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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。
In modern large commercial civil aviation aircraft, there are vibration faults caused by internal electronic equipment failures and structural self-vibration. However, the existing solutions require a large number of sensors and controllers, which leads to very complicated control structures and derivative failures. In order to solve this problem, based on the mathematic model of aircraft control loop including commercial civil aviation aircraft servo system, the fault analysis is carried out by using its analytical redundancy. At the same time, the residual error of the servo loop is analyzed and the residuals of dynamic state variables are designed Feedforward channel / feedback channel combination of control rules, simplification of the traditional multi-notch structure of the telex control system. The simulation results show that the control law designed based on the analytical redundant fault detection method of large commercial commercial light aircraft can effectively solve the problem of aircraft vibration failure at all frequencies without adversely affecting the pilot’s normal operation. For large commercial aircraft control law designer to provide a reference.