论文部分内容阅读
论述了SMI(structural mode interaction)试验接口控制器的详细设计和分析过程,以及其在全机地面结构模态耦合试验中的应用。SMI接口控制器是在全机地面结构模态耦合试验中用于向飞控系统主作动器电子控制装置注入信号和取出信号的试验设备,并用来测定有控飞机(受飞控系统控制的飞机)的伺服弹性稳定性是否满足相应适航条款的要求。SMI接口控制器已多次在某型号飞机全机地面结构模态耦合试验中得到应用,得到了可靠的试验数据,其设计原理可广泛应用于电传飞控系统飞机的多种系统大回路闭环试验,用来分析与验证飞机伺服弹性稳定性。
The detailed design and analysis process of SMI (experimental mode interface) experimental interface controller and its application in modal coupling test of whole ground plane structure are discussed. The SMI interface controller is a test equipment used to inject signals into and take out signals from the main actuator electronic control unit of the flight control system during the modal coupling test of the whole ground structure and is used to test whether the controlled aircraft (controlled by the flight control system Aircraft) whether the servo flexible stability meets the corresponding airworthiness requirements. The SMI interface controller has been applied to the modal coupling test of the whole aircraft ground structure of a certain type of aircraft on many occasions and the reliable test data has been obtained. The design principle can be widely applied to a variety of system large loop closed loop Test, used to analyze and verify the aircraft servo elasticity stability.