Abstract: This paper proposes a joint attitude control algorithm using MEMS solid propellant thruster array and magnetic torquer to tackle the issues of low torque outputs and slow attitude response in the conventional pico/nano-satellite attitude control systems. The novel approach improves the control accuracy and shortens the system response time. The stability of the proposed algorithm is proved by using the Lyapunov stability theory. An optimized ignition model of the MEMS solid propellant thruster array is established. The compensation time setting method is provided. Then, the control laws for large angular velocity damping and auxiliary velocity damping are proposed, as well as the joint control law for attitude acquisition based on the hybrid system model. Finally, the effectiveness of the velocity damping joint control law and joint control law for attitude acquisition is verified through simulation. The simulation results demonstrate that compared with the conventional magnetic torque control approaches, the proposed joint control scheme effectively improves the control accuracy and shortens the system response time.

Key words: MEMS solid propellant thruster array, Magnetic torquer, Attitude control