ABSTRACT The following approach in the main text is intended primarily for single-degree-of-freedom systems. Some consideration is also given for multi-degree-of-freedom systems.

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    ABSTRACT: Traditional maximax analysis of nonstationary flight data for space and launch vehicles can overestimate peak response and does not address the potential for fatigue failure of hardware. A new method, referred to as the damage-based approach, is presented that employs an extended response spectrum analysis and includes amplitude-cycle counts. The outcome is a conservative, stationary test specification that envelops the damage potential of the nonstationary flight environment for both,peak response and fatigue, while recognizing uncertainties in damping and the fatigue law. Notable features of the new analysis technique are a quantitative means for addressing fatigue-damage potential in flight and a reduction in the overestimation of peak flight responses. Damage-based analysis of flight data can, therefore, help define more appropriate test specifications from historical data. The new method also provides a more accurate means for assessing the qualification status of components following early missions of a new launch vehicle and may help avoid unnecessary requalification of hardware suggested by an over-conservative maximax analysis of flight data. Potential benefits of the damage-based approach are demonstrated by investigation of a vibration and an acoustic measurement from multiple flights of the Titan 4A launch vehicle.
    Journal of Spacecraft and Rockets 04/2003; 40(5):682-689. DOI:10.2514/2.6893 · 0.53 Impact Factor
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    ABSTRACT: The present study is concerned with the aspects of designing for electronic piece parts in a random vibration environment, taking into account the deflection and inertial load requirements for typical printed circuit boards, the part attachment to the board, and the vibration specifications for the part itself. It is found that designing for random vibration is not much different than designing for sinusoidal vibration as far as piece part applications are concerned. In both cases, it is necessary to derive q load factors and deflection criteria, develop part mounting techniques, and qualify piece parts. Differences in the environment do not result in significant differences in mechanical design criteria philosophy.
  • A Clarification of the Shock/Vibration Equivalence in Mil-Std-180D/E. . 12.


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