基于Kane方法的火箭抛绳系统飞行动力学模型  

Dynamic Model of Line Throwing Rocket System With Flight Motion Based on Kane's Method

作　　者：顾文彬[1] 陆鸣[1,2] 刘建青[1] 董勤星[1] 陈江海[1] 王振雄[1] 

机构地区：[1]解放军理工大学野战工程学院,南京210007 [2]武汉军械士官学校,武汉430075

出　　处：《弹道学报》2015年第2期19-23,共5页Journal of Ballistics

基　　金：国家"十二五"科技支撑计划项目(2012BAK05B02)

摘　　要：为了研究抛绳火箭系统的弹道特性,通过对抛绳火箭飞行的运动学描述,根据有限段方法将绳索离散为n个有限段,并进行了分析,考虑火箭和绳索上的作用力:重力、火箭所受推力、空气阻力、绳索末端所受拉力等,建立了基于Kane方法的抛绳火箭系统的动力学模型。数值实例表明:该动力学模型能够有效地实现抛绳火箭飞行过程的数值仿真,揭示了射角从25°到65°变化时,系统弹道轨迹、速度、弹道倾角、绳索状态等变化规律。该动力学模型的建立为下一步研究绳子对抛绳火箭飞行的扰动以及抛绳火箭的制导、飞行控制提供了重要理论支撑。To study the ballistic characteristics of line throwing rocket（LTR）system,a dynamic model based on Kane’s method was presented.The LTR with flight motion was described,and the rope was divided into ndiscrete finite segments by finite segment method.The dynamic model of the LTR was developed under the consideration of the forces such as the gravity,thrust,aerodynamic forces and the tension in the rope during rocket flying.The numerical result shows that the flying movement can be solved by given value of motion parameters,and the changing laws of trajectory,velocity,trajectory angle of the system can be revealed by the exploitation of the dynamic model when the launch angle changes from 25°to 65°.The dynamic model offers a key theoretical support for the research on the disturbance of the rope,the guidance and flight control of the towing rocket.

关 键 词：抛绳火箭 KANE方法 动力学 数值仿真 

分 类 号：TJ714[兵器科学与技术—武器系统与运用工程]