战术弹道导弹的弹道仿真

Ballistic Simulation of Tactical Ballistic Missile

战术弹道导弹(TBM)的弹道运动可以看作是导弹绕地心质点的二体运动,因此进行TBM弹道仿真的关键是根据发射点和落点的经纬度计算弹道轨道根数。考虑导弹运动过程中地球自转所产生的落点经度的变化,研究建立了弹道轨道根数的求解方法,通过坐标变化方法对轨道根数进行了校验,并采用二体椭圆轨道运动理论实现了TBM的弹道仿真,仿真得到的发射点落点位置与给定的位置完全重合,从而对轨道根数进行了进一步的确认。

The trajectory of tactical ballistic missile （TBM） can be considered as two body movement in which the missile moves around the centroid of the earth, so the key problem of trajectory simulation is to solve the elliptical orbit parameters according to the given points of both launching and landing in lon- gitude and latitude. Taking account with the variety of landing longitude caused by the earth rotation during missile movement, the solution of orbit parameters is put forwards by research, and is verified by coordinates transformations. The trajectory simulation is implemented with the elliptical orbit theory of two body movement, the simulated points of launching and landing are as same as given respectively, and the verification is passed thereby.