Mission-oriented Orbital Design Of LEO Platform

As the aerospace missions proceed and the space environment changes,for future space activities,the requirement of the orbital service techniques becomes stronger and stronger.These techniques include several aspects,such as cleaning of the space debris,common modules substitution for satellites,fuel filling,and so on.The development direction of the current space technology is led by the practical engineering demands,so developing a high effective,reliable,cheap orbital service platform has become a hot research point of current space engineering community.With this background,this dissertation studies the mission-oriented orbital design of LEO platform.The main research contents of this dissertation can be concluded as below:The technical path research of the maneuver of LEO orbital platform.Firstly,three maneuver strategies of the LEO platform transferring to MEO and GEO orbits are compared with each other,and the merits and suitable environments of the three strategies are discussed and analyzed based on numerical simulation examples.Secondly,the orbit transferring strategies from the LEO platform to the MEO and GEO targets are analyzed by using Lambert flight time theory and Herrick method.The researches of the two aspects above show that it is feasible for the LEO maneuver platform to perform orbital services with various orbit types.The analysis of the deviation propagation of the LEO platform maneuvering.The deviation propagation during the orbit transfer process is the problem that we need to face and research.Firstly,the variance analysis model of the deviation propagation in the processes of orbit transfer and near distance closing is deduced,considering the perturbations of earth oblateness J2 term and the atmosphere drag.Then,the influences of the initial deviation and the nonlinear rendezvous deviation propagation are analyzed,through intuitive simulation examples and orthogonal experiments.At last,the gradually change principle of non-Gaussian distribution of the terminal derivation is demonstrated by using the error ellipsoid of the terminal states and distribution map of the simulation points.The simulation analysis of the typical missions of the LEO platform.Firstly,two situations are considered,i.e.,the altitude of the maneuver platform is fixed and not,respectively.And the principle of the fuel consumption of the orbital service versus time is analyzed.Then,two mission scenarios are set,i.e.,the capture simulation of the LEO platform against MEO target and GEO target,respectively.And the change principles of the position and velocity of the maneuver platform are obtained,and the three-dimensional simulation figure of the orbit of the maneuver platform is also presented.Then,the research idea of mission-oriented orbit design of the LEO platform is validated.