A simple element for aeroelastic analysis of undamaged and damaged wings
- 1 February 1990
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 28 (2) , 329-337
- https://doi.org/10.2514/3.10393
Abstract
No abstract availableKeywords
This publication has 10 references indexed in Scilit:
- Shape Sensitivity Analysis of Flutter Response of a Laminated WingAIAA Journal, 1991
- Equivalent plate analysis of aircraft wing box structures with general planform geometryPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1986
- Static and Dynamic Formulation of a Symmetrically Laminated Beam Finite Element for a MicrocomputerJournal of Composite Materials, 1985
- Experimental aeroelastic behavior of unswept and forward-swept cantilever graphite/epoxy wingsJournal of Aircraft, 1985
- Divergence speed degradation of forward-swept wings with damaged composite skinJournal of Aircraft, 1984
- Vibration of Cantilevered Graphite/Epoxy Plates With Bending-Torsion CouplingJournal of Reinforced Plastics and Composites, 1982
- Frequency determination and non-dimensionalization for composite cantilever platesJournal of Sound and Vibration, 1980
- of Forward Swept Composite Wings DivergenceJournal of Aircraft, 1980
- Preliminary design of composite wing-box structures for global damage tolerancePublished by American Institute of Aeronautics and Astronautics (AIAA) ,1980
- Modified-strip-analysis method for predicting wing flutter at subsonic to hypersonic speeds.Journal of Aircraft, 1966