Study On Spacecraft Motion Compensation Based On Three-Axis Stabilized Scan Imager Satellites

The dissertation, taking the image navigation and registration (INR) of the second generation meteorological satellite as an example, studies systematically and thoroughly the design and realization of the spacecraft motion compensation system for the meteorological and three-axis stabilized satellite. Spacecraft motion compensation method and mathematic simulation is designed. Some further research is done in the field of the physical simulation, algorithms errors of spacecraft motion compensation. The main work done in the dissertation is as follows:1. Based on the controlled motion character of the scan mirror at first,the scan mirror was considered a momentum equipment connected with satellite by stepping axle and scanning axle. The dynamic motion equations of three-axis stabilized satellite coupled scan mirror were established, and the mathematical model of moment coupling between satellite attitude motion and scan mirror turning was deduced.2. On the basis of above research works, the spacecraft motion compensation design was described. The satellite attitude is gained in real time from the measurement value of gyros and star sensing, and according to measurement value of scan mirror turning angle, the compensation signals was computed by onboard computers . The compensation signals ware sent to cameras control system. The simulation results demonstrate the feasibility of SMC designed in this part.3. The problems on physical simulation of spacecraft motion compensation is researched and solved. The problems include time delay, time synchronization and evaluating method of the physical simulation results.4. Software and hardware design. The program is design to solve the problems on physical simulation with the hardware.