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Monitoring network for SHM in avionic application

Überwachungsnetzwerk zur Zustandsüberwachung bei Luftfahrtanwendungen
 
: Frankenstein, B.; Hentschel, D.; Schubert, F.

Deutsche Gesellschaft für Zerstörungsfreie Prüfung e.V. -DGZfP-, Berlin; European Federation for Non-Destructive Testing -EFNDT-:
9th European Conference on NDT. ECNDT Berlin 2006. CD-ROM : September 25 - 29, 2006
Berlin: DGZfP, 2006 (DGZfP Proceedings BB 103-CD)
ISBN: 3-931381-86-2
9 S.
European Conference on NDT (ECNDT) <9, 2006, Berlin>
Englisch
Konferenzbeitrag
Fraunhofer IZFP, Institutsteil Dresden ( IKTS-MD) ()
zerstörungsfreie Prüfung; Ultraschallprüfung; Luftfahrtindustrie; Überwachungseinrichtung; Netzwerkanalyse; Signalanalyse; Plattenwelle

Abstract
The condition of avionic structures has to be continuously monitored. In favor of such a Structural Health Monitoring (SHM), the evaluation of acoustic Lamb waves can contribute substantially. Methods for an effective, signal processing are required to detect wave modes and to reduce noise as much as possible. Frequently, a further necessity exists to integrate the measuring technique into the structure to be monitored. To meet these requirements, sensor near units for signal processing have to be developed, which can be connected as nodes within a network. A compact, sensor near signal processing structure has been realized containing components for analog preprocessing of acoustic signals, their digitization, algorithms for data reduction and network communication. The core component is a digital signal processor (DSP), which effectively performs the basic algorithms necessary for filtering, down sampling, mode selection and correlation of spectral components. For a fiber composite plate as the first application, impact detection and characterization of delaminations were realized. Starting from the simulation of wave propagation, characteristic signal parameters were determined. In some experiments, it could be proven that impact locations and delaminations can be identified from the detected Lamb waves. The final aim is to develop a special Structural Health Monitoring (SHM) system for selected aircraft components (e. g. stringer elements, panels).
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: http://publica.fraunhofer.de/dokumente/N-84618.html