Abstract: Laser micro-thruster has become one of the affordable power system options for micro-nano-satellites due to its high specific impulse, low thrust level, small size, low power consumption and high reliability. In view of the influence of laser ignition position and ignition sequence on the attitude of nano-satellite platform during the thrust output of solid fuel tape laser micro-thruster, the attitude dynamics equation based on laser ablation moment was established, and the relationship between attitude angle and its angular velocity with time was simulated and analyzed. The simulation results show that,the laser ignition sequence of micro thruster can be divided into two kinds:symmetrical on both sides and continuous output and symmetrical on both sides and spacing output, the effects of the two modes on the attitude of the nano-satellite are different. However, whether the laser ablation moment was from large to small or from small to large, the moment symmetrical and continuous output has the least impact on the attitude. This lays the foundation for the application of attitude stability control of micro-nano-satellite.