Research on the kinetics of rock motion for a missile model with strake wings
-
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。Abstract: 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=0.6 and α=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 8 style and the total energy of aerodynamic force acting on the model is equal to zero during a period. 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.
-
Keywords:
- strake wing missile /
- rock /
- limit cycle /
- dynamic stability /
- moment of inertia
-
-
[1] ALLEN J M. Aerodynamics of an axisymmetric missile concept having cruciform strakes and in-line tail fins from mach 0.60 to 4.63[R]. NASA TM 2005-213541, 2005.
[2] KATZ J. Wing/vortex interactions and wing rock[J]. Progress in Aerospace Sciences, 1999, 35: 727-750.[2] 张涵信, 刘伟, 谢昱飞, 等. 后掠三角翼的摇滚及其动态演化问题[J]. 空气动力学学报, 2006, 24(1): 5-9. [3] 达兴亚, 赵忠良, 陶洋, 等. 窄条翼导弹模型摇滚特性试验研究[J]. 实验流体力学, 2012, 26(6): 40-44. [4] KONSTADINOPOULOS P, MOOK D T, NAYFEH A H. Subsonic wing rock of slender delta wings[J]. Journal of Aircraft, 1985, 22(3): 223-228. [5] KANDIL O A, SALMAN A A. Three-dimensionla simulation of slender delta wing rock and divergence[R]. AIAA-92-0280, 1992. [6] LIU W, ZHANG H, ZHAO H. Numerical simulation and physical characteristics analysis for slender wing rock[J]. Journal of Aircraft, 2006, 43(3): 858-861. [7] ARENA A, NELSON R. A discrete vortex model for prediction wing rock of slender wings[R]. AIAA-92-4497, 1992 [8] 达兴亚, 陶洋, 赵忠良. 基于预估校正和嵌套网格的虚拟飞行数值模拟[J]. 航空学报, 2012, 33(6)：977-983. [9] ROE P. Approximate Riemann solvers, parameter vectors, and difference schemes[J]. Journal of Computational Physics, 1981, 43(2): 357-372. [10] DUBUC L, et al. Solution of the unsteady Euler equations using an implicit dual-time method[J]. AIAA Journal, 1998, 36(8): 1417-1424. [11] SPALART P R, ALLMARAS S. A one-equation turbulence model for aerodynamic flows[R]. AIAA-92-0439, 1992. [12] NELSON R C, PELLETIER A. The unsteady aerodynamics of slender wings and aircraft undergoing large amplitude maneuvers[J]. Progress in Aerospace Sciences, 2003, 39: 185-248. [13] LIU Z L. Control and simulation investigation of wing rock phenomenon[D]. [PhD thesis]. Concordia University, Canada, 2004. [14] 荣臻, 邓学蓥, 王兵, 等. 前体涡诱导双极限环摇滚流动特性的实验研究[J]. 实验流体力学, 2010, 24(3):19-24.
计量
- 文章访问数: 305
- HTML全文浏览量: 6
- PDF下载量: 903
下载:
