Research On Architecture And Control Method Of Spacecraft Formation

In the past two decades, the world’s space agencies have carried out the taskof planning and research of the spacecraft formation. Formation for thecontinuous development of technology, more and more spacecraft flying information. Architecture and control of spacecraft formation will become morecritical to system structure and control methods for large-scale spacecraftformation to commence the discussion and research of the following aspects:Nonlinear dynamic equations of the spacecraft relative orbital motion, andon this basis, the linearized Hill equation and its analytical solution. According tothe analytical solution of the spacecraft close relative movement around theflying characteristics, ease of algorithm design of the subsequent chapters.On the basis of analysis of conventional spacecraft formation architecture, ahybrid virtual structure formation architecture description. Specifically, the use ofthe virtual structure of the entire fleet as a rigid body description of the relativeposition and velocity. Then, in the analysis of the master of the traditionalspacecraft formations and distributed architecture based on, based on the virtualmulti-layer structure of thinking main/distribution combination of hybridarchitecture in order to overcome the traditional deficiencies of the master-slaveand distributed architecture.For natural orbit around the fly any flying around the track, different flyround the track the location of double pulse-based control algorithm to maintain.The retention of the natural fly round the track position, Hill equation-basedanalytical solution to calculate the specific location and size of the two pulse isapplied, and a number of pulse adjustment method is given for generalperturbation location. Orbital position to keep any flying around, based on thematrix form of the double-pulse method, consider that with the given two pointsof the initial and final position, velocity, calculate the pulse size and thesimplification of the algorithm. The simulation results show that the designalgorithm can meet the position of the orbit of the fixed flying around to keep.Orbit uncertainty and control input uncertainty and other factors, the designof robust control of spacecraft flying around a small thrust orbit transfer.Algorithm design, it will fly round the orbit transfer problem is transformed intomulti-objective control problem, using linear matrix inequalities controller solving. The simulation results show that the designed control law enables thespacecraft to achieve the corresponding fly around the inter-orbit transfer, and hasgood robustness.