목적 공력특성 달성을 위한 플루트 노즐 전산설계

다국어 초록 (Multilingual Abstract)

As a preliminary design study to achieve target aerodynamic performance, this work was conducted on an original nozzle with 9 flutes in order to design a fluted nozzle with 12 flutes. The thrust and rolling moment of the nozzle with 12 flutes were analyzed using a CFD code according to the depth and rotation angle of the flutes. Based on this, a fluted nozzle with 12 flutes was optimized to yield the same thrust as that of the original nozzle with 9 flutes. The response surface method was applied for shape optimization of the fluted nozzle and design variables were selected to determine the depth angle and rotation angle of the flutes. An optimized shape that led to a thrust as strong as that of the original nozzle was obtained

참고문헌 (Reference)

1 서지한, "초소형 노즐 유동장에 관한 수치적 연구" 한국전산유체공학회 12 (12): 38-43, 2007

2 김영목, "로켓 배기플룸에 관한 3차원 수치해석" 71-76, 1999

3 최정열, "로켓 노즐 유동의 열/화학적 특징 및 해석 기법" 144-148, 2001

4 Mermagen, W.H, "Yawsonde tests of 2.75-inch MK66 mod 1 rocket" 1981

5 Akira, K, "Solid propellant microthruster using Laser-Assisted combustion" AIAA 2004

6 Steven, C.C, "Numerical Methods for Engineers" McGraw-Hill 1999

7 Bentley, R, "Next generation 2.75-inch rocket propulsion" 2001

8 Hawley, E, "MK 66 rocket motor/helicopter compatibility program" Naval Surface Warfare Center 2003

9 Dahlke, C.W, "Hydra 70 MK66 aerodynamics and roll analysis"

10 "FLUENT 6.3 User's Guide"

11 Hawley, E, "Advanced propulsion concepts for the hydra-70 rocket system" Naval Surface Warfare Center 2003