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In the aeronautical industry, qualification and certification processes are very complex not only
because safety has to be ensured, but also because there is regulation that must be fulfilled.
This dissertation has its origin on the necessity of assisting a design certified company credited
as DOA (Design Organization Approval) in a preliminary phase of a modification project, and
fulfill the need of developing an analysis methodology at a preliminary design phase that allows
to produce confident results in a short time.
The modification in study consists in a flight instruments retrofit (upgrade) for Lockheed Martin
C-130 H aircraft series. One of the main concerns on the modified instrument panel is its level of
vibration.
Random vibration is recognized as the most realistic method of simulating the dynamic
environment of military applications. PSD (Power Spectral Density) is a statistical measure
defined as the limiting mean-square value of a random variable and it is used in random vibration
analyses in which the instantaneous magnitudes of the response can be specified only by
probability distribution functions that show the probability of the magnitude taking a certain
value.
The purpose of this work is a creation of an efficient methodology which is intended to provide
guidance for future possible projects of modification and fulfills the requirements of MIL-STD-
810G.
The design methodology was implemented in a case study: the Lockheed Martin C-130H
instrument panel retrofit (upgrade). Case study simulations were carried out through FEM (Finite
Element Method).
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Palavras-chave
Power Spectral Density (PSD) Random Vibration, Design Methodology Finite Element Analysis (FEA) Lockheed Martin C-130H Instrument Panel Retrofit
