Finite Element Modeling of the NASA Langley Aluminum Testbed Cylinder-Reference-Cited by-同舟云学术

Finite Element Modeling of the NASA Langley Aluminum Testbed Cylinder

Published:2002-06-17 Issue: Volume: Page:
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Container-title:8th AIAA/CEAS Aeroacoustics Conference & Exhibit
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Author:

Grosveld Ferdinand,Pritchard Jocelyn,Buehrle Ralph,Pappa Richard

Publisher

American Institute of Aeronautics and Astronautics

Reference7 articles.

1. Grosveld, F. W. "Structural Normal Mode Analysis of the Aluminum Testbed Cylinder," AIAA Paper 98-1949, Proceedings of the 39thAIAA/ASME/ASCE Structures, Structural Dynamics, and Materials Conference, Long Beach, CA, April 1998.

2. Fleming, G. A., Buehrle, R. D., and Storaasli, O. L. "Modal Analysis of an Aircraft Fuselage Panel Using Experimental and Finite Element Techniques," Proceedings of the 3rdInternational Conference on Vibration Measurements by Laser Techniques, Ancona, Italy, June 1998.

3. Buehrle, R. D., Fleming, G. A., Pappa, R. S., and Grosveld, F. W. "Finite Element Model Development and Validation for Aircraft Fuselage Structures," Proceedings of the 18thInternational Modal Analysis Conference, San Antonio, Texas, February7-10, 2000.

4. Buehrle, Ralph D., Robinson, Jay H. and Grosveld, Ferdinand W. "Vibro-Acoustic Model Validation for a Curved Honeycomb Composite Panel," AIAA Paper 2001-1587, 42ndAIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Seattle, WA, 16-19April 2001.

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