某型飞机非线性动力学特性的分叉分析

Bifurcation Analysis of a Nonlinear Dynamics Aircraft Model

针对某静不稳定飞机的非线性动力学模型 ,采用分叉与突变理论 (BACTM)计算了常规控制面变化的飞机本体平衡曲线 ,揭示了其固有的在大迎角下的开环运动特性。在此基础上 ,设计纵向增稳系统 ,以保证飞机在小迎角下具有良好的操纵特性 ,然后再用 BACTM分析预测其大迎角下的闭环运动特性。结果表明 ,其具有与静稳定性飞机类似的预测结果。

Bifurcation Analysis and Catastrophe Theory Method (BACTM) was applied to a nonlinear dynamics model of an inherently static unsteady aircraft to calculate the equilibrium curve while regular control surfaces deflected. The results show the basic information about open loop kinematical characteristics under high angle of attack. Further work was performed to design a pitch control augmentation system in order to ensure good maneuverability under regular angle of attack. Again BACTM was used to reveal the closed loop kinematical characteristics under high angle of attack and the outcome is similar to static steady aircraft.