Based on classical terrain following (TF) algorithm (adaptive angle method), a new method for TF controller is proposed by using angle of attack. A method of obtaining terrain outline data from Digital Elevation Map (...Based on classical terrain following (TF) algorithm (adaptive angle method), a new method for TF controller is proposed by using angle of attack. A method of obtaining terrain outline data from Digital Elevation Map (DEM) for TF control is discussed in order to save store space. The block control model, which is suitable for backstepping design, is given for nonlinear model of aircraft. Making full use of the characteristics of the system and combining block control principle, backstepping technique, a robust controller design method is proposed. Uncertainties in every sub-block are allowed, and can be canceled by using the idea of nonlinear damping. It is proved that the state tracking errors converge to the neighborhood of the origin exponentially. Finally, nonlinear six-degree-of-freedom simulation results for the aircraft model are presented to demonstrate the effectiveness of the proposed control law.展开更多
以可控飞行撞地(CFIT,controlled flight into terrain)事件类型信息为研究对象,依照基元事件分析法分析CFIT事件演化过程,建立了事件后果层—飞机状态层—诱发因素层三层贝叶斯网络结构模型。以2017—2019年中国民航收集的CFIT事件和...以可控飞行撞地(CFIT,controlled flight into terrain)事件类型信息为研究对象,依照基元事件分析法分析CFIT事件演化过程,建立了事件后果层—飞机状态层—诱发因素层三层贝叶斯网络结构模型。以2017—2019年中国民航收集的CFIT事件和航空安全网(ASN,Aviation Safety Network)近20年(2000—2019年)CFIT事件数据为样本,利用样本统计数据确立网络节点参数,采用GeNIe软件选取贝叶斯网络已知节点与目标节点进行量化分析,得到目标节点可能性排序、最大可能性目标节点及影响强度;最终得出该类事件的关键风险环节,即飞行高度控制、机组丧失情景意识、飞行保障及相应节点的量化结果,为加强此类事件风险控制提供数据支持。展开更多
文摘Based on classical terrain following (TF) algorithm (adaptive angle method), a new method for TF controller is proposed by using angle of attack. A method of obtaining terrain outline data from Digital Elevation Map (DEM) for TF control is discussed in order to save store space. The block control model, which is suitable for backstepping design, is given for nonlinear model of aircraft. Making full use of the characteristics of the system and combining block control principle, backstepping technique, a robust controller design method is proposed. Uncertainties in every sub-block are allowed, and can be canceled by using the idea of nonlinear damping. It is proved that the state tracking errors converge to the neighborhood of the origin exponentially. Finally, nonlinear six-degree-of-freedom simulation results for the aircraft model are presented to demonstrate the effectiveness of the proposed control law.
