YaBeSH Engineering and Technology Library

    • Journals
    • PaperQuest
    • YSE Standards
    • YaBeSH
    • Login
    View Item 
    •   YE&T Library
    • ASCE
    • Journal of Aerospace Engineering
    • View Item
    •   YE&T Library
    • ASCE
    • Journal of Aerospace Engineering
    • View Item
    • All Fields
    • Source Title
    • Year
    • Publisher
    • Title
    • Subject
    • Author
    • DOI
    • ISBN
    Advanced Search
    JavaScript is disabled for your browser. Some features of this site may not work without it.

    Archive

    Test and Simulation of Horizontal Tail Leading Edge Impacted by Bird

    Source: Journal of Aerospace Engineering:;2022:;Volume ( 035 ):;issue: 005::page 04022057
    Author:
    Jun Liu
    ,
    Chunyang Zhang
    ,
    Zhibin Wu
    ,
    Zhengli Zhang
    DOI: 10.1061/(ASCE)AS.1943-5525.0001454
    Publisher: ASCE
    Abstract: In this paper, the finite-element (FE) method combined with smoothed particle hydrodynamic (SPH) method is used to simulate the bird strike process, and a new type of tail leading edge structure is designed. This kind of bird is represented by the SPH model, and the structure is simulated by traditional Lagrangian elements. The design for the novel structure can be described as incorporating a triangular reinforcement component into traditional tail leading edge structure. Numerical simulations of bird strikes with the novel structure indicate that the anti-bird-strike capacity of the new type of tail leading edge is greatly enhanced. Then, the corresponding bird strike tests are carried out to verify the numerical simulation model. The simulation results are in good agreement with the test results, indicating that the SPH-FE coupling method gives a useful tool for predicting the deformation and damage behavior of aircraft structure under bird impact, and for the design of bird-strike-resistant structure. Finally, through bird strike simulation and test of the horizontal tail leading edge with the new design of commercial aircraft, it can be observed that the front beam does not penetrate, which indicates that the new design meets the requirements of the China Civil Aviation Regulations (CCAR) Part 25 on the certification of the bird strike resistance of the wing leading edge.
    • Download: (3.160Mb)
    • Show Full MetaData Hide Full MetaData
    • Get RIS
    • Item Order
    • Go To Publisher
    • Price: 5000 Rial
    • Statistics

      Test and Simulation of Horizontal Tail Leading Edge Impacted by Bird

    URI
    http://yetl.yabesh.ir/yetl1/handle/yetl/4286287
    Collections
    • Journal of Aerospace Engineering

    Show full item record

    contributor authorJun Liu
    contributor authorChunyang Zhang
    contributor authorZhibin Wu
    contributor authorZhengli Zhang
    date accessioned2022-08-18T12:15:13Z
    date available2022-08-18T12:15:13Z
    date issued2022/05/18
    identifier other%28ASCE%29AS.1943-5525.0001454.pdf
    identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4286287
    description abstractIn this paper, the finite-element (FE) method combined with smoothed particle hydrodynamic (SPH) method is used to simulate the bird strike process, and a new type of tail leading edge structure is designed. This kind of bird is represented by the SPH model, and the structure is simulated by traditional Lagrangian elements. The design for the novel structure can be described as incorporating a triangular reinforcement component into traditional tail leading edge structure. Numerical simulations of bird strikes with the novel structure indicate that the anti-bird-strike capacity of the new type of tail leading edge is greatly enhanced. Then, the corresponding bird strike tests are carried out to verify the numerical simulation model. The simulation results are in good agreement with the test results, indicating that the SPH-FE coupling method gives a useful tool for predicting the deformation and damage behavior of aircraft structure under bird impact, and for the design of bird-strike-resistant structure. Finally, through bird strike simulation and test of the horizontal tail leading edge with the new design of commercial aircraft, it can be observed that the front beam does not penetrate, which indicates that the new design meets the requirements of the China Civil Aviation Regulations (CCAR) Part 25 on the certification of the bird strike resistance of the wing leading edge.
    publisherASCE
    titleTest and Simulation of Horizontal Tail Leading Edge Impacted by Bird
    typeJournal Article
    journal volume35
    journal issue5
    journal titleJournal of Aerospace Engineering
    identifier doi10.1061/(ASCE)AS.1943-5525.0001454
    journal fristpage04022057
    journal lastpage04022057-9
    page9
    treeJournal of Aerospace Engineering:;2022:;Volume ( 035 ):;issue: 005
    contenttypeFulltext
    DSpace software copyright © 2002-2015  DuraSpace
    نرم افزار کتابخانه دیجیتال "دی اسپیس" فارسی شده توسط یابش برای کتابخانه های ایرانی | تماس با یابش
    yabeshDSpacePersian
     
    DSpace software copyright © 2002-2015  DuraSpace
    نرم افزار کتابخانه دیجیتال "دی اسپیس" فارسی شده توسط یابش برای کتابخانه های ایرانی | تماس با یابش
    yabeshDSpacePersian