基于嵌套网格的超声速子母弹分离数值分析
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摘要
为研究超声速下子母弹分离流场和气动特性,采用嵌套网格技术和有限体积法离散求解三维黏性可压缩流的Navier-Stokes方程,同时建立6自由度刚体的运动学方程与动力学方程。将6自由度刚体运动与计算流体力学耦合,数值模拟超声速下子母弹分离过程,研究子母弹分离过程的流场特性和子弹初始分离状态(如子母弹初始分离时子弹飞行速度及其初始姿态角等)对其分离过程的影响。结果表明:嵌套网格技术可以很好地模拟超声速下子母弹分离的复杂干扰流场;超声速条件下,子弹脱开母弹时的飞行速度和子母弹初始分离速度越大,分离攻角越小,各个弹体之间可以更安全快速地分离。
To study the separation flow field and aerodynamic characteristics of supersonic submunition,the nested grid technique and the finite volume method are used to discretize Navier-Stokes equations of three-dimensional viscous compressible flow,and simultaneously solve the kinematic equations and dynamics equations of 6-degree-of-freedom( DOF) rigid body. The 6-DOF rigid body motion is coupled with computational fluid dynamics( CFD) to simulate the separation process of submunition at supersonic speed. The characteristics of flow field in the separation of submunition and its initial separation state( such as initial flight velocity and initial attitude angle,etc) were analyzed. The results show that the nested grid technique can be well used to simulate the complex interferent flow field of supersonic submunition. Under the supersonic separation condition,the higher the initial flight speed is when a submunition is removed from cluster munition,the smaller the separation angle of attack is,and the submunition can be separated more quickly and safely.
To study the separation flow field and aerodynamic characteristics of supersonic submunition,the nested grid technique and the finite volume method are used to discretize Navier-Stokes equations of three-dimensional viscous compressible flow,and simultaneously solve the kinematic equations and dynamics equations of 6-degree-of-freedom( DOF) rigid body. The 6-DOF rigid body motion is coupled with computational fluid dynamics( CFD) to simulate the separation process of submunition at supersonic speed. The characteristics of flow field in the separation of submunition and its initial separation state( such as initial flight velocity and initial attitude angle,etc) were analyzed. The results show that the nested grid technique can be well used to simulate the complex interferent flow field of supersonic submunition. Under the supersonic separation condition,the higher the initial flight speed is when a submunition is removed from cluster munition,the smaller the separation angle of attack is,and the submunition can be separated more quickly and safely.
引文
[1]陶如意,张丁山,赵润翔,等.超声速子母弹分离干扰流场数值模拟与试验研究[J].空气动力学学报,2010,28(3):310-315.TAO R Y,ZHANG D S,ZHAO R X,et al. Numerical and experimental study of interference flow field on separation of supersonic cluster munition[J]. Journal of Aerodynamics,2010,28(3):310-315.(in Chinese)
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[12]王金龙,王浩,陶如意,等.子母弹不同舱段分离流场特性及运动特性研究[J].空气动力学报,2016,34(4):490-496.WANG J L,WANG H,TAO R Y,et al. Themoment characteristics analysis of interference flow field on the separation of multibay cluster munition[J]. Acta Aerodynamica Sinica,2016,34(4):490-496.(in Chinese)
[13]陶如意,张丁山,赵润祥,等.超声速子母弹分离干扰流场数值模拟与试验研究[J].空气动力学学报,2010,28(3):310-315.TAO R Y,ZHANG D S,ZHAO R X,et al. Numerical and experimental study of interference flow field on separation of supersonic cluster munition[J]. Acta Aerodynamica Sinica,2010,28(3):310-315.(in Chinese)
[14]赵承庆,姜毅.气体射流动力学[M].北京:北京理工大学出版社,1998:30-35.ZHAO C Q,JIANG Y. The kinetics of gas jet[M]. Beijing:Beijing Institute of Technology Press,1998:30-35.(in Chinese)
[15]陈永辉,王强,朴明波.湍流模型的发展及其研究现状[J].能源与环境,2009(2):4-6.CHEN Y H,WANG Q,PU M B. Development and research status of turbulence model[J]. Energy and Environment,2009(2):4-6.(in Chinese)
[16] WU Q,ZHAO Q J,WANG Q. Highly-efficient aerodynamic option design of rotor airfoil using viscous adjoint method[J].Transactions of Nanjing University of Aeronautics&Astronautics,2017,34(2):134-142.
[17]贾沛然,沈为异.弹道导弹弹道学[M].长沙:国防科技大学出版社,1980.JIA P R,SHEN W Y. Ballistic missile ballistics[M]. Changsha:National University of Defense Technology Press,1980.(in Chinese)
[18] POPE S P. Turbulent flows[M]. Cambridge,UK:Cambridge University Press,2000.
[19] THOMAS J P,DOWELL E H,HALL K C. Nonlinear inviscid aerodynamic effects on transonic divergence,flutter,and limitcycle oscillations[J]. AIAA Journal,2002,40(4):638-646.
