| The whole process of lunar exploration satellites from the Earth to the Moon can be divided into three parts: the Earth-Moon transfer section,the moon capture section,and the lunar orbit adjustment section.Before the orbit control of the satellite,the current state of the satellite needs to be measured so that the maneuvering value can be calculated.Therefore,the existence of the navigation deviation will cause that the state of the satellite deviates from the theoretical value,and the thrust error in the actual maneuvering process will also affect the accuracy of the control results.Therefore,it is necessary to analyze the distribution of orbital state deviations under the influence of navigation errors and control errors.The main contents of this thesis are as follows:In the Earth-Moon transfer section,based on the nominal orbit,the three body gravity of the Sun,the Earth and the Moon is considered while integrating the state transition matrix.The relationship between the state deviation and the navigation and control errors is derived,and the covariance analysis method is used to get the state deviation covariance of the satellite when it reaches the perilune.In the moon capture section,the motion of satellites is considered as the form of continuous propulsion under power-limited thrust.The thrust direction in the capture strategies considered to be along the opposite direction of velocity and to fixed in space,respectively,The formula of state error propagation in the process of maneuvering considering navigation and control errors is derived.Then the state deviation covariance of the satellite after braking is obtained.In the lunar orbit adjustment section,the Moon’s perturbation force and the three body gravity of the Sun,the Earth and the Moon are considered while integrating the state transition matrix.Based on this,the navigation and control errors are added while obtaining the deviation covariance of the height adjustment of the apolune and the perilune. |
