【摘要】 本文以分歧突变理论和微分方程定性理论为基础,建立了求解分歧面的完整的数学方法。根据分歧面提供的信息,制订了使飞机进入尾旋和改出尾旋的控制律,并给出了一定的物理解释,为从理论上研讨飞机在大迎角时的操纵规律进行了有益的尝试。所得结论经时间历程检验正确无误,与试飞结果一致。更多还原

【Abstract】 This thesis uses the theory of Bifurcation Analysis and Catastrophe to study spin maneuvers. Algorithm of Bifurcation Surfaces has been presented in considerable detail. According to Bifurcation Surface, the control law of bringing planes into spin and retiring has been worked out. Some physical explanations have been given. The thesis tries to study the control law of planes at high angle of attack by means of a new theory. The Tightness of resulting conclusions have been confirmed by the time history and the flight test.更多还原