Nonlinearities of an aircraft piccolo tube: Identification and modeling

T. Dossogne, P. Trillet, M. Schoukens, B. Bernay, J.P. Noël, G. Kerschen

Onderzoeksoutput: Hoofdstuk in Boek/Rapport/CongresprocedureConferentiebijdrageAcademicpeer review

Uittreksel

Piccolo tubes are parts of aircraft wings anti-icing system and consist of titanium pipes inserted into the internal structure of the slat. Due to differential thermal expansion, clearances between the tube and its support are unavoidable and cause the overall system to exhibit highly nonlinear behavior, resulting from impacts and friction. This paper addresses the identification and modeling of the nonlinearities present in the slat-Piccolo tube connection. The complete identification procedure, from nonlinearity detection and characterization to parameter estimation, is carried out based upon sine-sweep measurements. The use of several techniques, such as the acceleration surface method, enables to understand the complex dynamics of the Piccolo tube and build a reliable model of its nonlinearities. In particular, the parameters of nonsmooth nonlinear stiffness and damping mechanisms are estimated. The nonlinear model is finally validated on standard qualification tests for airborne equipments.
TaalEngels
TitelModel Validation and Uncertainty Quantification - Proceedings of the 36th IMAC, A Conference and Exposition on Structural Dynamics 2018
SubtitelProceedings of the 36th IMAC, A Conference and Exposition on Structural Dynamics 2018
RedacteurenRobert Barthorpe
Plaats van productieCham
UitgeverijSpringer
Pagina's57-59
Aantal pagina's3
Volume3
ISBN van elektronische versie978-3-319-74793-4
ISBN van geprinte versie978-3-319-74792-7
DOI's
StatusGepubliceerd - 31 jul 2018
Evenement36th IMAC, A Conference and Exposition on Structural Dynamics, 2018 - Orlando, Verenigde Staten van Amerika
Duur: 12 feb 201815 feb 2018

Publicatie series

NaamConference Proceedings of the Society for Experimental Mechanics Series

Congres

Congres36th IMAC, A Conference and Exposition on Structural Dynamics, 2018
LandVerenigde Staten van Amerika
StadOrlando
Periode12/02/1815/02/18

Vingerafdruk

Aircraft
Control nonlinearities
Parameter estimation
Thermal expansion
Identification (control systems)
Titanium
Damping
Pipe
Stiffness
Friction

Trefwoorden

    Citeer dit

    Dossogne, T., Trillet, P., Schoukens, M., Bernay, B., Noël, J. P., & Kerschen, G. (2018). Nonlinearities of an aircraft piccolo tube: Identification and modeling. In R. Barthorpe (editor), Model Validation and Uncertainty Quantification - Proceedings of the 36th IMAC, A Conference and Exposition on Structural Dynamics 2018: Proceedings of the 36th IMAC, A Conference and Exposition on Structural Dynamics 2018 (Vol. 3, blz. 57-59). (Conference Proceedings of the Society for Experimental Mechanics Series ). Cham: Springer. DOI: 10.1007/978-3-319-74793-4_8
    Dossogne, T. ; Trillet, P. ; Schoukens, M. ; Bernay, B. ; Noël, J.P. ; Kerschen, G./ Nonlinearities of an aircraft piccolo tube : Identification and modeling. Model Validation and Uncertainty Quantification - Proceedings of the 36th IMAC, A Conference and Exposition on Structural Dynamics 2018: Proceedings of the 36th IMAC, A Conference and Exposition on Structural Dynamics 2018. redacteur / Robert Barthorpe. Vol. 3 Cham : Springer, 2018. blz. 57-59 (Conference Proceedings of the Society for Experimental Mechanics Series ).
    @inproceedings{e9d74843c96b4d76820792fbb30597cf,
    title = "Nonlinearities of an aircraft piccolo tube: Identification and modeling",
    abstract = "Piccolo tubes are parts of aircraft wings anti-icing system and consist of titanium pipes inserted into the internal structure of the slat. Due to differential thermal expansion, clearances between the tube and its support are unavoidable and cause the overall system to exhibit highly nonlinear behavior, resulting from impacts and friction. This paper addresses the identification and modeling of the nonlinearities present in the slat-Piccolo tube connection. The complete identification procedure, from nonlinearity detection and characterization to parameter estimation, is carried out based upon sine-sweep measurements. The use of several techniques, such as the acceleration surface method, enables to understand the complex dynamics of the Piccolo tube and build a reliable model of its nonlinearities. In particular, the parameters of nonsmooth nonlinear stiffness and damping mechanisms are estimated. The nonlinear model is finally validated on standard qualification tests for airborne equipments.",
    keywords = "Acceleration surface method (ASM), Aircraft anti-icing system, Contact force model, Finite element model updating, Finite element model upgrading, Nonlinear system identification, Piccolo tube, Vibroimpact",
    author = "T. Dossogne and P. Trillet and M. Schoukens and B. Bernay and J.P. No{\"e}l and G. Kerschen",
    year = "2018",
    month = "7",
    day = "31",
    doi = "10.1007/978-3-319-74793-4_8",
    language = "English",
    isbn = "978-3-319-74792-7",
    volume = "3",
    series = "Conference Proceedings of the Society for Experimental Mechanics Series",
    publisher = "Springer",
    pages = "57--59",
    editor = "Robert Barthorpe",
    booktitle = "Model Validation and Uncertainty Quantification - Proceedings of the 36th IMAC, A Conference and Exposition on Structural Dynamics 2018",
    address = "Germany",

