基于CFD的带控制舵导弹的动导数计算  

Predictions of dynamic damping coefficients of basic finner based on CFD

作　　者：陶洋[1] 范召林[1] 赵忠良[1] 

机构地区：[1]中国空气动力研究与发展中心高速空气动力研究所,绵阳621000

出　　处：《航空动力学报》2010年第1期102-106,共5页Journal of Aerospace Power

基　　金：国际科技合作项目(2007DFA70880);国家863项目(2007AA042129)

摘　　要：介绍了基于计算流体动力学(CFD)的阻尼导数预测方法以及其在复杂带控制舵导弹外形的俯仰/滚转阻尼导数预测中的应用.方法采用求解三维非定常ALE(arbitrary Lagrangian-Eulerian)形式RANS(Reynolds-averaged Navier-Stokes)方程加湍流模型的方法得到模型强迫运动的气动力时间历程,再通过绕模型非定常运动过程得到的气动力迟滞曲线计算得到俯仰及滚转阻尼导数.为了验证采用数值方法的正确性,针对基本带翼导弹外形,采用强迫模型按正弦形式振动,计算得到了超声速范围内马赫数从1.5到2.5的俯仰及滚转稳定性参数,通过与风洞试验及弹道数据结果的比较发现,两者吻合较好.A method of predicting pitch and roll damping derivatives of missile geometries with fins using an unsteady RANS （Reynolds-averaged Navier-Stokes） solver was presented. A three-dimensional structured RANS solver based on arbitrary Lagrangian-Eulerian （ALE） formulation with a dynamically deforming mesh algorithm was used and validated by the wind tunnel and ballistic range data available in the literature. Roll and pitch damping derivatives were calculated from load history of the unsteady flow around the model. A standard research configuration, known as the basic finner,was studied under forced pitching and rolling conditions. Pitching and rolling motions with oscillation were analyzed at supersonic Mach numbers ranging from 1.5 to 2.5. Predicted results show good agreement with the available wind tunnel data.

关 键 词：基本带翼导弹 俯仰阻尼导数 滚转阻尼导数 非定常流动 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]