Simplified design of components and systems against aircraft crash induced loads using verified response spectra

The progress which has been achieved up to the present time in the application of the assumptions used to define relevant aircraft impact responses for the design of mechanical and electrical components and systems installed inside buildings for practical needs has led to a notable reduction in analytical calculation effort on the side of both the analyst and the reviewer. Allowance made for non-linear effects at the point of impact, as well as clarification of the negligible influence of high-frequency spectral acceleration on component loading has made it possible to define a relevant fequency range for the response spectra and a representative acceleraton level (covering the relevant range of the spectra). This knowledge and these new definitions have enabled a simplified quasi-static design procedure to be introduced for all components installed inside buildings. (orig.)