Aeroelastic stability analysis of rotor blade with complex three-dimensional design
A rotor dynamic analysis method for the complex three-dimensional design blade was developed and applied to analyzing its aeroelastic stability. Based on the medium-size deformation beam theory and Hamilton principle, the joint transfer matrix was used in the blade kinematic and the deformation comp...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | zho |
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EDP Sciences
2023-02-01
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| Series: | Xibei Gongye Daxue Xuebao |
| Subjects: | |
| Online Access: | https://www.jnwpu.org/articles/jnwpu/full_html/2023/01/jnwpu2023411p209/jnwpu2023411p209.html |
| _version_ | 1797415124941668352 |
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| author | DENG Jinghui YU Zhihao ZHOU Yun SONG Bin |
| author_facet | DENG Jinghui YU Zhihao ZHOU Yun SONG Bin |
| author_sort | DENG Jinghui |
| collection | DOAJ |
| description | A rotor dynamic analysis method for the complex three-dimensional design blade was developed and applied to analyzing its aeroelastic stability. Based on the medium-size deformation beam theory and Hamilton principle, the joint transfer matrix was used in the blade kinematic and the deformation compatibility principle was used in the assembled finite element matrix to develop the complex three-dimensional rotor structural dynamics model. The BO105 rotor was used to validate this method and the aeroelastic characteristic of the complex three-dimensional rotor was analyzed in detail. The results showed that the negative structural coupling of flap-torsion was appeared with tip sweep, and the 1/rev torsion modal frequency was decreased, and the 1/rev torsion modal damping ratio was maximally decreased about 90%. The positive structural coupling of lag-torsion was appeared with tip droop, the 2/rev lag modal frequency was decreased, the 1/rev torsion modal damping ratio was maximally decreased about 62%. The torsion stability was sharply decreased with tip sweep and droop design. |
| first_indexed | 2024-03-09T05:43:25Z |
| format | Article |
| id | doaj.art-a23f3a2333e24eb4aede70e74563aad3 |
| institution | Directory Open Access Journal |
| issn | 1000-2758 2609-7125 |
| language | zho |
| last_indexed | 2024-03-09T05:43:25Z |
| publishDate | 2023-02-01 |
| publisher | EDP Sciences |
| record_format | Article |
| series | Xibei Gongye Daxue Xuebao |
| spelling | doaj.art-a23f3a2333e24eb4aede70e74563aad32023-12-03T12:23:26ZzhoEDP SciencesXibei Gongye Daxue Xuebao1000-27582609-71252023-02-0141120921510.1051/jnwpu/20234110209jnwpu2023411p209Aeroelastic stability analysis of rotor blade with complex three-dimensional designDENG Jinghui0YU Zhihao1ZHOU Yun2SONG Bin3Science and Technology on Rotorcraft Aeromechanics Laboratory, CHRDIScience and Technology on Rotorcraft Aeromechanics Laboratory, CHRDIScience and Technology on Rotorcraft Aeromechanics Laboratory, CHRDIScience and Technology on Rotorcraft Aeromechanics Laboratory, CHRDIA rotor dynamic analysis method for the complex three-dimensional design blade was developed and applied to analyzing its aeroelastic stability. Based on the medium-size deformation beam theory and Hamilton principle, the joint transfer matrix was used in the blade kinematic and the deformation compatibility principle was used in the assembled finite element matrix to develop the complex three-dimensional rotor structural dynamics model. The BO105 rotor was used to validate this method and the aeroelastic characteristic of the complex three-dimensional rotor was analyzed in detail. The results showed that the negative structural coupling of flap-torsion was appeared with tip sweep, and the 1/rev torsion modal frequency was decreased, and the 1/rev torsion modal damping ratio was maximally decreased about 90%. The positive structural coupling of lag-torsion was appeared with tip droop, the 2/rev lag modal frequency was decreased, the 1/rev torsion modal damping ratio was maximally decreased about 62%. The torsion stability was sharply decreased with tip sweep and droop design.https://www.jnwpu.org/articles/jnwpu/full_html/2023/01/jnwpu2023411p209/jnwpu2023411p209.html直升机旋翼气弹稳定性后掠下反 |
| spellingShingle | DENG Jinghui YU Zhihao ZHOU Yun SONG Bin Aeroelastic stability analysis of rotor blade with complex three-dimensional design Xibei Gongye Daxue Xuebao 直升机 旋翼 气弹稳定性 后掠 下反 |
| title | Aeroelastic stability analysis of rotor blade with complex three-dimensional design |
| title_full | Aeroelastic stability analysis of rotor blade with complex three-dimensional design |
| title_fullStr | Aeroelastic stability analysis of rotor blade with complex three-dimensional design |
| title_full_unstemmed | Aeroelastic stability analysis of rotor blade with complex three-dimensional design |
| title_short | Aeroelastic stability analysis of rotor blade with complex three-dimensional design |
| title_sort | aeroelastic stability analysis of rotor blade with complex three dimensional design |
| topic | 直升机 旋翼 气弹稳定性 后掠 下反 |
| url | https://www.jnwpu.org/articles/jnwpu/full_html/2023/01/jnwpu2023411p209/jnwpu2023411p209.html |
| work_keys_str_mv | AT dengjinghui aeroelasticstabilityanalysisofrotorbladewithcomplexthreedimensionaldesign AT yuzhihao aeroelasticstabilityanalysisofrotorbladewithcomplexthreedimensionaldesign AT zhouyun aeroelasticstabilityanalysisofrotorbladewithcomplexthreedimensionaldesign AT songbin aeroelasticstabilityanalysisofrotorbladewithcomplexthreedimensionaldesign |