Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight
Само за регистроване кориснике
2008
Чланак у часопису (Објављена верзија)
Метаподаци
Приказ свих података о документуАпстракт
This paper presents the numerical model developed for rotor blade aerodynamics loads calculation. The model is unsteady and fully three-dimensional. Helicopter blade is assumed to be rigid, and its motion during rotation is modeled in the manner that rotor presents a model of rotor of helicopter Aerospatiale SA 341 "Gazelle" (the blade is attached to the hub by flap, pitch and pseudo lead-lag hinges). Flow field around the blade is observed in succession of several azimuth locations. Flow field around helicopter rotor is modeled as fully three-dimensional, unsteady and potential. Blade aerodynamics is modeled using a lifting surface model. Rotor wake is generated from the straight elements of constant vorticity, released from the trailing edge, at fixed azimuth angles. These vortices represent both trailed and shed wake components, and are allowed to freely convect along local velocity vectors. Wake is modeled as free one, and its shape at certain moment can be calculated from simple k...inematics laws applied on collocation points of the wake. Wake distortion is calculated only in the rotor near-field, i.e. in finite number of rotor revolutions. Vortex elements are modeled with vortex core. The radius of the vortex core is assumed independent of time, and it depends on circulation gradient at the point of vortex element released from the blade.
Кључне речи:
unsteady aerodynamics / potential flow / lifting surface theory / helicopter rotor bladeИзвор:
Strojniski Vestnik/Journal of Mechanical Engineering, 2008, 54, 3, 170-178Колекције
Институција/група
Mašinski fakultetTY - JOUR AU - Bengin, Aleksandar AU - Mitrović, Časlav AU - Cvetković, Dragan AU - Bekrić, Dragoljub AU - Pegić, Slavko PY - 2008 UR - https://machinery.mas.bg.ac.rs/handle/123456789/789 AB - This paper presents the numerical model developed for rotor blade aerodynamics loads calculation. The model is unsteady and fully three-dimensional. Helicopter blade is assumed to be rigid, and its motion during rotation is modeled in the manner that rotor presents a model of rotor of helicopter Aerospatiale SA 341 "Gazelle" (the blade is attached to the hub by flap, pitch and pseudo lead-lag hinges). Flow field around the blade is observed in succession of several azimuth locations. Flow field around helicopter rotor is modeled as fully three-dimensional, unsteady and potential. Blade aerodynamics is modeled using a lifting surface model. Rotor wake is generated from the straight elements of constant vorticity, released from the trailing edge, at fixed azimuth angles. These vortices represent both trailed and shed wake components, and are allowed to freely convect along local velocity vectors. Wake is modeled as free one, and its shape at certain moment can be calculated from simple kinematics laws applied on collocation points of the wake. Wake distortion is calculated only in the rotor near-field, i.e. in finite number of rotor revolutions. Vortex elements are modeled with vortex core. The radius of the vortex core is assumed independent of time, and it depends on circulation gradient at the point of vortex element released from the blade. T2 - Strojniski Vestnik/Journal of Mechanical Engineering T1 - Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight EP - 178 IS - 3 SP - 170 VL - 54 UR - https://hdl.handle.net/21.15107/rcub_machinery_789 ER -
@article{ author = "Bengin, Aleksandar and Mitrović, Časlav and Cvetković, Dragan and Bekrić, Dragoljub and Pegić, Slavko", year = "2008", abstract = "This paper presents the numerical model developed for rotor blade aerodynamics loads calculation. The model is unsteady and fully three-dimensional. Helicopter blade is assumed to be rigid, and its motion during rotation is modeled in the manner that rotor presents a model of rotor of helicopter Aerospatiale SA 341 "Gazelle" (the blade is attached to the hub by flap, pitch and pseudo lead-lag hinges). Flow field around the blade is observed in succession of several azimuth locations. Flow field around helicopter rotor is modeled as fully three-dimensional, unsteady and potential. Blade aerodynamics is modeled using a lifting surface model. Rotor wake is generated from the straight elements of constant vorticity, released from the trailing edge, at fixed azimuth angles. These vortices represent both trailed and shed wake components, and are allowed to freely convect along local velocity vectors. Wake is modeled as free one, and its shape at certain moment can be calculated from simple kinematics laws applied on collocation points of the wake. Wake distortion is calculated only in the rotor near-field, i.e. in finite number of rotor revolutions. Vortex elements are modeled with vortex core. The radius of the vortex core is assumed independent of time, and it depends on circulation gradient at the point of vortex element released from the blade.", journal = "Strojniski Vestnik/Journal of Mechanical Engineering", title = "Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight", pages = "178-170", number = "3", volume = "54", url = "https://hdl.handle.net/21.15107/rcub_machinery_789" }
Bengin, A., Mitrović, Č., Cvetković, D., Bekrić, D.,& Pegić, S.. (2008). Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight. in Strojniski Vestnik/Journal of Mechanical Engineering, 54(3), 170-178. https://hdl.handle.net/21.15107/rcub_machinery_789
Bengin A, Mitrović Č, Cvetković D, Bekrić D, Pegić S. Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight. in Strojniski Vestnik/Journal of Mechanical Engineering. 2008;54(3):170-178. https://hdl.handle.net/21.15107/rcub_machinery_789 .
Bengin, Aleksandar, Mitrović, Časlav, Cvetković, Dragan, Bekrić, Dragoljub, Pegić, Slavko, "Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight" in Strojniski Vestnik/Journal of Mechanical Engineering, 54, no. 3 (2008):170-178, https://hdl.handle.net/21.15107/rcub_machinery_789 .