期刊名称：Lecture Notes in Engineering and Computer Science
印刷版ISSN：2078-0958
电子版ISSN：2078-0966
出版年度：2018
卷号：2235&2236
页码：761-766
出版社：Newswood and International Association of Engineers
摘要：The skin of the fuselage and wings of the high
supersonic aircraft is designed using titanium-based thermal
shield structures to prevent high temperatures from being
transferred into the interior of an aircraft. A thermal shield
structure consists of double panels, and the outer skin panels,
those in contact with the outside, are designed using thin plates
with a thickness of 0.5 to 1.0 mm. Because of acoustic loading
caused by aerodynamic flow and engine noise, the thin skin
panels are exposed to acoustic loading of more than 150 dB
OASPL. Sonic fatigue damage of thin skin panels can occur due
to such acoustic loading. In this paper, the time domain and
frequency domain fatigue life prediction for a thin titanium skin
panels of the high supersonic aircraft subjected to acoustic
loading were performed. Frequency domain fatigue damage
results were compared with time domain fatigue damage
results. In addition, a method for reducing the calculation time
of the time domain fatigue life prediction method for the skin
panel subjected to acoustic load SPL which is without phase
information was studied.
关键词：Supersonic vehicle; Acoustic loading; Sound
pressure level; Fatigue life
