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
- 35 - 40 (6page)
이용수
초록· 키워드
오류제보하기
Numerical simulations are performed to predict the rotation rate of the free-rolling tail of a canard-tail missile configuration. A set of four tail fins placed around a cylindrical missile body is modeled to free-roll with respect to the axial axis of the body. Aerodynamic forces and moments acting on the fin set are computed in a time-accurate manner and the resulting rolling motion of the fin set is updated in real time using the Dynamic Fluid Body Interaction (DFBI) technique. The test condition spans the Mach number of 1.05, 1.2, 1.6, body roll angle of 22.5 degrees and angle of attack up to 15 degrees, and canard roll deflection angle of 5 degrees. It is observed that the rotation rate decrease with increasing angle of attack, which agrees well with the wind tunnel test results. The dynamics of the rotational motion and the aerodynamic roll moment are analyzed to find the physics governing the rotation rate.
목차
Abstract
1. Introduction
2. Numerical Method
3. Results
4. Conclusions
5. References
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