The Interrelated Technique Research For Formation Flying Of Micro-satellites

Almost all advanced techniques obtained in aerospace domain up to now are being concentrated in the formation flying of micro-satellites and it's interrelated techniques. As early as 90's in 20 centuries, NASA has regarded formation flying of micro-satellites and it's interrelated techniques as the available key technique in the future. China succeeded in launching the navigation and orientation satellites of Beidou No.1 and Beidou No.2 in "95" period, which established the technique foundation for the development of our country's formation flying of micro-satellites.However, the researchful time of formation flying of micro-satellites in the world is only more than ten years, many aspects were needed to be consummated. Our country and all the other countries are looking for the new breakthrough actively. Based the obtained achievement, this paper established a mathematics model, obtained many terse computational methods in the equation of relative orbit,the design of formation flying in three-dimensional orbits,the influence of perturbation,the analysis of surface coverage and etc.In the second section, this paper establishes three reference frames, under the assumptive condition of reference satellite moving in a circle orbit and surrounding satellite moving in a near circle orbit, surrounding satellite and reference satellite were located in the same reference frame by two times circumvolving of reference frame, and then a relative position dynamic equation for surrounding satellite and reference satellite was derived by the method of subtraction according to kinetic relationship.Utilizing the relative position dynamic equation, and then the surrounding satellite's motion was separated into two simple parts, after the initialization of the reference satellite's orbital elements, this paper designs the configuration of formation flying in three-dimensional orbits, and a set of calculated formulas of surrounding satellite's orbital elements were deduced.The relative position dynamic equation and the design of the configuration of formation flying in three-dimensional orbits were gained in the perfect situation , however, many kinds of perturbation will affect the structure of formation flying in fact. So this paper analyzes the influence of perturbation from two aspect of the relevant configuration and the integral absolute location of the formation in the fourth section, and then this paper brings forward a method to eliminate the affect of J2 perturbation and atmospheric drag perturbation to the formation flying by put an impulse on satellites.After controlling of formation flying, this paper analyzes the main application of formation flying in the fifth section. It is the surface coverage for satellites formation flying. A set of calculational formulas were advanced in this section, for example, the maximal coverage angle,the minimal coverage angle,the belt width of coverage and the total time,the total amount of circles needed for global coverage of the satellites formation flying.This paper gives many simulations at the end of every section, the results of the simulation prove that these technique bring forward in this paper are feasible and compact. These formulas and researchful methods can be served as reference for other kinds of researches about formation flying systems of micro-satellites.