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Civil-Comp Proceedings
ISSN 1759-3433 CCP: 76
PROCEEDINGS OF THE THIRD INTERNATIONAL CONFERENCE ON ENGINEERING COMPUTATIONAL TECHNOLOGY Edited by: B.H.V. Topping and Z. Bittnar
Paper 45
Dynamic Analysis of Strap-on Rocket Boosters using a Parallelized Chimera Grid Scheme S.-H. Ko+, S. Choi+, C. Kim+, O.-H. Rho+ and J.-J. Park*
+Department of Aerospace Engineering, Seoul National University, Korea
S.-H. Ko, S. Choi, C. Kim, O.-H. Rho, J.-J. Park, "Dynamic Analysis of Strap-on Rocket Boosters using a Parallelized Chimera Grid Scheme", in B.H.V. Topping, Z. Bittnar, (Editors), "Proceedings of the Third International Conference on Engineering Computational Technology", Civil-Comp Press, Stirlingshire, UK, Paper 45, 2002. doi:10.4203/ccp.76.45
Keywords: Chimera overset grid, parallel computating, separation dynamics, strap-on booster, relative motion, Titan-IV.Summary
The separation motions of boosters attached on the various three-stage rockets are
analysed by using 3-D compressible unsteady Navier-Stokes flow solver and rigid
body dynamics. For the governing equations, six degree-of-freedom rigid body
equations of motion are integrated into Navier-Stokes solution procedure to
determine the aerodynamic-dynamic coupled motions. A Chimera overset grid
technique is adopted for the calculation of the present configuration and grid around
the core rocket is composed of 3 zones to represent fins in the core rocket. Flow
solver is parallelized to reduce the calculation time, and an efficient parallelization
algorithm for Chimera grid technique is proposed. AUSMPW+ scheme is used for
the spatial discretization and LU-SGS for the time integration. The developed flow
solver is validated by comparing the computed results with wind tunnel data around
the Titan-IV launch vehicle, and applied to the various three-stage rockets.
From the analyses, booster trajectories are predicted and aerodynamic characteristics around the vehicle at each time interval are examined at various separation condition. In addition, additional jettisoning forces and moments needed for a safe separation are examined. As a result, H-II, the Japanese launch vehicle, had a safe separation of boosters in free separation case as shown in Figure 45.1. However, in the free separation case of KSR-I, the Korean sounding rocket, detached boosters collide with core rocket in about 0.2 sec after the separation as shown in Figure 45.2. So, additional jettisoning forces and moments are needed to ensure the safe separation of strap-on boosters and the result is shown in Figure 45.3.
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