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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.
In order to solve the flight control problem of spacecraft orbit formation in heliocentric space, a formation flight controller is designed by LADRC technique.Firstly, based on the external perturbation, the spacecraft is derived based on the circular constrained three-body problem (CRTBP) The formation of a non-linear dynamic equation of a suspended corridor of a orbiting heart is presented.Secondly, a formation flight control method based on disturbance estimation and compensation is proposed, which avoids the formation of a formation flight by means of a spacecraft local linearization dynamics equation or an exact nonlinear dynamic equation Controller over-reliance on the accuracy of the model and other defects.Finally, the numerical simulation shows that the existence of model accuracy in the presence of system model uncertainty, initial orbital error and Earth’s orbit eccentricity disturbance case, the controller designed to achieve high-precision formation Flight control and superior to 5 mm formation accuracy standards set by NASA.