摘要
针对某些对地观测卫星,其轨道参数不公开,只能通过对卫星的运行规律建立数学模型,推导出卫星的过顶时间,从而使对地目标有效规避卫星的对地观测.首先从卫星运行的基本规律出发,根据稀疏数据进行定轨建立了卫星定轨的数学模型,利用牛顿迭代法递推出轨道根数,同时利用摄动补偿优化了模型,再通过八阶龙格库塔法,进行轨道递推,得到了卫星过顶时间与轨道信息的对应关系.
As for some earth observation satellites, because of the private orbit parameters, the operation of the satellites cannot be obtained directly. So an appropriate mathematical model should be established to help the ground target to avoid the satellites＇ observe. This paper firstly in accordance with the basic law of the satellites operation, then establish the mathematical model for satellite orbit determination by sparse data. Using newton iteration method to get the orbital element, using perturbation compensation to optimize this model. Next using Eight Order Runge-Kutta to derive the change of the orbits. Finally the corre- sponding relationship between the satellite＇s zenith time and orbital information is obtained.
出处
《数学的实践与认识》
北大核心
2017年第15期38-45,共8页
Mathematics in Practice and Theory
