The Coordinated Attitude Control For The Formation Flying Of Satellites

The formation flying of satellites can make several satellites work together to form a huge"virtual satellite"which performs the same functions as a single big spacecraft with the large aperture or the long baseline. Moreover, it can not only bring down the cost and risk obviously, but also eliminate the impact of the satellite malfunction on the space mission. More and more people pay much attention to the research of it now. It will play an important role in many fields such as the electronic reconnaissance, three-dimensional imaging, satellite remote sensing, navigation etc. Researching work as follows about the formation flying of satellites has been done in the thesis.At first, the paper overviews the development of formation flying of satellite. It also investigates the current situation in the aspect of coordinated attitude control of formation flying satellite at home and abroad.Several common description methods of satellite attitude are analyzed, including their definition, the conversion relationship between them, their advantages and disadvantages, and the attitude matrix made up of them respectively. According to the actual problem should be solved, the description method of attitude quaternion is adopted to do our research. For some earth-observation three-axis stabilization satellite, Several usual reference coordinate for studying the motion of satellites are defined, the paper derives the transformation relationship between them. Based on the quaternion method, the attitude dynamical equation of rigid body satellite is established.After that, the attitude stabilization algorithm of single satellite based on quaternion method is studied. the Lyapunov stabilization theory is utilized to prove the global stabilization of the attitude stabilization control law we have designed. Numerical simulation is carried out. The simulation results validate further the efficiency of the control law the paper has designed. In addition, the paper defines the error variables of attitude quaternion, and on the basis of them, it investigates the attitude tracking algorithm of single satellite. The Lyapunov stabilization theory is utilized to prove the global stabilization of the attitude tracking control law we have designed. The paper carries out numerical simulation. The simulation results validate further the efficiency of the control law the paper has designed.Finally, taking the three satellites formation flying for instance, the paper adopts the leader-following attitude coordinated control strategy. The desired attitude algorithm of the following satellites in the formation is studied, and is validated using three-dimensional visualization. Through numerical simulation and visualization simulation, the efficiency of attitude coordinated control law the paper has designed is validated. The simulation results show that the following satellites could track their desired attitude every moment, in other words, the goal task of the coordinated attitude control for the formation flying of satellites can be realized.