面对称高速飞行器横侧向耦合失控特性

针对面对称高速飞行器滚转-偏航通道间存在的运动耦合、典型气动耦合和控制耦合，建立了耦合动力学模型，推导了耦合模态的数学描述；提出了基于滚转偏航/稳定比和副翼滚转/偏航操纵比的耦合模态分析方法，分析了副翼操纵对偏航通道的耦合影响程度；针对控制耦合引起的非最小相位特性，提出了基于偏航稳定力矩导数、副翼-偏航耦合力矩导数以及方向舵产生偏航力矩导数的控制耦合偏离边界条件，根据偏航稳定力矩导数、副翼-偏航耦合力矩导数的相对位置关系，确定控制耦合偏离区域，并分析了副翼控制滚转时的耦合失控特性.最后对失控特性进行了仿真验证，结果表明了耦合特性分析方法的有效性. 

Coupled Control Departure for Plane-Symmetrical High Speed Vehicles

In order to analyze the coupled lateral-directional dynamics of plane-symmetrical high speed vehicles, the coupled model was built, which involves kinematic coupling and aerodynamic coupling and control coupling. The analysis method for coupled dynamics was proposed, which is based on two parameters: the ratio of rollingmoment coefficient versus sideslip to yawing moment coefficient versus sideslip and the ratio of aileron effect on rolling moment to yawing moment. Due to the cross-control effect, the system has non-minimum phase behavior. The criterion of control departure was deduced, which involves yawing moment coefficient versus sideslip and aileron cross-control effect on yawing moment and rudder control effect on yawing moment. The characteristics of coupled mode and control departure were analyzed. Simulation results show that the method is reasonable.