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 design and analysis process of structural mode interaction test interface box(SMI-TIB) are illustrated and its practical application in structural mode interaction (SMI) testing of full-scale airplane is also discussed in detail.In full-scale airplane SMI testing,SMI-TIB is designed as a test equipment to provide instruments' vibration input/output signal access to primary actuator electronic control units of airplane flight control system,to verify the servo elastic stability of airplane engaged by flight control system whether meeting airworthiness items requirements.SMI-TIB has been used frequently in SMI testing for a type airplane,the reliable test data with few noises are provided,which also can be used in other system level closed-loop performance testing for airplane to analyze and verify the servo elastic stability of airplane.
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