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Inventi Impact - Aerospace Engineering

Articles

  • Inventi:eae/60/14
    NUMERICAL CALCULATION OF EFFECT OF ELASTIC DEFORMATION ON AERODYNAMIC CHARACTERISTICS OF A ROCKET
    Laith K Abbas, Dongyang Chen, Xiaoting Rui

    The application and workflow of Computational Fluid Dynamics (CFD)/Computational Structure Dynamics (CSD) on solving the static aeroelastic problem of a slender rocket are introduced. To predict static aeroelastic behavior accurately, two-way coupling and inertia relief methods are used to calculate the static deformations and aerodynamic characteristics of the deformed rocket. The aerodynamic coefficients of rigid rocket are computed firstly and compared with the experimental data, which verified the accuracy of CFD output.The results of the analysis for elastic rocket in the nonspinning and spinning states are compared with the rigid ones. The results highlight that the rocket deformation aspects are decided by the normal force distribution along the rocket length. Rocket deformation becomes larger with increasing the flight angle of attack. Drag and lift force coefficients decrease and pitching moment coefficients increase due to rocket deformations, center of pressure location forwards, and stability of the rockets decreases. Accordingly, the flight trajectory may be affected by the change of these aerodynamic coefficients and stability.

    How to Cite this Article
    CC Compliant Citation: Laith K. Abbas, Dongyang Chen, and Xiaoting Rui, “Numerical Calculation of Effect of Elastic Deformation on Aerodynamic Characteristics of a Rocket,” International Journal of Aerospace Engineering, vol. 2014, Article ID 478534, 11 pages, 2014. doi:10.1155/2014/478534. Copyright © 2014 Laith K. Abbas et al. This is an open access article distributed under the Creative Commons Attribution License (http://creativecommons.org/licenses/by/3.0/), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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