Dynamic Gust Load Analysis for Rotors
Dynamic load of helicopter rotors due to gust directly affects the structural stress and flight performance for helicopters. Based on a large deflection beam theory, an aeroelastic model for isolated helicopter rotors in the time domain is constructed. The dynamic response and structural load for a...
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Wiley
2016-01-01
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| Series: | Shock and Vibration |
| Online Access: | http://dx.doi.org/10.1155/2016/5727028 |
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| _version_ | 1832552840747286528 |
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| author | Yuting Dai Linpeng Wang Chao Yang Xintan Zhang |
| author_facet | Yuting Dai Linpeng Wang Chao Yang Xintan Zhang |
| author_sort | Yuting Dai |
| collection | DOAJ |
| description | Dynamic load of helicopter rotors due to gust directly affects the structural stress and flight performance for helicopters. Based on a large deflection beam theory, an aeroelastic model for isolated helicopter rotors in the time domain is constructed. The dynamic response and structural load for a rotor under the impulse gust and slope-shape gust are calculated, respectively. First, a nonlinear Euler beam model with 36 degrees-of-freedoms per element is applied to depict the structural dynamics for an isolated rotor. The generalized dynamic wake model and Leishman-Beddoes dynamic stall model are applied to calculate the nonlinear unsteady aerodynamic forces on rotors. Then, we transformed the differential aeroelastic governing equation to an algebraic one. Hence, the widely used Newton-Raphson iteration algorithm is employed to simulate the dynamic gust load. An isolated helicopter rotor with four blades is studied to validate the structural model and the aeroelastic model. The modal frequencies based on the Euler beam model agree well with published ones by CAMRAD. The flap deflection due to impulse gust with the speed of 2m/s increases twice to the one without gust. In this numerical example, results indicate that the bending moment at the blade root is alleviated due to elastic effect. |
| format | Article |
| id | doaj-art-380d8bb02c3f4bc1b7333f792e6a1718 |
| institution | Kabale University |
| issn | 1070-9622 1875-9203 |
| language | English |
| publishDate | 2016-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | Shock and Vibration |
| spelling | doaj-art-380d8bb02c3f4bc1b7333f792e6a17182025-02-03T05:57:39ZengWileyShock and Vibration1070-96221875-92032016-01-01201610.1155/2016/57270285727028Dynamic Gust Load Analysis for RotorsYuting Dai0Linpeng Wang1Chao Yang2Xintan Zhang3School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, ChinaSchool of Aeronautic Science and Engineering, Beihang University, Beijing 100191, ChinaSchool of Aeronautic Science and Engineering, Beihang University, Beijing 100191, ChinaBeijing Aeronautical Science and Technology Research Institute of COMAC, Beijing 100083, ChinaDynamic load of helicopter rotors due to gust directly affects the structural stress and flight performance for helicopters. Based on a large deflection beam theory, an aeroelastic model for isolated helicopter rotors in the time domain is constructed. The dynamic response and structural load for a rotor under the impulse gust and slope-shape gust are calculated, respectively. First, a nonlinear Euler beam model with 36 degrees-of-freedoms per element is applied to depict the structural dynamics for an isolated rotor. The generalized dynamic wake model and Leishman-Beddoes dynamic stall model are applied to calculate the nonlinear unsteady aerodynamic forces on rotors. Then, we transformed the differential aeroelastic governing equation to an algebraic one. Hence, the widely used Newton-Raphson iteration algorithm is employed to simulate the dynamic gust load. An isolated helicopter rotor with four blades is studied to validate the structural model and the aeroelastic model. The modal frequencies based on the Euler beam model agree well with published ones by CAMRAD. The flap deflection due to impulse gust with the speed of 2m/s increases twice to the one without gust. In this numerical example, results indicate that the bending moment at the blade root is alleviated due to elastic effect.http://dx.doi.org/10.1155/2016/5727028 |
| spellingShingle | Yuting Dai Linpeng Wang Chao Yang Xintan Zhang Dynamic Gust Load Analysis for Rotors Shock and Vibration |
| title | Dynamic Gust Load Analysis for Rotors |
| title_full | Dynamic Gust Load Analysis for Rotors |
| title_fullStr | Dynamic Gust Load Analysis for Rotors |
| title_full_unstemmed | Dynamic Gust Load Analysis for Rotors |
| title_short | Dynamic Gust Load Analysis for Rotors |
| title_sort | dynamic gust load analysis for rotors |
| url | http://dx.doi.org/10.1155/2016/5727028 |
| work_keys_str_mv | AT yutingdai dynamicgustloadanalysisforrotors AT linpengwang dynamicgustloadanalysisforrotors AT chaoyang dynamicgustloadanalysisforrotors AT xintanzhang dynamicgustloadanalysisforrotors |