Helicopter vibration reduction using structural optimization with aeroelastic/multidisciplinary constraints - A survey
- 1 January 1991
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Aircraft
- Vol. 28 (1) , 8-21
- https://doi.org/10.2514/3.45987
Abstract
No abstract availableKeywords
This publication has 24 references indexed in Scilit:
- Helicopter Vibrations: A Technological PerspectiveJournal of the American Helicopter Society, 1984
- Optimum Design of Rotor Blades for vibration Reduction in Forward FlightJournal of the American Helicopter Society, 1984
- Blade Design for Reduced Helicopter VibrationJournal of the American Helicopter Society, 1983
- Aeroelastic tailoring of rotor blades for vibration reduction in forward flightPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1983
- On Making Things the Best-Aeronautical Uses of OptimizationJournal of Aircraft, 1982
- Structural synthesis - Its genesis and developmentAIAA Journal, 1981
- Application of the Finite Element Method to Rotary‐Wing AeroelasticityJournal of the American Helicopter Society, 1980
- Investigation of Helicopter Blade Flutter and Load Amplification ProblemsJournal of the American Helicopter Society, 1957
- Helicopter Blade Vibration and FlutterJournal of the American Helicopter Society, 1956
- Effect of Spanwise and Chordwise Mass Distribution on Rotor Blade Cyclic StressesJournal of the American Helicopter Society, 1956