日心悬浮轨道航天器编队飞行控制  

Control of Spacecraft Formation Flying around Heliocentric Displaced Orbits

作　　者：张楷田 楼张鹏 王永[1] 程松松[1] 

机构地区：[1]中国科学技术大学自动化系,安徽合肥230027

出　　处：《信息与控制》2016年第1期114-119,128,共7页Information and Control

摘　　要：针对日心悬浮轨道航天器编队飞行控制问题,应用线性自抗扰控制(LADRC)技术设计了编队飞行控制器.首先,考虑外部扰动,基于圆形限制性三体问题(CRTBP)模型推导了航天器编队日心悬浮轨道非线性动力学方程.其次,提出了一种基于扰动估计和补偿的编队飞行控制方法,避免了通过航天器局部线性化动力学方程或精确非线性动力学方程设计编队飞行控制器时存在的模型精确性过度依赖等缺陷.最后,数值仿真表明存在系统模型不确定性、初始入轨误差及地球轨道偏心率扰动的情况下,所设计的控制器实现了高精度的编队飞行控制,并优于NASA制定的5 mm编队飞行精度标准.We investigate the control of spacecraft formation flying around heliocentric displaced orbits,and propose a control method based on linear active disturbance rejection control（ LADRC）. First,we derive a nonlinear dynamic model of the spacecraft formation based on the circular restricted three-body problem（ CRTBP） model,considering external disturbance. Then,we present a spacecraft formation flying control method based on the estimation of and compensation for disturbance. This control method avoids the problem of excessive dependency on model accuracy,which occurs when controllers are designed according to a locally linearized model or an accurate nonlinear model. Finally,our numerical simulation results show that the proposed method achieves high control accuracy in the presence of system uncertainties,initial injection errors,and perturbations due to the eccentric nature of the Earth＇s orbit. Furthermore,the precision of the formation control is within 5 millimeters,and satisfies NASA＇s high accuracy requirement.

关 键 词：日心悬浮轨道 航天器编队飞行 线性自抗扰控制 

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]