Based On Dsp Technology, The Skin Of The Satellite Attitude Control System Design And Realization

Since the concept of microsatellite was proposed in the 80's 20 centuries, it's techniques have made great processs in recent years, the development of which is a significant trend in the aerospace area. The microsatellite characterized with light weight, good performance, short development cycle and low cost. As a key section of microsatellite, the microsatellite attitude control system should have the feature of simple configureation, light weight, long working time and high reliability. In this paper, the methods of attitude controlling and stabilization are systematically studied and validated experimentally.The final goal of this system is an efficient, low energy-cost, three-axis stabilized attitude controlling system and the current task is to design a reasonable scheme and to realize a single-axis prototype machine. Because of the naraowness of the space and shortness of the energy, during designing this system, we must consider these two factors. The system chooses an MEMS bias momentum flywheel as main executing apparatus, four tiny-thrustors to reload the momentum and a three-axis magnetic-coil as a subsidiary apparatus. The system derectly chooses the six solar chip-batteries as solar sensors and a three-axis magnetometer to measure three axises' magnetic strengths. The main control board, which takes charge of gathering information and determining satellite's attitude and computing attitude deviation and driving various apparatuses to adjust and stabilize satellite, is designed based on DSP and other digital circuit techniques.In this paper, we first introduce the procedure of designing main controlling board based DSP and other digital circuit techniques. Through studying the relationship of solar batteries' power outputs and angle of incidentce of the luminous source, which simulates the sun, the method is obtained to determine and compute the angle, rotational speed and angular acceleration of the satellite relative to the sun. Utilizing the attitude information, main controlling board drives the bias momentum flywheel to adjust and stabilize the satellite's attitude. Finally, a project of single-axis attitude controlling and stabilization for the pico-satellite is designed and verified on the experimental platform, which is specially designed.