Research On Jet System For Attitude Control Of Digitial Satellite

Space technology is the most influential technology of modern science andtechnology. With the development of space technology, many kinds of satellites arecreated to complete different tasks, and the functions are becoming more and morepowerful. Attitude control system is an important part of satellite, and the performancesof high accuracy, durability and fast response become the focus.In this dissertation, the attitude control system using reaction thrusters of digitalsatellite based on phase plane theory is deeply studied theoretically and practically forthe attitude control of the three-axis stabilized satellite. The main contents of thisdissertation consist of the following parts:First, whole mathematical model about attitude control system of satellite isfounded. The attitude description of Euler Angle are analyzed and generalized. Then theattitude kinematics and dynamic models are developed. The basic theories are alsointroduced.Considering time-optimal control and time-fuel optimal control law and thedifferent control requirements, phase plane divisions are designed in detail. It is provedthat each area is efficient according to the simulation. Compared with analog controllaw and the results show that within required accuracy range the digital control law canform the longest period one-sided limit cycle against the effect of the variabledisturbance. So the system is robust and adaptive to a certain extent.A kind of estimator is given in this article to solve the problem that the disturbanceangular acceleration is measureless, and the simulation results show that high accuracydisturbance acceleration is achieved with this estimator.Finally, numeral results for three-axis stabilized satellite are provided todemonstrate the effectiveness of the control algorithm.