Design of shell structures for buckling using correction response surface approximations
Author:
Affiliation:
1. Florida, Univ., Gainesville
2. NASA, Langley Research Center, Hampton, VA
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1998-4855
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1. Analytical and experimental study of a blade stiffened panel in axial compression
2. Evaluation of various analytical models for buckling and vibration of stiffened shells.
3. Global/local structural wing design using response surface techniques
4. Integration of finite element analysis program and panel design program
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