Citation

Heimbs S, Ritzer J, Markmiller J. Int. J. Aerosp. Eng. 2015; 2015: 1-8.

Copyright

(Copyright © 2015, Hindawi Publishing)

DOI

10.1155/2015/897213

PMID

unavailable

Abstract

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.

Language: en