考虑战机非线性运动建模中推力矢量、非定常气动力等因素,建立了适合战机大迎角机动纵向动力学模型和非定常气动力模型,采用数值仿真对速度、平尾偏角、推力矢量舵偏角及俯仰角速度动态特性进行了分析。基于某型战机大迎角机动的仿真结果表明:各参数的变化符合实际情况,能够有效地反映真实机动状态,为大迎角机动飞行操稳系统的设计提供了依据。 Considering the thrust vector, unsteady aerodynamic forces and other factors in non-linear fighter modeling, a longitudinal dynamic model and unsteady aerodynamic model suitable for fighter aircraft at high angles of attack are established. The numerical simulation of velocity, tail angle, thrust vector rudder Declination and pitch angular velocity dynamic characteristics were analyzed. The simulation results of maneuvering at a high angle of attack of a certain type of fighter show that the change of each parameter is in accordance with the actual situation and can effectively reflect the real maneuvering condition, which provides the basis for the design of maneuvering flight stability system at high angle of attack.