临近空间高超声速滑翔弹弹道特性仿真

Simulation of Trajectory Characteristics for Near Space Hypersonic Gliding Missile

临近空间高超声速滑翔弹独特的运动特性给预警系统带来了巨大挑战,为了区分控制量和初始运动状态对弹道轨迹的具体影响,以升力式再入滑翔弹为对象进行了对比仿真。仿真结果表明:强机动发生在纵向平面,控制量倾侧角决定横向机动,攻角决定纵向机动,初始航向角对横向偏移影响显著,而初始航迹倾角和初始飞行高度对纵向跳跃影响显著。

The unique motion characteristics of near space hypersonic gliding missile pose a great challenge to the early warning system. In order to distinguish the specific influence of the control quantities and the initial motion state on the trajectory,the lifting reentry vehicle is used as an object for comparative simulation. The simulation results show that strong maneuvering occurs in the longitudinal plane,the bank angle and attack angle determines the maneuvering in lateral and longitudinal plane respectively,the initial heading angle has a significant effect on lateral offset,and the initial flight path angle and flight height has a significant effect on longitudinal jump.