日心悬浮轨道混合推进航天器编队构型保持研究  

Solar Sail and Coulomb Hybrid Propulsion Spacecraft Formation Around the Displaced Solar Orbit

作　　者：左晨熠 袁长清[1] 龚胜平[2] 贺京九 ZUO Chenyi;YUAN Changqing;GONG Shengping;HE Jingjiu(Air Force Aviation University,Changchun 130022,China;Tsinghua University,Beijing 100084,China)

机构地区：[1]空军航空大学,长春130022 [2]清华大学,北京100090

出　　处：《空间控制技术与应用》2020年第5期36-41,共6页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(11372353,10902125).

摘　　要：针对混合推进航天器编队日心悬浮轨道保持控制问题进行了研究.首先推导出在日心悬浮轨道附近的航天器编队相对运动方程,考虑到航天器间距离变化值较小且航天器间距离与航天器到太阳的距离的比值为小量,将其在悬浮轨道附近线性化.基于该线性化方程,设计了一种LQR编队控制方式,该控制方式可通过调节太阳帆的姿态及航天器间库仑力的大小对编队构型进行改变或保持,具有响应速度快和控制简单的特点.最后对控制律进行数值仿真,表明该控制方法能实现编队.The problem of maintaining control is investigated for the hybrid propulsion spacecraft formation around the displaced solar orbit.Firstly,the equation of the formation around the displaced solar orbit for relative motion is derived.Since the changing of the displacement between two different spacecrafts is small and the displacement between two different spacecrafts is very small compared with the displacement from the spacecrafts to the sun,the equation of motion is linearized around the displaced solar orbit.Based on the linear equation,the linear quadratic regular(LQR)is designed.This control method which responds fast and is easier to control can change or maintain the formation configuration by adjusting the attitude of the solar sail and the Coulomb force between the spacecrafts.Simulations are given based on the linear equation.The results show that the strategies can realize the formation around the displaced solar orbit.

关 键 词：太阳帆 悬浮轨道 库仑力 编队保持 线性二次型调节器 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]