CAJ | 학술논문

采用基于N-S方程的计算流体力学(CFD)技术和基于有限元技术的结构力学(CSM)分析方法,结合动网格技术,发展一种求解大长细比弹箭静气动弹性问题的直接耦合方法.以某鸭式布局大长细比导弹(火箭)为算例,研究弹性变形对全弹气动特性的影响.结果表明:相对于刚体模型,全弹轴向力和法向力降低,压力中心明显前移,气动设计中应加以考虑.
채용기우N-S방정적계산류체역학(CFD)기술화기우유한원기술적결구역학(CSM)분석방법,결합동망격기술,발전일충구해대장세비탄전정기동탄성문제적직접우합방법.이모압식포국대장세비도탄(화전)위산례,연구탄성변형대전탄기동특성적영향.결과표명:상대우강체모형,전탄축향력화법향력강저,압력중심명현전이,기동설계중응가이고필.
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.