발사체 선두부 다점 최적설계
A Multi-Point Design Optimization of a Space Launcher Nose Shapes Using Response Surface Method
- 발행 : 2000.10.01
초록
To improve the performance at all design points, multi-point optimization method is implemented for the nose fairing shape design of space launcher. The response surface method is used to effectively reduce the huge computational loads during the optimization process. The drag is selected as the objective function, and the surface heat transfer characteristics, and the internal volume of the nose fairing ate considered as design constraints. Full Wavier-Stokes equations are selected as governing equations. Two points drag minimization, and two points drag / heat flux optimization were successfully performed and configurations which have good performance for the wide operation range were derived. By considering three design points, the space launcher shape which undergoes the least drag during whole flight mission was designed. For all the design cases, the constructed response surfaces show good confidence level with only 23 design points with the proper stretching of the design space.
키워드