Journal of Projectiles, Rockets, Missiles and Guidance >
CFD/CSD and Missile Separation Integrative Simulation Method
Received date: 2013-02-22
Online published: 2025-05-26
Using rigid model in missile separate simulation can not embody the influence of wing's elastic deformation. In this paper, the loose CFD/CSD algorithm of aeroelasticity was established and validated, then AEDC wind tunnel test model was computed. The result of solution conforms with the wind tunnel test result. Through flow-field dynamic mesh updating, the wing's deformation and the missile's 6-dof movement were simultaneity considered. In this method, the aircraft's flow-field nonlinear and structural nonlinear were considered. Time-marching simulation's method was applied in CSD, CFD and 6-dof Newton Euler solver, then the whole coupling system's response was obtained.
Key words： CFD/CSD; missile separation; dynamic mesh; coupling solution; aeroelasticity; nonlinear
WANG Fang , GONG Junfeng . CFD/CSD and Missile Separation Integrative Simulation Method[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2013 , 33(6) : 193 -196 . DOI: 10.15892/j.cnki.djzdxb.2013.06.016
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