Control Method Of Flexible Satellite Attitude Maneuvering

There are more and more flexible appendages such as solar panels and flexibleantenna on spacecraft now. These flexible appendages have serious impact on theposture and movement of central rigid body. So it will have important practicalsignificance on the study of attitude control of this group of spacecrafts. The problemof Maneuver Control of the flexible satellite will be detailed studied in this article on aSatellite with individual flexible solar panels. The mathematical modeling aboutSatellite with individual flexible solar panels, problems about attitude control andposture stability of flexible satellite will be included in this research.First of all, using a coordinate system mixed with inertial coordinate system andnon-inertial coordinate system, the principles of the physical dynamics and modalanalysis to establish the kinetic equation of the flexible satellite with individual solarpanels, and converted it to the standard state in the form of the space equation. Andquantitative analysis of the coupling between the central rigid body and solar panelsand qualitative analysis of the uncertainty of kinetic model and it’s parameters wasmade.Second, PID control law was used to solve the problems about attitude control andposture stability of flexible satellite firstly. So, a PD controller was designed for thismodel and the simulation was analyzed. Then a common variable structure controller,quasi-synovial variable structure controller and variable structure controller based onreaching law were established, and they were applied to the flexible satellite model.Compared the simulation characteristics of the three types of variable structurecontroller above and PD controller, and detailed analyzed the inherent chatteringphenomenon of variable structure control law.Third, as the result of the uncertainty in the system dynamics model and theinherent chattering phenomenon of variable structure control law, the fuzzy variablestructure control law which combined fuzzy control and variable structure control lawwas put forward. The aim was to combine the advantages of both to make goodcontrol of the attitude maneuver of flexible satellite. Ordinary fuzzy variable structurecontroller and fuzzy variable structure controller based on reaching law which adaptedto the model built above were designed, and the simulations was analyzed. Finally, make analysis and design of the physical simulation experiments ofattitude control of the Satellite with individual flexible solar panels control. Includingthe analysis of the need and feasibility for the system of this physical simulationexperiment, and single-axis air bearing table, the flexible simulator of flexible solarpanels, the control law improvement, and software design of this experimental systemwas introduced.