Turnover and tail end control semi-physical simulation test method

The invention relates to a turnover and end control semi-physical simulation test method, which comprises the following steps of: designing corresponding control logic according to control requirements of different stages of an aircraft; in the initial launching stage, inertial smoothing is carried out on a course angle, a pitch angle, a course sight angle and a pitch sight angle; in the terminal guidance stage, exponential smooth transition processing is carried out on the roll angle according to a certain rule according to the missile-target distance; and in a tail end attack stage, according to the course sight angle and the pitching sight angle variation, the course sight angle and the pitching sight angle are re-assigned so as to control the course sight angle and the pitching sight angle of the five-axis turntable. According to the invention, the problem that the aircraft cannot be subjected to turnover maneuvering and end attack simulation due to limitation of rolling frames of the five-axis turntable