发射扰动与初始弹道耦合模型研究  

Research on coupling model of launch disturbance and initial trajectory

作　　者：何泽鹏 毕世华[1] 傅德彬[1] 李云峰 HE Zepeng;BI Shihua;FU Debin;LI Yunfeng(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;Ministry of Technology,Jilin Jiangji Special Industry Co.,Ltd.,Jilin 132021,China)

机构地区：[1]北京理工大学宇航学院,北京100081 [2]吉林江机特种工业有限公司技术部,吉林132021

出　　处：《固体火箭技术》2019年第4期546-552,共7页Journal of Solid Rocket Technology

基　　金：国家自然科学基金项目(51306019)

摘　　要：针对火箭、导弹发射扰动与初始弹道互相耦合引起的弹道散布问题,提出发射扰动与弹道解算相耦合的计算分析模型。该模型以多体系统动力学为基础,建立能够模拟弹架相互作用和弹体初始扰动的发射动力学模型,并将弹体受到的气动载荷转化到弹体坐标系下进行刚体动力学计算以获得弹道参数。通过滚转弹应用实例分析表明,采用此模型能够有效模拟发射扰动与初始弹道相互耦合状态;弹架间隙扰动与气动载荷作用都会对弹体在飞行时的姿态角及飞行位置产生较大影响。当存在1 mm的弹架间隙且有气动载荷作用的影响下,与无弹架间隙和气动载荷的作用影响的结果对比发现,存在弹架间隙扰动的影响会使得弹体在飞行过程中的俯仰角和弹道倾角的幅值范围减小4°左右,也使得弹体在飞行过程中的Y向位移量在1.5 s时刻减小6 m左右;存在气动载荷作用的影响,会使得弹体在0.5 s撤去推力后的姿态角成波动式变化,滚转弹稳定飞行,也会使得弹体Y向位移量在撤去推力后持续的平稳增加。Aiming at the phenomenon that the initial trajectory is widely dispersed due to the initial disturbance of the missile launching and the initial trajectory coupling,a calculation method based on multi-body dynamics launch,initial disturbance and initial trajectory coupling has been proposed.Based on the theory of multi-body system dynamics,this method establishes a launch dynamics model that simulated the interaction of the projectile frame and the initial disturbance of the projectile.It converts all aerodynamic loads into the missile body coordinate system for initial ballistic calculation.By analysis of the rolling missile application example,it has been shown that the model can simulate the state of mutual coupling between the missile launching and the initial trajectory effectively. In addition, the effects of the clearance impact between the missiles and launchers, the aerodynamic load disturbance are significant on the attitude angle and flight position of the missile during flight. When there is a 1 mm rack clearance and the effect of aerodynamic load, comparing to the condition free of the rack clearance and aerodynamic loads,the effect of the clearance between the missiles and launchers would reduce the range of the pitch angle and the ballistic inclination of the projectile during the flight by about 4°.The Y -direction displacement of the projectile during flight has been reduced by about 6 m at 1.5 s.The effect of the aerodynamic load may cause fluctuation of the attitude angle of the projectile after the thrust is removed in 0.5 s,and the rolling missile could become stable flight and make the displacement of the Y -direction of the projectile continue to increase steadily after the thrust is removed.

关 键 词：发射扰动 初始弹道 多体系统动力学 气动载荷 弹架间隙 

分 类 号：V553.2[航空宇航科学与技术—人机与环境工程] TJ013.2[兵器科学与技术—兵器发射理论与技术]