Design Of Control S Ystem For Fast Large Angle Satellite Attitude Maneuver

The level of Astronautic technology is an important symbol of comprehensive national strength and the whole science and technology capacity. As a top item of Astronautic technology, outer space detection is the obligatory choice of Chinese Astronautics.Fast large angle satellite attitude maneuver has great development space in military reconnaissance, communication and space exploration satellites. And it has become an important evaluation of modern spacecraft performance. Based on the background of Chinese first Mars detector this paper mainly researched the technology of attitude maneuvers and target location.Premise for satellite attitude control is to select an appropriate gesture description method. Firstly several definitions attitude reference coordinate system were given. Then the basic gesture description methods were introduced. Based on above knowledge the dynamics and kinematics model of satellite attitude were established especially the derivation based on quaternion method. Detailed analysis of model uncertainty caused by disturbance torque was made on the basis of dynamic foundation, which laid the root for the design Maneuver Control System.By analyzing the relative advantages of the Euler and quaternion method, quaternion method were selected as control method in the research of fast large angle attitude maneuver. In this paper the mathematical model of large angle attitude maneuvers was built on the arbitrary target attitude reference design of typical near-Earth satellites. Then the maneuver problem can be converted into a regulation problem of adjusting the error of quaternion. And based on a typical attitude sensor configurations, a gyro integral attitude determination method was designed when the star sensor was unavailable during the process of attitude maneuver.According to the large angle attitude maneuver model the control algorithm was designed based on the idea of variable structure control. For traditional sliding mode has obvious shortcomings that it can only provide limited maximum torque and control time in practical application. This paper presents variable structure controller design based on the non-equivalent control. And the stability of the algorithm were also discussed.Finally considering the design of arbitrary target large angle maneuver control attitude reference and the control law of variable structure fast maneuvering simulations were made. The simulation results show that the design of reference attitude is reasonable and feasible. The maneuver control law has strong robustness and excellent dynamic performance with system parameter perturbation and external disturbance.