翼型火箭橇弹橇分离过程气动特性研究  

Study on the Aerodynamic Characteristics of the Separation Process Between Missile and Airfoil Rocket Sled

作　　者：张晨辉 周学文 王磊 庞超 程新涛 ZHANG Chenhui;ZHOU Xuewen;WANG Lei;PANG Chao;CHENG Xintao(NORINCO GROUP Test and Measuring Academy of China Ordance Industries,Huayin 714200,Shaanxi,China)

机构地区：[1]中国兵器工业试验测试研究院,陕西华阴714200

出　　处：《弹箭与制导学报》2024年第4期82-88,共7页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国防科技创新特区项目(20-163-16-ZD-005-007-01)资助。

摘　　要：针对翼型橇终点效应试验攻角控制问题,采用基于耦合流场数值模拟方法与刚体六自由度运动方程的被试品飞行攻角工程预示程序,获取了弹-橇分离过程中被试品攻角和特征位置处弹-橇相对位置与飞行时间、距离的关系,分析了地面效应、橇体气流扰动作用下被试品气动力矩变化趋势,研究了预置攻角、分离速度、轨道参数对分离过程中被试品压心位置及攻角变化的影响规律,为翼型橇弹-橇分离方案优化设计提供技术支持。Under the special configuration the airfoil rocket sled,an engineering prediction code based on the numerical flow simulation method as well as the six degrees of freedom function was used to investigate the angle of attack of missile and the relative missile-sled position in the separation process.The influence on aerodynamic moment of the missile from the ground effect as well as the aerodynamic interference between the missile and sled was studied.In the meanwhile,the influence in the center of pressure and angle of attack of missile from the presetting angle of attack,separation speed and track parameters was studied.The conclusions would point out some technical directions to optimize the missile-sled separation plan for the airfoil rocket sled.

关 键 词：翼型火箭橇 弹橇分离 气动特性 

分 类 号：TJ76[兵器科学与技术—武器系统与运用工程]