蜂窝夹层复合材料舵面对FES激励的动力学仿真技术

Dynamic Simulation of an On-Aircraft FES Test Conducted to a Control Surface with the Composite Material and Honeycomb Sandwich Structure

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 (Flight Excitation System) test is conducted to excite the aircraft structure in terms of servo actuator whose input signals is send from the FES system installed on the aircraft. This report describes a new system composed of a composite control surface with honeycomb sandwich structure and a servo actuator. The mathematics model of the actuator is simplified as a tow power linear system. Having built the dynamic model of the control surface, the MSC/NASTRAN is applied to perform the dynamic simulation for a on aircraft FES test of the control surface. By investigating the analytic results, the vibration property of the system is completely obtained. Also the sensitive factor by means of dynamic response for the composite material control surface with honeycomb sandwich structure is found. All results can be treated as an important reference used both in the on aircraft FES test of the control surface and in its vibration suppressing work.