大型商用民航飞机振动故障控制律研究与设计

Control Law Research and Design of Large Commercial Civil Aircraft for Oscillatory Failure

现代大型商用民航飞机存在由于内部电子设备故障以及结构自振引发的振动故障,而现有的解决方法需要运用大量传感器以及控制器,这导致控制结构变得非常复杂和衍生故障的发生。为了解决这一问题,基于包含商用民航飞机伺服系统在内的飞机控制回路数学模型,运用其解析冗余进行故障分析;同时基于伺服回路解析冗余残差以及动力学模型状态量残差设计了前馈通道/反馈通道组合控制规律,改进简化了传统电传操纵系统中的多陷波结构。仿真结果表明:基于大型商用明航飞机的解析冗余的故障检测方法而设计的控制律可以有效解决各个频率下的飞机振动故障问题,同时不会对飞行员正常操纵带来不利影响。可为大型商用民机的控制律设计者提供参考。

The oscillatory failure often occurs because of the electronic equipment failure or the structure vibration in the modern commercial civil aircraft. The solution to the problem needs lots of sensors and control controllers and it make the control structure complex and leads to further fault. The mathematical model including the servo loop was built and the analytical redundancy was used for the fault detection. A combined control law was designed based on the detection result that was the residual of the servo signal and the state quantities. The design improves the control structure of the EFCS feedforward channel and the simulation result shows that the problem of the oscillatory is well solved. It provides reference for the designer of the commercial civil aircraft.