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FES (FlightExcitationSystem)试验是通过机上FES系统产生激励、并借助伺服作动器输出舵面偏度信号 ,由此达到激励飞机结构的目的。本文针对蜂窝夹层复合材料舵面与伺服作动器所组成的新系统 ,将伺服作动器的数学模型简化为二阶线性系统 ,同时建立舵面的动力学模型 ,应用MSC/NASTRAN成功地实现了对舵面机上FES试验的动力学仿真。通过分析 ,全面了解和掌握了该系统的振动特性 ,并从中找出对蜂窝夹层复合材料舵面动力响应最为敏感的因素 ,为进一步指导舵面机上FES试验、有效抑制舵面振动提供了重要参考。
FES (FlightExcitationSystem) test is to generate incentives through the on-board FES system, and output the rudder deflection signal with the servo actuator to achieve the purpose of exciting the aircraft structure. In this paper, a new system consisting of a honeycomb sandwich composite servo surface and a servo actuator is proposed. The mathematical model of the servo actuator is simplified to a second-order linear system. At the same time, the dynamics model of the control surface is established. The application of MSC / NASTRAN Dynamic simulation of FES test on rudder machine. Through analyzing and understanding the vibration characteristics of the system and finding out the most sensitive factors to the dynamic response of the honeycomb sandwich composite surface, it provides an important reference for further guiding the FES test on the rudder machine and effectively suppressing the rudder surface vibration .