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Keywords: fluid-structure interaction, composite rocket nozzle, finite element modelling, ignition transient.

Summary

Contemporary solid rocket motor (SRM) nozzles have evolved into highly refined and optimised structures, capable of withstanding some of the most extreme conditions encountered in engineering. The characteristics of possible aeroelastic interaction between such nozzles during SRM ignition, and the subsequent effects of this interaction on the nozzle structure, have not been thoroughly investigated previously. The objective of this study therefore, was to conduct such an investigation, based on a hypothetical "ultra-simple" composite SRM nozzle design, featuring a three-dimensional spatially reinforced carbon-carbon integral throat, entrance and exit cone.

The numerically simulated response of this nozzle to dynamic pressure loading during motor start-up is generated using the advanced multiphysics code, ADINA [1]. A solids-based finite element model and a fluids-based finite element / finite volume model were constructed to represent the nozzle structure and the exhaust gas flow within the nozzle, respectively. The ignition transient pressure characteristic applied in the fluids model was obtained from the literature [2].

Two computational analyses were conducted using the coupled and uncoupled fluid-structure interaction solution schemes incorporated in the ADINA code. The simulations were established to represent the behaviour of the nozzle structure and exhaust flow during the first 0.3s of the ignition process, and involved solution iteration over 3000 time steps, of equal length.

Results predicting the velocity and pressure distributions of the fluid flow, and the displacement and stress behaviour of the nozzle are presented. Interpretation of these results suggests that the level of fluid-structure coupling that takes place between the nozzle and the exhaust gas flow field during motor ignition is small. In addition, dynamic stresses generated in the exit cone of the nozzle during this phase of operation are found to be negligible. Future work will seek to incorporate thermal loading effects in order to establish whether this consideration contributes to an increased level of domain coupling.

References

1: Automatic Dynamic Incremental Nonlinear Analysis (ADINA) Finite Element Analysis Software, Version 8.4, Copyright ADINA R&D, Inc., 2006.
2: W.A. Johnston, "Flow-Structural Analysis of the Ariane 5 Solid Rocket Motor during Ignition Transient", in "Proceedings of the AIAA 34th Aerospace Sciences Meeting and Exhibit", Reno, United States of America, 1996.

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Front Page Browse CCP CSETS CTR IJRT Other Authors Search Purchase Guide FAQ Contact us	Civil-Comp Proceedings ISSN 1759-3433 CCP: 88 PROCEEDINGS OF THE NINTH INTERNATIONAL CONFERENCE ON COMPUTATIONAL STRUCTURES TECHNOLOGY Edited by: B.H.V. Topping and M. Papadrakakis Paper 3 Simulation of Fluid-Structure Interaction Phenomena of a Composite Rocket Nozzle J.F.P. Pitot de la Beaujardiere¹, E.V. Morozov² and G. Bright¹ ¹Department of Mechanical Engineering, University of KwaZulu-Natal, South Africa ²School of Aerospace, Civil & Mechanical Engineering, The University of New South Wales, University College, Australian Defence Force Academy, Australia doi:10.4203/ccp.88.3 purchase the full-text of this paper Full Bibliographic Reference for this paper J.F.P. Pitot de la Beaujardiere, E.V. Morozov, G. Bright, "Simulation of Fluid-Structure Interaction Phenomena of a Composite Rocket Nozzle", in B.H.V. Topping, M. Papadrakakis, (Editors), "Proceedings of the Ninth International Conference on Computational Structures Technology", Civil-Comp Press, Stirlingshire, UK, Paper 3, 2008. doi:10.4203/ccp.88.3 Keywords: fluid-structure interaction, composite rocket nozzle, finite element modelling, ignition transient. Summary Contemporary solid rocket motor (SRM) nozzles have evolved into highly refined and optimised structures, capable of withstanding some of the most extreme conditions encountered in engineering. The characteristics of possible aeroelastic interaction between such nozzles during SRM ignition, and the subsequent effects of this interaction on the nozzle structure, have not been thoroughly investigated previously. The objective of this study therefore, was to conduct such an investigation, based on a hypothetical "ultra-simple" composite SRM nozzle design, featuring a three-dimensional spatially reinforced carbon-carbon integral throat, entrance and exit cone. The numerically simulated response of this nozzle to dynamic pressure loading during motor start-up is generated using the advanced multiphysics code, ADINA [1]. A solids-based finite element model and a fluids-based finite element / finite volume model were constructed to represent the nozzle structure and the exhaust gas flow within the nozzle, respectively. The ignition transient pressure characteristic applied in the fluids model was obtained from the literature [2]. Two computational analyses were conducted using the coupled and uncoupled fluid-structure interaction solution schemes incorporated in the ADINA code. The simulations were established to represent the behaviour of the nozzle structure and exhaust flow during the first 0.3s of the ignition process, and involved solution iteration over 3000 time steps, of equal length. Results predicting the velocity and pressure distributions of the fluid flow, and the displacement and stress behaviour of the nozzle are presented. Interpretation of these results suggests that the level of fluid-structure coupling that takes place between the nozzle and the exhaust gas flow field during motor ignition is small. In addition, dynamic stresses generated in the exit cone of the nozzle during this phase of operation are found to be negligible. Future work will seek to incorporate thermal loading effects in order to establish whether this consideration contributes to an increased level of domain coupling. References 1 Automatic Dynamic Incremental Nonlinear Analysis (ADINA) Finite Element Analysis Software, Version 8.4, Copyright ADINA R&D, Inc., 2006. 2 W.A. Johnston, "Flow-Structural Analysis of the Ariane 5 Solid Rocket Motor during Ignition Transient", in "Proceedings of the AIAA 34th Aerospace Sciences Meeting and Exhibit", Reno, United States of America, 1996. purchase the full-text of this paper (price £20) go to the previous paper go to the next paper return to the table of contents return to the book description purchase this book (price £145 +P&P)
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