Maneuver Scheme Planning Of The Close-range Rendezvous For The High Earth Orbit Spacecraft

Geosynchronous orbit(GEO)spacecrafts play an important role in many fields.With the increasing number of spacecrafts in the geosynchronous orbit area,on-orbit services for geosynchronous orbit spacecrafts have become the focus of current orbit technology research.Before conducting on-orbit services for GEO spacecrafts,it is necessary to have a comprehensive understanding of its operational status.It is,therefore,necessary to design the orbital maneuver strategy to perform close-range observation or detection of the target spacecraft.However,when the payload carried by the service spacecraft needs to meet certain conditions when observing or detecting the target spacecraft at close range,such as distance limitations,lighting conditions,etc..It is necessary to consider the situation of the payload when designing the orbit change strategy so that the spacecraft can serve the spacecraft at a specific location.This paper focuses on the problem of high-orbits spacecraft for close-range rendezvous of geosynchronous orbit spacecrafts.Considering the limitation of observation conditions,the research on the solution to the variable orbit strategy is carried out.The main research content is as follows:In order to solve the orbital transfer strategy,we firstly establish the coordination system based on the operation range and analyze the forces of the spacecraft in the space.We set out from the speed and accuracy respectively,an ideal and high-precision orbital dynamics model is established for whether to consider the perturbation existing in space.According to the differences between the two models and the accuracy requirements in the numerical solution,considering the optimization variables and optimization functions used in the optimization process,a mathematical model is established for the position vector angle between different models,so as to take into account the accuracy and rapidity of the solution.Since the payload has different constraints when observing the target spacecraft in different orbits,the process is classified according to the orbit of the target spacecraft.The coplanar process needs to consider the light conditions so that the service spacecraft has better imaging conditions for the target spacecraft.The nonplanar process needs to consider the latitude amplitude of the target spacecraft,so that the service spacecraft has a longer observation time for the target spacecraft.Establish a complete close-range rendezvous process,turn the meeting issue into an optimization problem,and complete the solution to the orbital strategy.Mathematical simulations verify the effectiveness of the orbital strategy and the reliability of the observed effects.Against with the restrictions on the ability to observe only one particular direction of the target spacecraft for close-range rendezvous,we design the orbit change strategy to enable the service spacecraft to form a stable orbital ellipse for the target spacecraft,which can observe the target spacecraft more fully.Firstly,the relative kinematics model of the spacecraft in the orbital coordinate system is established based on the C-W equation.The light conditions and the relative positions between the two spacecrafts and the sun are analyzed to obtain the phasing time of the spacecraft for better lighting conditions.Secondly,the motion process of the service spacecraft is deduced,and a variable orbit strategy for stable orbital flight is obtained.Finally,the effectiveness of the orbit change strategy is verified by numerical simulation.