Abstract: There are defects in the pose movement simulation of vertical launching aerocraft which can circumrotate continuously in yaw with three -axis flight motion simulator. Based on analysis of these defects, a four-axis project which could be applied to the situation of the changing range of vehicle pitch pose and vehicle roll attitude more than ±180° and the changing range of vehicle course pose towards infinite greatness was proposed. The structure of the four-axis flight motion simulator was analyzed and the control model was made. Above all, a four-axis concerted control law was designed with" switching movement mechanism", and a smooth switch measure in the control process of flight motion simulator was designed too, then the result was validated with simulation. A continuous, real-time and high-efficient simulation method for the pose movement of vertical launching aerocraft which could circumrotate continuously in yaw was confirmed.

Key words: vertical launching, four-axis flight motion simulator, switching movement mechanism, concerted control law