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采用计算流体力学(CFD)数值模拟方法,研究战术导弹大迎角状态下涡破裂导致滚转力矩随迎角非线性增长引起舵面控制能力不足的现象。首先通过标准模型的数值分析,验证了所采用的CFD方法具有三角翼前缘涡破裂现象的捕捉能力;然后采用雷诺平均Navier-Stokes方程对某“++”字正常布局导弹构型(含弹翼、弹身、尾舵和整流罩等)进行了数值模拟,结果显示亚声速状态下滚转力矩在迎角大于20°时出现非线性增长,导致全动尾舵的滚转控制能力不足。通过分解各部件对滚转力矩的贡献,并分析流场结构,探明了该现象发生的流动机理,其主要原因是:随着迎角的增长,弹体迎风面的尾舵前缘涡首先发生破裂,导致其平衡诱导滚转力矩的作用被削弱。
The computational fluid dynamics (CFD) numerical simulation method is used to study the phenomenon that the controllability of the rudder surface caused by the vortex rupture caused by the non-linear growth of the angles of attack due to the vortex rupture at the high angle-of-attack state of the tactical missile is insufficient. Firstly, the numerical simulation of the standard model is used to verify that the adopted CFD method has the capability of capturing the vortex rupture at the delta front. Secondly, using the Reynolds-averaged Navier-Stokes equations, Including the winglet, body shell, tail rudder and fairing, etc.). The results show that the rolling torque in the sub-sonic state increases nonlinearly when the angle of attack is larger than 20 °, resulting in the roll control ability of the full-body rudder insufficient. By decomposing the contribution of each component to the rolling torque and analyzing the flow field structure, the flow mechanism of this phenomenon is proved. The main reason is that as the angle of attack increases, the leading edge vortex at the windward side of the projectile first Rupture, resulting in the balance of the role of inducing rolling torque is weakened.