Aeroelastic stability analysis of rotor blade with complex three-dimensional design
نویسندگان
چکیده
A rotor dynamic analysis method for the complex three-dimensional design blade was developed and applied to analyzing its aeroelastic stability. Based on medium-size deformation beam theory Hamilton principle, joint transfer matrix used in kinematic compatibility principle assembled finite element develop structural dynamics model. The BO105 validate this characteristic of analyzed detail. results showed that negative coupling flap-torsion appeared with tip sweep, 1/rev torsion modal frequency decreased, damping ratio maximally decreased about 90%. positive lag-torsion droop, 2/rev lag 62%. stability sharply sweep droop design.
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ژورنال
عنوان ژورنال: Xibei gongye daxue xuebao
سال: 2023
ISSN: ['1000-2758', '2609-7125']
DOI: https://doi.org/10.1051/jnwpu/20234110209