大长径比远程弹箭的极限平面摆动及其抑制  

Limit Plane Swing Motion and Its Restraining Measure of Un-rotary Long-range Missile with Large Ratio of Length to Diameter

作　　者：李臣明[1] 刘怡昕[1] 

机构地区：[1]解放军南京炮兵学院,南京211132

出　　处：《系统仿真学报》2009年第23期7390-7392,7396,共4页Journal of System Simulation

摘　　要：为了寻求远程弹箭研制过程中出现的试验射程与计算射程相差较大的原因,分析了可能造成高空远程弹箭近弹的因素,引入数学中的奇点理论与振幅平面方程,重点研究了非旋转大长径比远程弹箭在非线性气动力作用下作极限平面摆动的机理及其抑制措施。结果表明:大攻角下产生的非线性气动力可使大长径比弹箭作极限平面摆动造成攻角长时间不衰减,导致弹箭的弹道阻力增大,减小射程。可以通过改变气动参数与发射初始扰动对其进行抑制。Aiming at the problem that the testing range of unrotary long-range missile with large ratio of length to diameter was nearer markedly than the calculational range,some factors were analyzed in order to find the truth.The singular point theory and swing plane equation theory were applied to solve this problem,and these theories were the mathematic tool to study the stability of the system.The limit plane swing movement and its restraining measure of un-rotary long-range missile with large ratio of length to diameter were studied emphatically.The result shows that the nonlinear aerodynamic force arose by large angle of attack can lead to limit plane swing movement which can make the angle of attack un-damping during a long trajectory,and this case can increase the drag force of the trajectory to decrease the range.The simulation shows that this phenomenon can be restrained through changing the aerodynamic parameters and initial value.

关 键 词：外弹道 非线性运动 极限运动 奇点理论 振幅平面 

分 类 号：TJ013.2[兵器科学与技术—兵器发射理论与技术]