CFD/CSD与机弹分离的耦合模拟技术  

CFD / CSD and Missile Separation Integrative Simulation Method

作　　者：王芳[1,2] 龚军锋[1,2] 

机构地区：[1]西北工业大学无人机研究所,西安710065 [2]西安爱生技术集团公司,西安710065

出　　处：《弹箭与制导学报》2013年第6期193-196,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：机弹分离模拟的刚性模型不能反映机翼弹性变形的影响。在分别建立并验证的CFD/CSD气弹模拟方法和机弹分离模拟方法的基础上,通过流场网格更新环节同时反映机翼结构的变形运动和弹体的六自由度运动对流场的相互影响。CFD与CSD的求解方法可计及真实飞行器流场的非线性和结构的非线性。基于各主控方程的时间域积分,交错时间推进获得整个耦合系统的响应,建立了一套CFD/CSD与机弹分离耦合求解的时域仿真系统。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.

关 键 词：CFD CSD 机弹分离 动网格 耦合求解 气弹 非线性 

分 类 号：TJ760.36[兵器科学与技术—武器系统与运用工程]