摘要
针对大型联合作战仿真系统需求,建立某种飞行器运动学仿真轨迹模型。讨论了射击诸元(射击方位角、俯仰程序角、初始装订参数等)的确定方法,建立了在射击平面上的飞行器主动段运动学方程组和末速修正飞行段的关机方程,推导出由平台误差分离系数到飞行器飞行主动段终点偏差的误差传递关系,然后利用椭圆轨迹理论将主动段终点偏差折算为落点偏差,并完成了轨迹数据由发射坐标系向地心大地直角坐标系的转换关系模型。仿真计算结果与飞行试验数据比对一致性好,证实了该方法的可行性。
A trajectory simulation model of a vehicle was designed to meet the requirements of joint operation simulation.Firstly the calculation methods of firing data（including firing azimuth,pitching procedure,bookbinding parameter and so on） were discussed,vehicle motion equations on firing plane for boost-phase and final powered phase were modeled,error transfer equations from guidance instrument error to boost-phase end point error was founded.Then elliptical orbit theory was applied to convert boost-phase end point error into fall point error,lastly coordinate transformation relation was established from launching coordinate system to earth centered rotation coordinate system.The simulation results and flight test results had preferably coherence,and this simulation method was feasible.
出处
《战术导弹技术》
2012年第2期20-26,共7页
Tactical Missile Technology
关键词
飞行器
运动学仿真
射击诸元
误差传递
椭圆轨迹
vehicle
dynamic simulation
firing data
error transfer equations
elliptical orbit theory
