大气摄动力作用下卫星轨道仿真

Simulation of Satellite Orbit Under the Action of Atmospheric Perturbation Force

卫星飞行过程中,会受到地球非球形、大气、日月引力、太阳光压等摄动要素的影响.这里把地球视为密度均匀的圆形球体,考虑了大气密度和大气旋转的摄动影响,给出了相应的数学模型;利用四阶龙格-库特算法和MATLAB-simulink进行模型求解,得到了大气摄动影响下卫星轨道;在给定的初始条件下卫星飞行两圈的仿真结果显示:第一圈的远地点:7168.05 km,近地点:7118.56 km;第二圈的远地点:7166.75 km,近地点:7117.32 km;第二圈比第一圈轨道的远地点减小了1.3 km,近地点减小了1.24 km.随着时间的推移,轨道逐渐变小.由于大气密度变化以及大气旋转机制十分复杂,目前仍没有很精确的大气模型,该文的大气模型采用的是一种近似模型,大气要素的影响仍需要进一步去探索.

During the flight of a satellite,it will be affected by the factors such as the non-sphericity of the earth,the atmosphere,the gravity of the sun and the moon,the solar light pressure and so on.Here,the earth is regarded as a circular sphere with uniform density,and the perturbation effects of atmospheric density and atmospheric rotation are considered,and the corresponding mathematical model is given.The fourth-order Longo-Cooter algorithm and MATLAB-simulink are used to solve the model.The satellite orbit under the influence of atmospheric perturbation is obtained.Under the given initial conditions,the simulation results of satellite flying twice show that the apogee of the first lap is 7168.05 km and the perigee is 7118.56 km.The apogee of the second lap:7166.75 km,perigee:7117.32 km;The apogee of the second lap is 1.3 km lower than that of the first lap,and the perigee is 1.24 km lower.With the passage of time,The orbit is getting smaller.Due to the complexity of atmospheric density change and atmospheric rotation mechanism,there is still no accurate atmospheric model.The atmospheric model in this paper is an approximate model,and the influence of atmospheric factors still needs further exploration.