In the present work, computational analyses on aeroelastic instability of an aircraft wing are conducted. A jet fighter wing with different armament configurations is evaluated. Aeroelastic instability, i.e., divergence and flutter, occurs as the aerodynamic loads interact with the structure and may lead to a catastrophic phenomenon, i.e., amplified deformation or oscillation. In a case of a jet fighter, the armaments affect the inertial, and further, the structural dynamic characteristics of the aircraft or wing. In the current study, the variation of armament’s placement and computational model is investigated. The structure of the wing and its armaments is modelled by means of Finite Element Method (FEM). The aerodynamic model of the wing is constructed using frequency domain – based methods, Doublet Lattice Method (DLM) and Piston theory for subsonic and supersonic regimes, respectively. The shifting of armament center of gravity further from elastic axis causes flutter to occur in a lower speed. In addition, the increase in mass moment of inertia also gives the same effects.


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    Title :

    Flutter Analysis of Fighter Aircraft Wing with Installed Armament


    Additional title:

    Springer Proceedings Phys.



    Conference:

    International Seminar on Aerospace Science and Technology ; 2024 ; Bali, Indonesia September 17, 2024 - September 17, 2024



    Publication date :

    2025-02-15


    Size :

    11 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English




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