基于差分气动力的J_2项摄动下卫星编队构形重构研究  

Research on Satellite Formation Reconfiguration by Using Differential Aerodynamic Forces under J_2 Perturbation

作　　者：宋明轩[1] 邵晓巍[1] 刘付成 王继河[1] 张德新[1] 

机构地区：[1]上海交通大学航空航天学院,上海200240 [2]上海航天控制技术研究所,上海200233

出　　处：《航天控制》2014年第4期42-48,61,共8页Aerospace Control

摘　　要：针对低轨小卫星的编队构形重构,设计了一种新型的差分气动力控制方法。根据卫星在低轨道飞行时会受到较大气动力的特点,基于稀薄气体动力学理论,建立了卫星气动板的气动力模型。考虑了J2项摄动对卫星编队队形的影响,结合Schweighart和Sedwick提出的高精度J2项摄动方程,推导出了一组适用于差分气动力控制的非线性相对运动方程。卫星编队飞行时,通过切换六种不同的气动板配置方式可以产生稳定的差分气动升力或阻力,依次进行编队卫星轨道面内和轨道面外的路径规划,实现编队构型重构。仿真结果表明,与不考虑J2摄动影响的模型相比较,该方法具有更高的控制精度,可用于卫星编队飞行时的轨道机动控制。A novel control method by using differential aerodynamic forces is designed for the small satellite formation reconfiguration at low earth orbit（LEO） in this paper.Due to the characteristics of LEO,the spacecraft is subject to larger aerodynamic force.And the aerodynamic model of satellite plate is established,which is based on the Kinetic theory.By considering J2 perturbation,a non-linearized model using differential aerodynamic force is derived from the high-fidelity J2 equations proposed by Schweighart and Sedwick.The satellite formation reconfiguration can be achieved by conducting in-plane and out-of-plane maneuvers in sequence in terms of stable differential lift or drag which is generated by switching six different configurations of aerodynamic plates.The simulation results show that the proposed method can be applied to satellite formation reconfiguration as higher control precision compared to the case without considering J2 perturbation.

关 键 词：卫星 编队飞行 差分气动力 构形重构 J2项摄动 

分 类 号：V448.234[航空宇航科学与技术—飞行器设计]