A Research About Self-organized Co-location Aircraft Orbits

While there is a limitation of the fixed-point longitude resources in the geostationary orbit and a shortage of the equatorial ring position,the demand for satellite communication capacity is increasing.However,because of the difficulties of satellite launch and heat dissipation problem make it becomes difficult to make a single machine large and complex.In this case,it is necessary to consider distributing large amount of user access requirements to multiple satellites,and multiple satellites sharing the same fixed-point longitude and coordinated operation.And this is called multi-satellites co-location problem.Multi-satellites co-bit refers to that multiple geosynchronous orbit satellites in the same equatorial longitude position,as an effective solution using the synchronous orbit,has received more and more attention in recent years.In this thesis,after fully researching the relevant research internationally,and with basic understanding of what problems still need to be solved based on current researching situation of relative field,it takes the five-satellites co-location as an case to study the multi-satellites co-location isolation program design,based on the study of multi-satellite co-location development,the specific work is as follows:Gave description of the relative motion of the geostationary satellites by using Non-singular Point Number of geostationary orbit;Deduced the Relative Motion Equations of the satellites;Introduced the segregation strategies of the multi-satellite co-location and also simulated the different isolation strategies and Introduced the segregation strategies of the multi-satellite co-location and also simulated the different isolation strategies.Deduced the Lagrangian equations for non-singular point number as well as different orbital roots;Studied the influence of the perturbation force on the orbital elements.Analysed the influence of the drift rate vector difference,eccentricity vector difference and inclination vector difference on the multi-satellites co-location isolation strategy,and the results are verified by simulation.Besides,analysed the theory of multi-satellites co-location design;Designed strategies for five satellites co-location based on three different conditions:Eccentricity and inclination joint isolation strategy fully connected configuration,eccentricity vector isolation fully connected configuration and eccentricity vector isolationlinear configuration.Tested these designed strategies by simulation and analysis.