Study On Attitude Control Methods Of Deep Space Explorer

For deep space explorer, the attitude control system design methods were studied in this dissertation, which is funded by the National 863 Plan (2004AA735080),"Autonomy Technology and Simulation Demonstration System for Deep Exploration". The main contents of this dissertation consisted of the following parts:The dynamics mathematic model for the deep space explorer is building up. The compositions and features of environmental torques were analyzed during interplanetary cruise period. The result shows that the solar radiation pressure moments play a mainly part.Based on Kalman filtering, three kinds of attitude determination algorithms were studied using the attitude sensor now available on the explorer: the first based on digital solar sensor (DSS) and gyroscope when the star sensor is not available; another based on DSS, high-gain antenna (HGA) and gyroscope when the explorer is in the earth-safe mode; the third based on star sensor combined with gyroscope when the explorer is in the normal mode. The simulations show that these algorithms can partly or fully achieve the estimations of the explorer attitude and the gyroscope bias when satisfying some conditions.The attitude control system using reaction thrusters is studied. Based on phase plane theory, PD control law, time-optimal control law and time-fuel optimal control law were designed. Characteristics and application conditions of these laws were compared in simulations. The quaternion feedback control laws was studied for the three-axis stabilization control using reaction wheels, a design method for the PID controller parameters was presented and the simulation results indicated that the control algorithm works efficiently.Designed semi-physical simulations emphasized on attitude determination algorithm based on star sensor combined with gyroscope, bang-off-bang time-optimal jet control algorithm, and quaternion feedback control algorithm using flywheel. In the attitude determination experiment, star sensor hardware is introduced into the control loop to correct the gyro bias. In the attitude control experiment, firstly using reaction thrusters to perform large-angle slew and then...