지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학술대회자료
- 저자정보
- 발행연도
- 2014.10
- 수록면
- 193 - 198 (6page)
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초록· 키워드
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In this paper, the prediction of the separation trajectory for a Two-Stage-To-Orbit (TSTO) space launch vehicle has been numerically simulated by using an aerodynamic database based on steady state analysis. The steady flow simulations around the launch vehicle have been made by using a 3-D RANS flow solver based on unstructured mesh. Calculations were made for the wind-tunnel experiment model of the LGBB TSTO vehicle configuration on steady state conditions. An overset mesh technique was adopted to handle the relative distance between an orbiter and a booster. To construct aerodynamic database, the calculation cases considering the relative positions were obtained from an improved distributed hypercube sampling method. An artificial neural network (ANN) was applied to construct the interpolation functions representing the relations between the relative position of two vehicles and the aerodynamic forces. The separation trajectory for the TSTO launch vehicle was predicted using six-degree-of-freedom equation of motion based on the interpolation functions. The predicted separation trajectory wasfound in good agreement with the experimental results.
목차
Abstract
1. Introduction
2. Numerical Method
3. Model Description
4. Computational mesh
5. Results and Discussion
6. Conclusions
7. References
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