F-16 Aircraft Benchmark Based on Ground Vibration Test Data

The F-16 Ground Vibration Test benchmark features a high order system with clearance and friction nonlinearities at the mounting interface of the payloads.<br><br>The experimental data made available here were acquired on a full-scale F-16 aircraft on the occasion of the Siemens LMS Ground Vibration Testing Master Class.<br><br>During the test campaign, two dummy payloads were mounted at the wing tips to simulate the mass and inertia properties of real devices typically equipping an F-16 in flight. The aircraft structure was instrumented with accelerometers. One shaker was attached underneath the right wing to apply input signals. The dominant source of nonlinearity in the structural dynamics was expected to originate from the mounting interfaces of the two payloads. These interfaces consist of T-shaped connecting elements on the payload side, slid through a rail attached to the wing side. A preliminary investigation showed that the back connection of the right-wing-to-payload interface was the predominant source of nonlinear distortions in the aircraft dynamics, and is therefore the focus of this benchmark study.<br><br>All the provided files and information together with a detailed description of the F-16 aircraft benchmark system are available for download here. This zip-file contains a detailed system description, the estimation and test data sets, and some pictures of the setup. The data is available in the .csv and .mat file format.<br>

F-16地面振动测试基准（F-16 Ground Vibration Test benchmark）面向一类高阶系统，该系统的载荷安装界面存在间隙与摩擦非线性特性。

本次公开的实验数据采自一架全尺寸F-16战机，采集场景为西门子（Siemens）LMS地面振动测试大师班（Siemens LMS Ground Vibration Testing Master Class）。

在本次测试任务中，研究人员在翼尖安装了两个模拟载荷，以模拟F-16战机飞行状态下挂载的真实设备的质量与惯性特性。战机结构加装了加速度传感器，右翼下方安装了一台激振器以施加输入激励信号。研究预期，结构动力学中的主要非线性来源为两个载荷的安装界面：载荷侧采用T型连接元件，通过滑接于翼侧固定导轨的方式实现安装。前期预研表明，右翼与载荷的后端连接界面是战机动力学非线性畸变的主要来源，因此本基准研究将其作为核心研究对象。

所有公开文件、相关信息以及F-16战机基准系统的详细说明均可在此处下载。该压缩包包含系统详细说明、估计数据集与测试数据集，以及试验装置实拍图，数据格式为.csv与.mat文件。