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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
*Korea Aerospace Research Institute, Yusung, Korea Full Bibliographic Reference for this paper
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.
Figure 45.1:
A Free Separation of H-II
(Left: At The Initial Stage; Right: 0.5 sec After The Separation)
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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.
Figure 45.2:
A Free Separation of KSR-I
(Left: At The Initial Stage; Right: 0.2 sec After The Separation)
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Figure 45.3:
A Free Separation of KSR-I
(Left: At The Initial Stage; Right: 0.3 sec After The Separation)
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