椭圆参考轨道卫星编队飞行的高阶积分滑模控制

Higher Order Integral Sliding Mode Control for Spacecraft Formations in Eccentric Reference Orbits

针对椭圆参考轨道卫星编队飞行相对轨道控制问题,提出了一种以积分滑模为基础的高阶滑模相对轨道控制律.该控制律除具有高阶滑模抑制扰动的优点外,还具有使系统状态在有限时间稳定的特点,且控制精度高并具有全局鲁棒性.此外,还采用Lyapunov变换和自由变量变换将椭圆参考轨道的相对动力学方程转化为真近点角域中的量纲-形式,这种形式设计起来比较简单.仿真结果表明所设计的高阶积分滑模控制具有抑制控制律的扰动,燃料消耗少且控制精度高等优点.

Considering the relative orbit control problem of spacecraft formations in eccentric reference orbits,this paper proposed a higher order integral sliding mode control law.This control law can not only restrain chattering,but also make system states converge to equilibrium points in finite time,and with high accuracy and global robust.Furthermore,the general relative equations of motion were transferred into non-dimensional form by using Lyapunov transformation.This form is easy for design.Numerical simulations demonstrate that the higher order integral sliding mode control can counteract chattering with optimal fuel consuming and high accuracy.