地球轨道卫星电推进变轨控制方法  

Control Method for Earth Satellite Orbit Transfer Using Electric Propulsion

作　　者：杨大林[1] 徐波[2] 高有涛[1] 

机构地区：[1]南京航空航天大学航天学院,南京210016 [2]南京大学天文与空间科学技术学院,南京210093

出　　处：《宇航学报》2015年第9期1010-1017,共8页Journal of Astronautics

基　　金：国家高技术研究发展计划(2012AA121602);国家自然科学基金(11078001);中央高校基本科研业务费专项资金(NS2012132)

摘　　要：针对地球同步轨道(GEO)卫星,采用电推进系统完成转移轨道变轨。采用基于Lyapunov函数的反馈控制方法确定时间最短变轨策略。首先在开普勒模型下研究变轨过程,然后在开普勒模型的基础上考虑地球J2项摄动和地球阴影,最后在全引力模型下研究变轨过程,即在开普勒模型的基础上考虑地球非球形引力摄动、日月第三体引力摄动、太阳光压摄动和地球阴影。仿真结果显示在变轨过程中摄动项不可忽略,除地球J2项摄动外还应该考虑日月第三体引力摄动和太阳光压摄动。对比上述三组仿真结果,发现考虑摄动后轨道转移时间的增加比燃料消耗的增加更为明显。数值仿真结果表明本文研究对未来的全电推进任务具有良好的通用性和应用参考价值。The geostationary satellite is equipped with an electric propulsion system, which is used to complete the orbit transfer. The time-optimal orbit transfer is determined by using Lyapunov-based feedback control method. Firstly, the simulation is carried out in a Keplerian model. Then earth J2 perturbation and earth shadow are considered. Finally, full gravity model, including the oblateness and triaxiality of the earth, the gravitational forces of the sun and the moon, the solar radiation pressure, and the earth shadow is considered. The effect of perturbations on orbital elements is analyzed, and it is indicated that the effect of perturbations is not negligible. In addition to the earth J2 perturbation, the gravitational forces of the sun and the moon and the solar radiation pressure should also be considered in the orbit transfer process. A comparison between solutions in above cases is presented, revealing that the increase of transfer time is more obvious than the increase of fuel consumption when the perturbations are considered. Numerical simulation results show that this method has good versatility and application reference value for future all-electric propulsion mission.

关 键 词：地球同步轨道卫星 电推进 基于Lyapunov函数的反馈控制方法 全引力模型 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]