Abstract: Based on dynamic theory of systems of rigid bodies, a six degree freedom motion equation of aircraft body and gear is formulated. The control characteristics of the pilot during landing task with right side wind are analysed. Three axes pilot maneuver logic is proposed. By the method of collecting and processing the flying stale information and controlling the aircraft at separated time, three single axis pilot control models are used to describe pilot's three axes control at one moment. Based on three axes pilot aircraft closed loop system model, the dynamic simulation software during landing task is programed. The dynamic qualities of some verifier during landing'task are evaluated, and the numerical simulation results agree well with the real flight test data.

Key words: right side wind, three axes control, dynamic qualities during landing task