低转速条件下的弹丸飞行稳定性分析
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摘要
为了解决制导炮弹引信试验成本高、研制进度慢、试验条件复杂等问题,以制式榴弹为原型设计了模拟试验弹,用于模拟引信的发射环境。由于试验弹转速较低,在不采用尾翼的条件下,出炮口距离200~300 m内,弹丸是否飞行稳定,是一个需要重点考虑的问题。飞行中的弹丸,由于阻力方向与质心运动方向不一致,导致合力不一定通过质心,迫使弹体在空中翻转,所以弹体的旋转速度和气动外形设计是弹体飞行稳定的必要条件。通过对弹丸在一定距离内的飞行稳定性数值计算,用数值计算结果进行稳定性仿真分析,进而说明数值仿真计算对弹丸气动外形设计可以提供有效参考。
To solve the problems of high cost,slow development speed and complex test conditions of the guided projectile fuze,a simulation test projectile was designed based on the standard grenade,which is used to simulate the launching environment of the fuze. Since the speed of test projectile is low under the condition of not using the tail fin,the flying stability of the projectile within the muzzle distance from200 meters to 300 meters needs to be considered. In flight,because the resistance direction is not consistent with the direction of the center of mass movement,the resultant force does not necessarily pass through the centroid,forcing the projectile to rotate in the air,so the rotation speed and aerodynamic shape design of the projectile body is the necessary condition for the projectile flight stability. The flight stability of the projectile within a certain distance is calculated,the stability simulation analysis is carried out with the numerical calculation results,and the numerical simulation calculation can provide effective reference for the projectile aerodynamic shape design.
To solve the problems of high cost,slow development speed and complex test conditions of the guided projectile fuze,a simulation test projectile was designed based on the standard grenade,which is used to simulate the launching environment of the fuze. Since the speed of test projectile is low under the condition of not using the tail fin,the flying stability of the projectile within the muzzle distance from200 meters to 300 meters needs to be considered. In flight,because the resistance direction is not consistent with the direction of the center of mass movement,the resultant force does not necessarily pass through the centroid,forcing the projectile to rotate in the air,so the rotation speed and aerodynamic shape design of the projectile body is the necessary condition for the projectile flight stability. The flight stability of the projectile within a certain distance is calculated,the stability simulation analysis is carried out with the numerical calculation results,and the numerical simulation calculation can provide effective reference for the projectile aerodynamic shape design.
引文
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[16]江晓东,谢京稳,郭军海.基于动力学模型的弹道式再入弹道估计方法[J].现代防御技术,2014,42(2):128-133.JIANG Xiao-dong,XIE Jing-wen,GUO Jun-hai.Ballistic Reentry Trajectory Estimation Method Based on Dynamic Model[J].Modern Defence Technology,2014,42(2):128-133.
[2]彭勇,习滔滔.122 mm火箭弹制导化发展途径研究[J].现代防御技术,2016,44(3):18-24.PENG Yong,XI Tao-tao.Guidance Development of 122mm Rocket[J].Modern Defence Technology,2016,44(3):18-24.
[3]贾子英,陈松辉,叶春燚.作战体系结构稳定性突变分析[J].现代防御技术,2016,44(1):1-4,21.JIA Zi-ying,CHEN Song-hui,YE Chun-yan.Analysis of Stability of Operation So S Structure Based on Catastrophe[J].Modern Defence Technology,2016,44(1):1-4,21.
[4]祁载康.制导弹药技术[M].北京:北京理工大学出版社,2002.QI Zai-kang.Guided Ammunition Technology[M].Beijing:Beijing Institute of Technology Press,2002.
[5]钱翼稷.空气动力学[M].北京:北京航空航天大学出版社,2004.QIAN Yi-ji.Aerodynamics[M].Beijing:Beijing University of Aeronautics and Astronautics Press,2004.
[6]谷逸宇.多导弹编队飞行导引律设计[J].现代防御技术,2014,42(1):51-55.GU Yi-yu.Guidance Law of Multi-Missiles Formation Fight[J].Modern Defence Technology,2014,42(1):51-55.
[7]美军装备司令部.弹丸的飞行稳定性设计[M].杨为中,译.北京:国防工业出版社,1976.The United States Military Equipment Command.The Flight Stability Design of Projectiles[M].YANG Weizhong,Translatied.Beijing:National Defense Industry Press,1976.
[8]韩子鹏.弹箭外弹道学[M].北京:北京理工大学出版社,2014.HAN Zi-peng.Missile Exterior Ballistics[M].Beijing:Beijing Institute of Technology Press,2014.
[9]宋丕极.弹丸动稳定性的物理解释[J].兵工学报,1987,31(2):72-75.SONG Pi-ji.Physical Explanation of Dynamic Stability of Projectile[J].Acta Armamentarii,1987,31(2):72-75.
[10]王晓兵,李菁,廖忠全,等.基于FLUENT的弹丸外流场数值仿真[J].计算机辅助工程,2010,19(1):92-94.WANG Xiao-bing,LI Jing,LIAO Zhong-quan,et al.Numerical Simulation on Outer Flow Field of Projectile Based on FLUENT[J].Computer Aided Engineering,2010,19(1):92-94.
[11]姜波,齐杏林,贾波,等.基于fluent的弹丸外流场仿真计算[J].计算机仿真,2014,31(3):38-40,45.JIANG Bo,QI Xing-lin,JIA Bo,et al.Simulation Research on Projectile External Flow with Fluent[J].Computer Simulation,2014,31(3):38-40,45.
[12]伍星,卢永刚,宋琼,等.基于Fluent的弹体气动特性计算与分析[J].兵器装备工程学报,2016,37(2):22-25.WU Xing,LU Yong-gang,SONG Qiong,et al.FluentBased Calculation and Analysis of Missile Aerodynamic Characteristics[J].Journal of Ordnance Equipment Engineering,2016,37(2):22-25.
[13]王朋飞,曹红松,王智军,等.高旋火箭弹增程稳定性设计及气动特性分析[J].弹箭与制导学报,2012,32(5):124-126.WANG Peng-fei,CAO Hong-song,WANG Zhi-jun,et al.Stability Design and Aerodynamic Characteristics Analysis of High Rotating Rocket Projectile[J].Journal of Projectiles,Rockets,Missiles and Guidance,2012,32(5):124-126.
[14]周觐,雷虎民,李炯,等.导弹俯仰通道制导控制一体化设计[J].现代防御技术,2014,42(5):80-84,90.ZHOU Jin,LEI Hu-min,LI Jiong,et al.Integrated Design of Guidance and Control for Missile Pitching channel[J].Modern Defence Technology,2014,42(5):80-84,90.
[15]范文锋,许波,郝昀.助推-滑翔飞行器弹道最优控制研究[J].现代防御技术,2014,42(3):31-36.FAN Wen-feng,XU Bo,HAO Jun.Trajectory Optimal Control for Boost-Glide Vehicle[J].Modern Defence Technology,2014,42(3):31-36.
[16]江晓东,谢京稳,郭军海.基于动力学模型的弹道式再入弹道估计方法[J].现代防御技术,2014,42(2):128-133.JIANG Xiao-dong,XIE Jing-wen,GUO Jun-hai.Ballistic Reentry Trajectory Estimation Method Based on Dynamic Model[J].Modern Defence Technology,2014,42(2):128-133.