掠飞末敏弹耦合运动动导数计算
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摘要
以新型掠飞末敏弹为研究对象,提出了基于欧拉转动定理和滑移网格技术的复杂角运动模拟方法,利用著名的罗德里格斯转换矩阵插值求得弹箭在每个时间步的角速度修正值,并指定给球形滑移网格区。通过对非定常气动参数进行求解辨识,分析了不同马赫数下掠飞末敏弹滚转运动对其俯仰组合动导数和升力系数动导数的影响规律。结果表明:所提角运动模拟方法可有效消除姿态角计算的累积误差,实现对弹箭任意给定角运动的准确模拟;弹箭滚转运动对俯仰组合导数和升力系数动导数的辨识结果均存在显著影响,在进行弹箭动导数计算和稳定性分析时需充分考虑俯仰耦合效应的影响。
A novel swept flight terminal sensitive projectile was taken as a computation object,and the method to deal with simulation of the complex angular motion based on the Euler rotation theorem and a spherical sliding meshing technique was proposed. The modification value of the projectile's angular velocity at each time step was interpolated out through applying the Rodriguez transformation matrix,and it was further allocated to the sliding meshing zone. Based on the method,the influences on pitching combination dynamic derivatives and lift coefficients under various Mach numbers made by the projectile' s rolling motion were analyzed after solving and identifying the unsteady aerodynamic parameters. Results indicate that: the proposed method can eliminate the accumulative errors in the calculation of attitude angles effectively and can realize the accurate simulation under arbitrary given angular motion; the projectile's rolling motion generate significant influences on the identification results of pitching combination dynamic derivatives and lift coefficients,and the influence of the pitching coupled effect should be taken into account in the process of calculating the projectile's pitching motion and stability analysis.
A novel swept flight terminal sensitive projectile was taken as a computation object,and the method to deal with simulation of the complex angular motion based on the Euler rotation theorem and a spherical sliding meshing technique was proposed. The modification value of the projectile's angular velocity at each time step was interpolated out through applying the Rodriguez transformation matrix,and it was further allocated to the sliding meshing zone. Based on the method,the influences on pitching combination dynamic derivatives and lift coefficients under various Mach numbers made by the projectile' s rolling motion were analyzed after solving and identifying the unsteady aerodynamic parameters. Results indicate that: the proposed method can eliminate the accumulative errors in the calculation of attitude angles effectively and can realize the accurate simulation under arbitrary given angular motion; the projectile's rolling motion generate significant influences on the identification results of pitching combination dynamic derivatives and lift coefficients,and the influence of the pitching coupled effect should be taken into account in the process of calculating the projectile's pitching motion and stability analysis.
引文
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[2]赵博博,刘荣忠,郭锐,等.新型掠飞末敏弹的捕获概率分析[J].兵工学报,2016,37(2):232-238.ZHAO Bobo,LIU Rongzhong,GUO Rui,et al.Research on acquisition probability of a novel hedgehopping overhead attack projectile[J].Acta Armamentarii,2016,37(2):232-238.(in Chinese)
[3]陈亮,刘荣忠,郭锐,等.扭曲尾翼弹箭气动外形多目标优化[J].兵工学报,2016,37(7):1187-1193.CHEN Liang,LIU Rongzhong,GUO Rui,et al.Multiobjective optimization on the aerodynamic shape of the projectile with twisted empennages[J].Acta Armamentarii,2016,37(7):1187-1193.(in Chinese)
[4]郭东,徐敏,陈士橹.基于网格速度法的非定常流场模拟和动导数计算[J].西北工业大学学报,2012,30(5):784-788.GUO Dong,XU Min,CHEN Shilu.An effective computation method based on field velocity approach for unsteady flow simulation and obtaining dynamic derivatives[J].Journal of Northwestern Polytechnical University,2012,30(5):784-788.(in Chinese)
[5]米百刚,詹浩,王斑.基于刚性动网格技术的动导数数值模拟[J].航空动力学报,2014,29(11):2659-2664.MI Baigang,ZHAN Hao,WANG Ban.Numerical simulation of dynamic derivatives based on rigid moving mesh technique[J].Journal of Aviation Power,2014,29(11):2659-2664.(in Chinese)
[6]邓帆,陈少松,王学德.栅格翼翼身组合体超声速滚转阻尼特性[J].弹道学报,2011,23(3):58-62.DENG Fan,CHEN Shaosong,WANG Xuede.Roll damping characteristics for missile with grid fins at supersonic speed[J].Journal of Ballistics,2011,23(3):58-62.(in Chinese)
[7]史志伟,黄达,吴根兴,等.耦合运动非定常气动模型对飞机飞行特性仿真的影响[J].航空学报,2008,29(6):1424-1428.SHI Zhiwei,HUANG Da,WU Genxing,et al.Effects of coupled motion unsteady aerodynamic model on flight characteristics simulation of aircraft[J].Acta Aeronautica et Astronautica Sinica,2008,29(6):1424-1428.(in Chinese)
[8]吴金华,孙海生,沈志洪,等.旋转流场下的振荡动导数试验技术研究[J].实验流体力学,2014,28(4):54-58.WU Jinhua,SUN Haisheng,SHEN Zhihong,et al.Investigation of test technique of oscillatory dynamic derivative in rotational flow field[J].Journal of Experiments in Fluid Mechanics,2014,28(4):54-58.(in Chinese)
[9]郭正.包含运动边界的多体非定常流场数值模拟方法研究[D].长沙:国防科技大学,2002.GUO Zheng.Numerical simulation technique research for unsteady multi-body flowfeild involving moving boundaries[D].Changsha:National University of Defense Technology,2002.(in Chinese)
[10]Wang X L.Computational fluid dynamics predictions of stability derivatives for airship[J].Journal of Aircraft,2012,49(3):933-940.
[11]Ronch A D,Vallespin D,Ghoreyshi M,et al.Computation of dynamic derivatives using CFD[C]//Proceedings of 28th AIAA Applied Aerodynamics Conference,2010.
[12]Shantz I,Groves R T.Dynamic and static stability measurements of the basic finner at supersonic speeds[R].U.S Naval Ordnance Laboratory White OAK,Maryland,1960.
[13]Moore F G,Swanson R C.Dynamic derivatives for missile configurations to Mach number three[J].Journal of Spacecraft and Rockets,1978,15(2):65-66.