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Spectral analysis of response acceleration during instrument vibration test. 4 Principles of Space Instrument Design Launch excitation of vibration The first stage burn begins with the vehicle held firmly on the pad. From a few seconds before lift-off, rocket motor efflux generates an intense noise field (possibly 140dB above the standard reference amplitude of 20 JlPa). When hold-down arms are released, there is a transfer of stress which excites transiently the axial modes, parti~ularly the lowest' pogo' frequency which may be near 15 Hz.

In calculating the effect of the geometry of the beam on its stiffness, small elements of material at a distance y from the neutral plane are considered. The further these elements are from the neutral plane (the larger the value of y) the greater is their contribution to the bending moment because the force acts with a larger lever arm. In addition to this factor, the stress increases with the value of y itself, since the extension of the material increases away from the neutral plane. These two factors involving y mean that the ability of the beam to resist bending increases as y 2 and so the stiffness can be increased markedly by positioning much of the material at large values of y, as in tubes or the skins of honeycomb panels.

6 Mechanical design - spacecraft vibration 49 with motion at the resonant mass greater by factor Q. Thus the rms response is The probability distribution of acceleration data has been supposed Gaussian, implying that the peak accelerations are in a Rayleigh distribution (Fig. 27). 2D _ 3 for peaks. - .... 2 C --- 1 ~-~ ·6 DistribUtion of i'" Probability density - - Time Fig. 27. Rayleigh and Gaussian distributions for the narrow band, quasi-resonant response of a structure vibration mode.

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