Design of Spacecraft Attitude Control Physical Simulation System Based on New DSP Controller

Abstract

In this paper, the hardware and software experiment system of the large angle maneuver of the satellite attitude is designed and realized according to the requirement of the professional construction. The composition includes: single axis turntable, a nitrogen source, the new DSP controller, model simulator, router, multi-channel rechargeable power supply system and battery, fiber optic gyro, flywheel, jet system, computer and printer etc. Attitude maneuver control method is PD control. The controller uses DSP SEED-DEC28335. The control experiment program is developed by using C language. Its research characteristic is to realize the wireless data communication between PC and DSP. The CCS compiler v5.5 and the operating system Windows 8-32 bits. The experimental results show that the large angle attitude maneuver simulation of the satellite based on flywheel is accomplished. The rotating angle range of the turntable is ±90 degrees. The accuracy of maneuver is less than 0.5 degrees and meet the simulation mission requirements.