Input parameter determination method for calculating yaw direction rotation dynamic derivative of aircraft

The invention discloses an input parameter determination method for calculating a yaw direction rotation dynamic derivative of an aircraft, and relates to the technical field of aerospace aircrafts. According to the method, input parameters such as different rotation center coordinates and incoming flow conditions are determined through calculation, and rapid calculation of the yaw direction rotation dynamic derivative of the aircraft in different attack angle and sideslip angle combined states under the same calculation grid can be achieved through a calibration calculation method based on a rotation coordinate system. According to the method, the working efficiency of the whole calculation process of the rotation dynamic derivative in the yaw direction of the aircraft is improved, and wrong input parameters are reduced. 本发明公开了用于飞行器偏航方向旋转动导数计算的输入参数确定方法，涉及航空航天飞行器技术领域；该方法通过计算确定不同旋转中心坐标和来流条件等输入参数，可以帮助基于旋转坐标系的准定计算方法实现在同一套计算网格下不同攻角和侧滑角组合状态的飞行器偏航方向旋转动导数快速计算。该方法提高了飞行器偏航方向旋转动导数整个计算流程的工作效率，并减少了错误的输入参数发生。