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International Journal of Aerospace Engineering
Volume 2015 (2015), Article ID 897213, 8 pages
Research Article

A Numerical Method for Blast Shock Wave Analysis of Missile Launch from Aircraft

1Department of Structure Engineering, Production and Aeromechanics, Airbus Group Innovations, Willy-Messerschmitt-Strasse, 85521 Ottobrunn, Germany
2Department of Stress, Loads and Crash, Airbus Helicopters, Industriestrasse 4, 86609 Donauwörth, Germany

Received 1 June 2015; Accepted 13 September 2015

Academic Editor: Hikmat Asadov

Copyright © 2015 Sebastian Heimbs et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


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.