ESDU 72015
Endurance of aluminium alloy structural elements subjected to simulated acoustic loading.
Abstract:
ESDU 72015 provides fatigue endurance data for aluminium alloy specimens, typical of aircraft structural elements. The endurance range covered is 0.1 to 1000 MHz. Data are based on results of tests on specimens that were excited by narrow-band loading of random amplitude with zero mean load to simulate stress response to acoustic loading. Data are provided for plain cantilever specimens, integrally-machined stiffeners, and skin/rib combinations. For the last specimen types both skin- and rib-flange failures are considered. Test methods, used to obtain endurance data, are described and factors (such as cladding and jointing compounds) that may influence the results are discussed.Indexed under:
- Acoustic Fatigue
- Aluminium Alloys
- Cladding
- Integrally-Machined Panels
- Skin-Rib Joints in Aluminium Alloys
Details:
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This Data Item contains 12 interactive graph(s) as listed below.
| Graph | Title |
|---|---|
| Figure 3 | S-N data for plain and integrally machined specimens |
| Figure 4 | S-N data for riveted-skin specimens |
| Figure 5 | S-N data for riveted-skin specimens |
| Figure 6 | S-N data for riveted-skin specimens |
| Figure 7 | S-N data for riveted-skin specimens |
| Figure 8 | S-N data for riveted-skin specimens |
| Figure 9 | S-N data for riveted-skin specimens |
| Figure 10 | S-N data for riveted-skin specimens |
| Figure 11 | S-N data for riveted-skin specimens |
| Figure 12 | S-N data for riveted-skin specimens |
| Figure 13 | S-N data for rib-flange specimens |
| Figure 14 | S-N data for rib-flange specimens |