窄条翼导弹模型摇滚运动动力学特性研究  

Research on the kinetics of rock motion for a missile model with strake wings

作　　者：达兴亚[1] 周为群[1] 赵忠良[1] 陶洋[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622661

出　　处：《空气动力学学报》2014年第2期154-158,共5页Acta Aerodynamica Sinica

基　　金：自然科学基金(11372336)

摘　　要：利用NS方程和飞行力学方程耦合的数值模拟,研究分析了窄条翼导弹模型摇滚运动的动力学特性和产生机理。控制方程为URANS和刚体单自由度转动方程,计算取Roe格式、SA湍流模型、双时间步法,气动/运动耦合采用双时间步三阶Adams预估校正法。计算Ma=0.6,α=35°,模型进入极限环振荡,振幅10.14°,周期20Hz,与风洞试验结果吻合较好。受力分析表明力矩迟滞曲线为双8环,中间为不稳定环,两侧为稳定环;模型的动不稳定性是由迎风尾舵引起,背风尾舵不能提供足够的动稳定性,导致模型丧失滚转阻尼,最终进入等幅等周期的极限环振荡;计算证实,该极限环是稳定的,模型在任意初始状态或微扰动作用下都将进入该极限环振荡。计算结果还表明,在非定常效应较强时,转动惯量对摇滚振幅影响不大,对频率影响明显。Numerical computations of coupled Navier-Stokes equations and flight mechanic equations are conducted to research and analyse the kinetic characteristics and mechanism of rock motion for a missile model with strake wings.Control equations are unsteady RANS and one-DOF rigid-body roll equation.Roe scheme,S-A turbulence model and dual time stepping techniques are selected to solve the URANS,and 3rd Adams prediction-correction method is used to couple the aerodynamic and flight mechanic computations. Calculation at Ma=0.6andα =35°resulted in a Limited Cycle Oscillation（LCO）with amplitude of 10.14° and frequency of 20Hz which agree with wind tunnel test.The hysteresis loop of rolling moment coefficient is double 8style and the total energy of aerodynamic force acting on the model is equal to zero during aperiod.Forces acting on different components show that the unstability is caused by the windward fins and cannot be compensated by the leeward fins,resulting in the loss of roll damping and the limit cycle oscillation. Computations validate that this LCO is stable,meaning that the model would enter into it by disturbances.It is also shown that the moment of inertia has little effect on the rock amplitude while has a significant effect on the frequency when the unsteady effect is strong.

关 键 词：窄条翼导弹 摇滚 极限环 动稳定性 转动惯量 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]