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- W2894844669 abstract "The experimental data made available to the Workshop participants were acquired on a full-scale F-16 aircraft (see Fig. 1 (a)) on the occasion of the Siemens LMS Ground Vibration Testing Master Class, held in September 2014 at the Saffraanberg military basis, Sint-Truiden, Belgium. 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 (see Fig. 1 (b)). The aircraft structure was instrumented by means of 145 acceleration sensors. One shaker was attached underneath the right wing to apply input signals (see Fig. 1 (c)). 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 see Fig. 1 (d)). 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." @default.
- W2894844669 created "2018-10-12" @default.
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- W2894844669 date "2017-04-24" @default.
- W2894844669 modified "2023-09-27" @default.
- W2894844669 title "F-16 aircraft benchmark based on ground vibration test data" @default.
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