远程尾控制导炮弹气动特性及仿真分析  

Aerodynamic characteristics and simulation analysis of remote tail control guided projectiles

作　　者：王桂奇 刘福朝 刘宁[1,2] 李存健[1,2] WANG Guiqi;LIU Fuchao;LIU Ning;LI Cunjian(School of Automation,Beijing Information Science and Technology University,Beijing 100192,China;Beijing Key Laboratory of High Dynamic Navigation Technology,Beijing Information Science and Technology University,Beijing 100192,China)

机构地区：[1]北京信息科技大学自动化学院,北京100192 [2]北京信息科技大学高动态导航技术北京市重点实验室,北京100192

出　　处：《兵器装备工程学报》2023年第5期11-16,共6页Journal of Ordnance Equipment Engineering

基　　金：北京市自然科学基金项目(4214071,4212003)。

摘　　要：针对高旋制导炮弹高转速导致控制难度大的问题,设计了一种利用船尾装置进行弹体减旋控制的制导炮弹外形,减旋船尾的轴承装置与前部舱段采用非硬连接方式,能够保证弹体出膛后达到船尾减旋效果。对弹体的气动外形进行物理建模,使用GAMBIT进行非结构化网格划分,通过FLUENT软件在Spalart-Allmaras模型的基础上对非硬连接减旋船尾的制导炮弹进行气动特性仿真。仿真结果表明:在500次迭代完成后,随着马赫数的升高,阻力系数的收敛值从0.1740增加到0.4665,升力系数的收敛值从0.06699增加到0.4088,力矩系数的收敛值从0.08668增加到0.6460;弹头和弹尾所受压力值随着马赫数的增加而增大,且弹头所受压力最大值为9.82e+0.5 Pa,弹尾所受压力最大值为1.71e+0.5 Pa。仿真结果表明具有减旋船尾的制导炮弹气动外形合理,所得气动参数可为减旋制导炮弹提供设计依据。Aiming at the problem that the control of a high-rotation guided projectile is difficult due to a high rotation speed,this paper designs guided projectile shape by using stern devices for projectile spinning reduction control.The bearing device of the spinning reduction stern is non-hard connected with the front cabin,which can ensure that the effect of spinning reduction at the stern can be achieved after the projectile is out of the chamber.Firstly,a physical model of the aerodynamic shape of the projectile is established,and unstructured grid division is done by GAMBIT.Based on the Spalart-Allmaras model,the FLUENT software is used to simulate the aerodynamic characteristics of the guided projectile of the spinning reduction stern with non-rigid connection.The simulation results show that after 500 iterations,with the increase of Mach number,the convergence value of resistance coefficient increases from 0.1740 to 0.4665,the convergence value of lift coefficient increases from 0.06699 to 0.4088,and the convergence value of torque coefficient increases from 0.08668 to 0.6460.The pressure on the warhead and the stern increases with the increase of Mach number,and the maximum pressure on the warhead is 9.82e+0.5 Pa and on the tail is 1.71 e+0.5 Pa.The simulation results show that the aerodynamic shape of the guided projectile with an anti-spinning stern is reasonable,and the obtained aerodynamic parameters can provide design basis for anti-spinning guided projectiles.

关 键 词：制导炮弹 气动特性 减旋船尾 力学模型 数值仿真 

分 类 号：TJ399[兵器科学与技术—火炮、自动武器与弹药工程]