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Experimental Modal Analysis of an Aircraft Fuselage Panel

2017; Springer Nature; Linguagem: Inglês

10.1007/978-3-319-54735-0_17

2191-5652

Travis A. Wyen, Joshua J. Schoettelkotte, Ricardo Pérez, Thomas Eason,

Structural Response to Dynamic Loads

Hypersonic aircraft structures must operate in complex loading conditions and very high temperatures, making the design of a robust and reusable platform very challenging. An analytical and experimental test program was developed by the Air Force Research Laboratory (AFRL) and industry. The objective of the program is to review the design process of a thin skinned aircraft panel subjected to combined thermal-acoustic-mechanical loading, through a series of laboratory experiments at the AFRL’s Structural Dynamics Laboratory. This paper presents the results from a series of modal tests, performed to estimate the modal parameters of a hat-stiffened fuselage panel designed by industry. A comparison of the modal parameters of the panel, estimated from roving impact and a multiple input multiple output (MIMO) shaker test data of the panel is presented. Also, the variation in the natural frequencies and damping through various stages prior to the combined environment test is discussed.