低速旋转导弹滚转特性数值模拟研究
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摘要
为了研究旋转以及尾翼斜置角对尾翼式导弹滚转特性的影响,基于三维非定常N-S方程和滑移网格技术,对旋转弹的滚转特性进行了数值模拟。提出了适用于小尾翼斜置角、低转速情况下的滚转力矩系数以及平衡转速的经验公式,以美国陆-海军动导数计算标模验证了该方法具有的较高计算精度。模拟研究表明:滚转力矩系数随转速呈线性变化关系。
In order to study the influences of rotation and oblique angle of wing on rolling characteristics of missile,computational fluid dynamic simulations which based on Navier-Stokes equations with time dependent method and the sliding mesh,were used to predict the rolling characteristics over a spinning missile. The Army-Navy Basic Finner Missile is used for verifying the validity of the numerical method which has a high accuracy. The result shows that rolling moment coefficient vary linearly with rotate rate.The empirical equation of rolling moment coefficient and balancing rotating speed for small oblique angle of wing and slow rotate rate were put forward and verified.
In order to study the influences of rotation and oblique angle of wing on rolling characteristics of missile,computational fluid dynamic simulations which based on Navier-Stokes equations with time dependent method and the sliding mesh,were used to predict the rolling characteristics over a spinning missile. The Army-Navy Basic Finner Missile is used for verifying the validity of the numerical method which has a high accuracy. The result shows that rolling moment coefficient vary linearly with rotate rate.The empirical equation of rolling moment coefficient and balancing rotating speed for small oblique angle of wing and slow rotate rate were put forward and verified.
引文
[1]周德娟.不同尾翼结构形式的翼身组合体滚转阻尼导数及其它气动特性的研究[D].南京:南京理工大学,2012.
[2]REGAN F J.Roll Damping Moment Measurements for The Basic Finner at Subsonic and Supersonic Speed[R].Navord Report 6652,1964(04).
[3]COLLINS J A.Verofication Test of the AEDC High Aloha Roll Dynamics System[R].AEDC-TSR-78-P50,1978.
[4]LEROY.Experimental Roll-damping,Magnus,and Staticstability Characteristics of Two Slender Missile Configuration at High Angles of Attack and Mach Number 0.2through 2.5[R].AEDC-TR-75-58,1976.
[5]PAUL WEINACHT W B S.Computation of the Roll Characteristics of The M829 Kinetic Energy Projectile and Comparison with Range Data[R].BRL-TR-3172,1990.
[6]ERDAL OKTAY.CFD Predictions of Dynamic Derivatives for Missiles[J].AIAA 2002-0276,2002.
[7]JOHN F.Stalnaker.Computation of Stability Derivatives of Spnning Missiles Using Unstructured Certesain Meshes[J].AIAA 2002-2802,2002.
[8]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(3):58-62.
[9]余奇华,敬代勇.旋转尾翼鸭式布局导弹数值模拟[J].战术导弹技术,2012(2):16-19.
[10]米百刚,詹浩,朱军.基于CFD数值仿真技术的飞行器动导数计算[J].空气动力学学报,2014(6):834-839.
[11]雷娟棉,李田田,黄灿.高速旋转弹丸马格努斯效应数值研究[J].兵工学报,2013(6):718-725.
[12]BHAGWANDIN V.Numerical Prediction of Roll Damping and Magnus Dynamic Derivatives for Finned Projectiles at Angle of Attack[C]//Aiaa Applied Aerodynamics Conference.2013:683-695.
[13]BHAGWANDIN V A,SAHU J.Numerical Prediction of Pitch Damping Stability Derivatives for Finned Projectiles[J].Journal of Spacecraft and Rockets,2014,51(5):1603-1618.
[14]余陵,郑健,王栋,等.火箭外弹道基础[M].南京:南京理工大学,2014,78-80.
[15]万莹.斜切角尾翼对弹箭滚转特性的影响研究[D].南京:南京理工大学,2011.
[16]何颖,胡金波,邹亚,等.低速旋转弹丸偏流现象数值模拟[J].兵器装备工程学报,2016,37(1):18-22.
[2]REGAN F J.Roll Damping Moment Measurements for The Basic Finner at Subsonic and Supersonic Speed[R].Navord Report 6652,1964(04).
[3]COLLINS J A.Verofication Test of the AEDC High Aloha Roll Dynamics System[R].AEDC-TSR-78-P50,1978.
[4]LEROY.Experimental Roll-damping,Magnus,and Staticstability Characteristics of Two Slender Missile Configuration at High Angles of Attack and Mach Number 0.2through 2.5[R].AEDC-TR-75-58,1976.
[5]PAUL WEINACHT W B S.Computation of the Roll Characteristics of The M829 Kinetic Energy Projectile and Comparison with Range Data[R].BRL-TR-3172,1990.
[6]ERDAL OKTAY.CFD Predictions of Dynamic Derivatives for Missiles[J].AIAA 2002-0276,2002.
[7]JOHN F.Stalnaker.Computation of Stability Derivatives of Spnning Missiles Using Unstructured Certesain Meshes[J].AIAA 2002-2802,2002.
[8]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(3):58-62.
[9]余奇华,敬代勇.旋转尾翼鸭式布局导弹数值模拟[J].战术导弹技术,2012(2):16-19.
[10]米百刚,詹浩,朱军.基于CFD数值仿真技术的飞行器动导数计算[J].空气动力学学报,2014(6):834-839.
[11]雷娟棉,李田田,黄灿.高速旋转弹丸马格努斯效应数值研究[J].兵工学报,2013(6):718-725.
[12]BHAGWANDIN V.Numerical Prediction of Roll Damping and Magnus Dynamic Derivatives for Finned Projectiles at Angle of Attack[C]//Aiaa Applied Aerodynamics Conference.2013:683-695.
[13]BHAGWANDIN V A,SAHU J.Numerical Prediction of Pitch Damping Stability Derivatives for Finned Projectiles[J].Journal of Spacecraft and Rockets,2014,51(5):1603-1618.
[14]余陵,郑健,王栋,等.火箭外弹道基础[M].南京:南京理工大学,2014,78-80.
[15]万莹.斜切角尾翼对弹箭滚转特性的影响研究[D].南京:南京理工大学,2011.
[16]何颖,胡金波,邹亚,等.低速旋转弹丸偏流现象数值模拟[J].兵器装备工程学报,2016,37(1):18-22.