Research On The Lagrange Satellite Maneuver Orbit Determination Based On State Observer

Deep space exploration is a hot research topic in the field of spaceflight.Due to the far distance of the deep space detector,it is difficult to satisfy the requirement of real-time and high precision of the deep space detector by the way of ground station navigation.The special dynamical properties of Lagrange points in the Earth Moon system determine that the navigation satellite constellation can provide strong navigation support for deep space exploration at the Lagrange point.Lagrange navigation satellite constellation provides accurate navigation information on the premise that the navigation satellite itself can achieve accurate positioning.This paper focuses on autonomous orbit determination technology of Lagrange navigation satellite constellation.In the process of autonomous orbit determination using only the inter satellite ranging as observation data,although the planet of autonomous orbit determination for navigation constellation in inter satellite ranging when using only the rank deficient problem,but the dynamic environment of special thanks to the Lagrange navigation satellite,which can only use the inter satellite ranging can achieve precise autonomous orbit determination.Firstly,the motion mode of Lagrange satellite under the circular restricted three body problem model is studied,and the autonomous orbit determination of the Lagrange satellite is realized by using the combination of the Kalman filtering algorithm and the distance measurement between the satellites and the.The simulation results show that the Kalman filtering algorithm can realize long-term autonomous orbit determination of the navigation satellite constellation with the consideration of range error and initial error.In addition to the gravitational pull from the earth and the moon,the Lagrange satellite is also affected by other perturbations,and the moon around the earth orbit is not absolute orbit.Considering the eccentricity of the moon around the earth's orbit and the rate of perturbations,this paper proposes a method of using only the inter satellite ranging autonomous orbit determination by neural network state observer Lagrange satellite.Firstly,the motion of the satellite near the Lagrange point is analyzed under the elliptic restricted three body problem model.Then the state observer is designed according to the dynamic equation and the convergence of the observer is proved.Finally,the simulation results show that the designed state observer can not only be used for autonomous orbit determination of Lagrange satellite,but also can estimate the disturbance accurately.Because Lagrange satellite orbit is more sensitive to the position error,it is often necessary to control the high frequency of Lagrange satellite in orbit.Orbit determination during orbit control becomes an important problem to be solved for Lagrange navigation satellite.This part of the neural network state observer design,using inter satellite ranging Lagrange satellite autonomous orbit maneuver at the same time,get the control quantity during the satellite maneuver by neural network,realizes the integrated design of Lagrange navigation satellite orbit determination algorithm and control law.The neural network state observer and neural network control law are designed according to the dynamic equation.The simulation results show that the proposed neural network state observer can realize autonomous orbit determination of Lagrange satellite,and the neural network control can keep the Lagrange navigation satellite on the nominal orbit.