期刊
INTERNATIONAL JOURNAL OF AEROSPACE ENGINEERING
卷 2015, 期 -, 页码 -出版社
HINDAWI LTD
DOI: 10.1155/2015/897213
关键词
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An efficient empirical approach was developed to accurately represent the blast shock wave loading resulting from the launch of a missile from a military aircraft to be used in numerical analyses. Based on experimental test series of missile launches in laboratory environment and from a helicopter, equations were derived to predict the time-and position-dependent overpressure. The method was finally applied and validated in a structural analysis of a helicopter tail boom under missile launch shock wave loading.
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