Journal of Projectiles, Rockets, Missiles and Guidance >
Study of Effect of Elastic Deformation on Aerodynamic Characteristics of a Slender Missile (Rocket)
Received date: 2009-06-03
Online published: 2025-05-28
A direct fluid-structure coupling method was presented for solving the static aeroelastic problem of a slender missile (rocket). In this method, the compressible flow was modeled using the N-S equations on a deformable mesh, and the structure mechanical characteristics were solved by a finite element method. With this approach, aerodynamic characteristic of a canard-layout slender missile was studied. The results indicate that the axial force and the normal force decrease, and the center of pressure move forward obviously comparing with those of the rigid model. Thus, elastic deformation should be considered during designing a slender missile.
Key words： static aeroelasticity; CFD; slender missile; direct coupling method
LIU Wangang , ZHANG Weiwei , JIANG Shengju , ZHAO Zhijun , ZHU Hongxing . Study of Effect of Elastic Deformation on Aerodynamic Characteristics of a Slender Missile (Rocket)[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2010 , 30(2) : 177 -180 . DOI: 10.15892/j.cnki.djzdxb.2010.02.032
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