Analysis and design of helicopter rotor blades for reduced vibrational level

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2011

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Tamer, Aykut

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In this thesis analysis and design of helicopter rotor blades were discussed for reduced vibrational level. For this purpose an optimization procedure was developed which involves coupling of the comprehensive rotorcraft analysis tool CAMRAD JA and the gradient based optimization algorithm. The main goal was to achieve favorable blade structural dynamics characteristics that would lead to reduction in vibrational level. For this purpose blade stiffness and mass distributions were considered as the design variables. In order to avoid likely occurrences of unrealistic results, the analyses were subjected to constraints which were sensitive to the design variables. The optimization procedure was applied on two isolated rotor blades and a full helicopter with main rotor, tail rotor and fuselage by using natural frequency separation and hub load minimization respectively. While the former approach relied on the blade natural frequencies, the latter approach involved higher harmonic aerodynamic and blade motion calculations. For both approaches, the improvement in vibration characteristics and blade mass and stiffness distributions of the initial design and the design after optimization analyses were compared and discussed.

Subject Keywords

Compressors, Aerospace engineering.

URI

http://etd.lib.metu.edu.tr/upload/12613661/index.pdf
https://hdl.handle.net/11511/20971

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Graduate School of Natural and Applied Sciences, Thesis

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Citation Formats

A. Tamer, “Analysis and design of helicopter rotor blades for reduced vibrational level,” M.S. - Master of Science, Middle East Technical University, 2011.