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
- 2012.5
- 수록면
- 601 - 611 (11page)
이용수
초록· 키워드
오류제보하기
The study of stage separation and abort simulation has always been important in the development of next-generation launch vehicles. In the present study, numerical simulation of stage separation of two-stage reusable launch vehicles was made by using a two-dimensional viscous flow solver on unstructured meshes. Aerodynamic data were obtained for a matrix of longitudinal and vertical positions in the supersonic (Mach number 3) and hypersonic (Mach number 6) speeds. For these simulation, the Langley Glide-Back Booster (LGBB) configuration in a beLLy-to-belly bimese arrangement was used. The present study was conducted to investigate the interference aerodynamic characteristics and to study the proximity flow environment. The results showed that complex bow shock interactions have an impact on the proximity aerodynamic characteristics and the stability of the vehicle during the stage separation.
목차
1. 서론
2. 지배방정식 및 수치해석기법
3. 결과 및 고찰
4. 결론
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UCI(KEPA) : I410-ECN-0101-2013-422-002848756