NTRS - NASA Technical Reports Server

Back to Results
Test-Anchored Vibration Response Predictions for an Acoustically Energized Curved Orthogrid Panel with Mounted ComponentsA rich body of vibroacoustic test data was recently generated at Marshall Space Flight Center for a curved orthogrid panel typical of launch vehicle skin structures. Several test article configurations were produced by adding component equipment of differing weights to the flight-like vehicle panel. The test data were used to anchor computational predictions of a variety of spatially distributed responses including acceleration, strain and component interface force. Transfer functions relating the responses to the input pressure field were generated from finite element based modal solutions and test-derived damping estimates. A diffuse acoustic field model was employed to describe the assumed correlation of phased input sound pressures across the energized panel. This application demonstrates the ability to quickly and accurately predict a variety of responses to acoustically energized skin panels with mounted components. Favorable comparisons between the measured and predicted responses were established. The validated models were used to examine vibration response sensitivities to relevant modeling parameters such as pressure patch density, mesh density, weight of the mounted component and model form. Convergence metrics include spectral densities and cumulative root-mean squared (RMS) functions for acceleration, velocity, displacement, strain and interface force. Minimum frequencies for response convergence were established as well as recommendations for modeling techniques, particularly in the early stages of a component design when accurate structural vibration requirements are needed relatively quickly. The results were compared with long-established guidelines for modeling accuracy of component-loaded panels. A theoretical basis for the Response/Pressure Transfer Function (RPTF) approach provides insight into trends observed in the response predictions and confirmed in the test data. The software modules developed for the RPTF method can be easily adapted for quick replacement of the diffuse acoustic field with other pressure field models; for example a turbulent boundary layer (TBL) model suitable for vehicle ascent. Wind tunnel tests have been proposed to anchor the predictions and provide new insight into modeling approaches for this type of environment. Finally, component vibration environments for design were developed from the measured and predicted responses and compared with those derived from traditional techniques such as Barrett scaling methods for unloaded and component-loaded panels.
Document ID
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Frady, Gregory P.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Duvall, Lowery D.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Fulcher, Clay W. G.
(Jacobs Engineering Group, Inc. Huntsville, AL, United States)
Laverde, Bruce T.
(Jacobs Engineering Group, Inc. Huntsville, AL, United States)
Hunt, Ronald A.
(Jacobs Engineering Group, Inc. Huntsville, AL, United States)
Date Acquired
August 25, 2013
Publication Date
December 5, 2011
Subject Category
Report/Patent Number
Meeting Information
Meeting: 8th Modeling and Simulation Subcommittee, JANNAF 2011
Location: Huntsville, AL
Country: United States
Start Date: December 5, 2011
End Date: December 7, 2011
Sponsors: Department of the Army, Department of the Navy, Department of the Air Force, NASA Headquarters
Distribution Limits
Public Use Permitted.
No Preview Available