Abstract:

The output moment of the reaction wheels utilized in the attitude control system of the microand nanosatellites is too small to overcome the disturbance torque of the air bearing table. To solve this problem and experimentally verify the attitude control system, the disturbance torque is required to be compensated for. Thus, the disturbance torque is classified and analyzed and the compensation methods are proposed accordingly. An air bearing table with supper low disturbance torque is constructed, based on which the hardware in loop simulation system for attitude control system of micro- and nano-satellites is developed. Experimental results demonstrate that the disturbance torque is 2×10^-5 Nm, and it is smaller than the minimum output of the reaction wheels. The verification of the large angle attitude maneuver control algorithm of the micro- and nano- satellites is completed by the simulation platform effectively.