This paper describes a modal test on a non-linear aircraft frame structure. Both stepped-sine and burst random excitation forces were used to estimate frequency response functions relative to four inputs. Comparisons are discussed between both excitation techniques, between single and multiple input excitation, and between the time domain Polyreference and the frequency domain direct parameter identification techniques.
Comparison of stepped-sine and broad band excitation to an aircraft frame
Vergleich von stufenfoermiger Sinus- und Breitband-Schwingungsanregung einer Flugzeugzelle
1988
8 Seiten, 10 Bilder, 3 Tabellen, 8 Quellen
Conference paper
English
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