[2]黄凯.子母弹抛撒过程射流流场对子弹运动的影响[D].南京:南京理工大学,2015:8-11.HUANG K. The jet flow field of submunition dispersal process and its influence on the projectile motion[D]. Nanjing:Nanjing University of Science and Technology,2015:8-11.(in Chinese)
[3]林靖明,安复兴,于德滨.母弹激波对子弹气动特性影响的研究[J].兵工学报,2000,21(4):334-337.LIN J M,AN F X,YU D B. Shock effects from the dispenser on the aerodynamic characteristics of submunitions[J]. Acta Armamentarii,2000,21(4):334-337.(in Chinese)
[4] STALMAEH C J,ROMERO S. Dynamie tests of a submissile dispensing system in a supersonic wind tunnel[C]∥Proceedings of the 11th AIAA Aerodynamic Testing Conference. Reno,NV,US:AIAA,1980:0452.
[5] RIZK M,JOLLY B. Aerodynamic simulation of bodies with moving components using CFD overset gird methods[C]∥Proceedings of the 44th AIAA Aerospace Sciences Meeting&Exhibit 2006.Reno,NV,US:AIAA,2006:1252.
[6] BHANGE N P,SEN A,GHOSH A K. Technique to improve precision of kinetic energy projectiles through motion study[C]∥Proceedings of Atmospheric Flight Mechanics Conference. Chicago,IL,US:AIAA,2009:5720.
[7] WOODEN P A,BROOKS W,JUBARAJ S B. Calibrating CFD predictions for use in multiple store separation analysis[C]∥Proceedings of the 36th AIAA Aerospace Sciences Meeting&Exhibit.Reno,NV,US:AIAA,1998:0754.
[8] PERKINS S C,DILLENIUS M F E. Supersonic submunition aerodynamics during dispense[C]∥Proceedings of the 26th Aerospace Sciences Meeting. Reno,NV,US:AIAA,1988:0335.
[9] CAVALLO P,LEE R,HOSANGADI A. Simulation of weapons bay separation flow fields using unstructured grids[C]∥Proceedings of the 19th Applied Aerodynamics Conference. Norfolk,VA,US:AIAA,1999:33412.
[10]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:国防科学技术大学,2002:4-20.GUO Z. Study on numerical simulation of multibody unsteady flow field with motion boundary[D]. Changsha:National University of Defense Technology,2002:4-20.(in Chinese)
[11]张玉东,纪楚群.子母弹分离非定常气动特性数值模拟[C]∥近代空气动力学研讨会论文集.北京:中国宇航出版社,2005:333-338.ZHANG Y D,JI C Q. Numerical simulation of the unsteady aerodynamic characteristics of the submunition separation[C]∥Proceedings of Modern Aerodynamics Symposium. Beijing:China Astonautic Publishing House,2005:333-338.(in Chinese)
[12]王金龙,王浩,陶如意,等.子母弹不同舱段分离流场特性及运动特性研究[J].空气动力学报,2016,34(4):490-496.WANG J L,WANG H,TAO R Y,et al. Themoment characteristics analysis of interference flow field on the separation of multibay cluster munition[J]. Acta Aerodynamica Sinica,2016,34(4):490-496.(in Chinese)
[13]陶如意,张丁山,赵润祥,等.超声速子母弹分离干扰流场数值模拟与试验研究[J].空气动力学学报,2010,28(3):310-315.TAO R Y,ZHANG D S,ZHAO R X,et al. Numerical and experimental study of interference flow field on separation of supersonic cluster munition[J]. Acta Aerodynamica Sinica,2010,28(3):310-315.(in Chinese)
[14]赵承庆,姜毅.气体射流动力学[M].北京:北京理工大学出版社,1998:30-35.ZHAO C Q,JIANG Y. The kinetics of gas jet[M]. Beijing:Beijing Institute of Technology Press,1998:30-35.(in Chinese)
[15]陈永辉,王强,朴明波.湍流模型的发展及其研究现状[J].能源与环境,2009(2):4-6.CHEN Y H,WANG Q,PU M B. Development and research status of turbulence model[J]. Energy and Environment,2009(2):4-6.(in Chinese)
[16] WU Q,ZHAO Q J,WANG Q. Highly-efficient aerodynamic option design of rotor airfoil using viscous adjoint method[J].Transactions of Nanjing University of Aeronautics&Astronautics,2017,34(2):134-142.
[17]贾沛然,沈为异.弹道导弹弹道学[M].长沙:国防科技大学出版社,1980.JIA P R,SHEN W Y. Ballistic missile ballistics[M]. Changsha:National University of Defense Technology Press,1980.(in Chinese)
[18] POPE S P. Turbulent flows[M]. Cambridge,UK:Cambridge University Press,2000.
[19] THOMAS J P,DOWELL E H,HALL K C. Nonlinear inviscid aerodynamic effects on transonic divergence,flutter,and limitcycle oscillations[J]. AIAA Journal,2002,40(4):638-646.
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