    }

    Dossogne, T, Trillet, P, Schoukens, M, Bernay, B, Noël, JP & Kerschen, G 2018, Nonlinearities of an aircraft piccolo tube: Identification and modeling. in R Barthorpe (redactie), Model Validation and Uncertainty Quantification - Proceedings of the 36th IMAC, A Conference and Exposition on Structural Dynamics 2018: Proceedings of the 36th IMAC, A Conference and Exposition on Structural Dynamics 2018. vol. 3, Conference Proceedings of the Society for Experimental Mechanics Series , Springer, Cham, blz. 57-59, Orlando, Verenigde Staten van Amerika, 12/02/18. DOI: 10.1007/978-3-319-74793-4_8

    Nonlinearities of an aircraft piccolo tube : Identification and modeling. / Dossogne, T.; Trillet, P.; Schoukens, M.; Bernay, B.; Noël, J.P.; Kerschen, G.

    Model Validation and Uncertainty Quantification - Proceedings of the 36th IMAC, A Conference and Exposition on Structural Dynamics 2018: Proceedings of the 36th IMAC, A Conference and Exposition on Structural Dynamics 2018. redactie / Robert Barthorpe. Vol. 3 Cham : Springer, 2018. blz. 57-59 (Conference Proceedings of the Society for Experimental Mechanics Series ).

    Onderzoeksoutput: Hoofdstuk in Boek/Rapport/CongresprocedureConferentiebijdrageAcademicpeer review

    TY - GEN

    T1 - Nonlinearities of an aircraft piccolo tube

    T2 - Identification and modeling

    AU - Dossogne,T.

    AU - Trillet,P.

    AU - Schoukens,M.

    AU - Bernay,B.

    AU - Noël,J.P.

    AU - Kerschen,G.

    PY - 2018/7/31

    Y1 - 2018/7/31

    N2 - Piccolo tubes are parts of aircraft wings anti-icing system and consist of titanium pipes inserted into the internal structure of the slat. Due to differential thermal expansion, clearances between the tube and its support are unavoidable and cause the overall system to exhibit highly nonlinear behavior, resulting from impacts and friction. This paper addresses the identification and modeling of the nonlinearities present in the slat-Piccolo tube connection. The complete identification procedure, from nonlinearity detection and characterization to parameter estimation, is carried out based upon sine-sweep measurements. The use of several techniques, such as the acceleration surface method, enables to understand the complex dynamics of the Piccolo tube and build a reliable model of its nonlinearities. In particular, the parameters of nonsmooth nonlinear stiffness and damping mechanisms are estimated. The nonlinear model is finally validated on standard qualification tests for airborne equipments.

    AB - Piccolo tubes are parts of aircraft wings anti-icing system and consist of titanium pipes inserted into the internal structure of the slat. Due to differential thermal expansion, clearances between the tube and its support are unavoidable and cause the overall system to exhibit highly nonlinear behavior, resulting from impacts and friction. This paper addresses the identification and modeling of the nonlinearities present in the slat-Piccolo tube connection. The complete identification procedure, from nonlinearity detection and characterization to parameter estimation, is carried out based upon sine-sweep measurements. The use of several techniques, such as the acceleration surface method, enables to understand the complex dynamics of the Piccolo tube and build a reliable model of its nonlinearities. In particular, the parameters of nonsmooth nonlinear stiffness and damping mechanisms are estimated. The nonlinear model is finally validated on standard qualification tests for airborne equipments.

    KW - Acceleration surface method (ASM)

    KW - Aircraft anti-icing system

    KW - Contact force model

    KW - Finite element model updating

    KW - Finite element model upgrading

    KW - Nonlinear system identification

    KW - Piccolo tube

    KW - Vibroimpact

    UR - http://www.scopus.com/inward/record.url?scp=85061101065&partnerID=8YFLogxK

    U2 - 10.1007/978-3-319-74793-4_8

    DO - 10.1007/978-3-319-74793-4_8

    M3 - Conference contribution

    SN - 978-3-319-74792-7

    VL - 3

    T3 - Conference Proceedings of the Society for Experimental Mechanics Series

    SP - 57

    EP - 59

    BT - Model Validation and Uncertainty Quantification - Proceedings of the 36th IMAC, A Conference and Exposition on Structural Dynamics 2018

    PB - Springer

    CY - Cham

    ER -

    Dossogne T, Trillet P, Schoukens M, Bernay B, Noël JP, Kerschen G. Nonlinearities of an aircraft piccolo tube: Identification and modeling. In Barthorpe R, redacteur, Model Validation and Uncertainty Quantification - Proceedings of the 36th IMAC, A Conference and Exposition on Structural Dynamics 2018: Proceedings of the 36th IMAC, A Conference and Exposition on Structural Dynamics 2018. Vol. 3. Cham: Springer. 2018. blz. 57-59. (Conference Proceedings of the Society for Experimental Mechanics Series ). Beschikbaar vanaf, DOI: 10.1007/978-3-319-74793-4_8