피칭운동을 고려한 우주발사체 형상의 천음속 비정상 유동해석

다국어 초록 (Multilingual Abstract)

In this study, steady and unsteady aerodynamic analyses of a huge rocket configuration have been conducted in a transonic flow region. The launch vehicle structural response are coupled with the transonic flow state transitions at the nose of the payload fairing. Before performing the coupled fluid-structure transonic aeroealstic simulations transonic aerodynamic characteristics are investigated for the pitching motions of the rocket at finite angle-of-attack. An unsteady CFD analysis method with a moving grid technique based on the Reynolds-averaged Navier-Stokes equations with the k-w SST transition turbulence model is applied to accurately predict the transonic loads of the rocket at pitching motion. It is shown that the fluctuating amplitude of the lateral aerodynamic loads imposed on the rocket due to the pitching motion can be significantly increased in the transonic flow region.

참고문헌 (Reference)

1 김동현, "충격파 및 유동점성 효과를 고려한 항공기 날개-동체 형상에 대한 공탄성 응답" 한국항공우주학회 37 (37): 984-991, 2009

2 Azevedo, J.L.F, "Transonic Aeroelastic Analysis of Launch Vehicle Configurations" NASA CR-4186 1988

3 Graham, F.J, "Static Pressure Distribution on a 0.07 Scale Aerodynamic Model of the Atlas-Able IV at Free-Stream Mach Numbers from 0.50 to 1.60"

4 "Flutter, Buzz, and Divergence"

5 "FLUENT 6.3 User's Guide" Fluent 2006

6 Bisplinghoff, R. L, "Aeroelasticity" John Wiley & Sons 1962

7 김동현, "3차원 축류압축기 블레이드의 유체유발진동 해석" 한국소음진동공학회 19 (19): 551-559, 2009