Real-Time Hybrid Simulation (RTHS) is an experimental framework that allows the testing of components or substructures under realistic, dynamic boundary conditions, by imposing the reactions calculated from a model of the rest of the assembly through one or more actuators. In the context of rapid prototyping of mechanical components, RTHS could be used to explore the design space of a device while at the same time physically validating its interaction with other components of the final assembly from the early stages of the design-to-production cycle. In this work, RTHS was applied for the first time to the investigation of aerodynamic gust loading alleviation devices in a highly flexible strut-braced wing. The model wing was taken as the physical substructure and tested in a low-speed wind tunnel equipped with gust generators. The load alleviation device was simulated through a real-time feedforward-feedback controller, and its response imposed via an electro-mechanical linear actuator, in contrast with the hydraulic actuators more commonly used in standard RTHS. The controller-actuator subsystem was studied in detail to assess and minimise errors at the physical interface with the wing. The behaviour of the electromechanical subsystem showed a strong dependence on the characteristics of the numerical substructure and the frequency of excitation, and resulted in a significant discrepancy between the simulated and real displacements at the interface between the actuator and the wing. A narrow-band feedforward displacement control scheme based on a model of this subsystem alone was therefore developed and shown to significantly reduce synchronisation errors at the interface.

中文翻译：

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使用电动执行器在气动载荷下对支柱支撑机翼进行实时混合测试

实时混合仿真 (RTHS) 是一种实验框架，它允许在真实的动态边界条件下测试组件或子结构，方法是通过一个或多个执行器施加从组件其余部分的模型计算出的反应。在机械部件的快速原型制作的背景下，RTHS 可用于探索设备的设计空间，同时从设计到生产周期的早期阶段物理验证其与最终组装的其他部件的交互. 在这项工作中，RTHS 首次应用于研究高度灵活的支柱支撑机翼中的气动阵风载荷减轻装置。以模型机翼为物理子结构，在配备阵风发生器的低速风洞中进行测试。负载减轻装置通过实时前馈反馈控制器进行模拟，其响应通过机电线性执行器施加，与标准 RTHS 中更常用的液压执行器形成对比。详细研究了控制器-执行器子系统，以评估和最小化机翼物理接口处的错误。机电子系统的行为表现出对数值子结构特性和激励频率的强烈依赖，并导致执行器和机翼之间界面处的模拟位移与实际位移之间存在显着差异。