Fuzzy uncertainty analysis in the flutter boundary of an aircraft wing subjected to a thrust force

被引:9
|
作者
Rezaei, M. [1 ]
Fazelzadeh, S. A. [1 ]
Mazidi, A. [2 ]
Khodaparast, H. Haddad [3 ]
机构
[1] Shiraz Univ, Sch Mech Engn, Ghasro Dasht St, Shiraz, Iran
[2] Yazd Univ, Sch Mech Engn, Yazd, Iran
[3] Swansea Univ, Coll Engn, Swansea, W Glam, Wales
关键词
Uncertainty; flutter; aircraft wing; thrust force; fuzzy method; non-probabilistic; INTERVAL-ANALYSIS METHOD; DYNAMIC-RESPONSE; PARAMETERS; MODELS; AIRFOIL;
D O I
10.1177/0954410018773898
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
In this study, flutter uncertainty analysis of an aircraft wing subjected to a thrust force is investigated using fuzzy method. The linear wing model contains bending and torsional flexibility and the engine is considered as a rigid external mass with thrust force. Peters' unsteady thin airfoil theory is used to model the aerodynamic loading. The aeroelastic governing equations are derived based on Hamilton's principle and converted to a set of ordinary differential equations using Galerkin method. In the flutter analysis, it is assumed that the wing static deflections do not have influence on the results. The wing bending and torsional rigidity, aerodynamic lift curve slope and air density are considered as uncertain parameters and modelled as triangle and trapezium membership functions. The eigenvalue problem with fuzzy input parameters is solved using fuzzy Taylor expansion method and a sensitivity analysis is performed. Also, the upper and lower bounds of flutter region at different alpha-cuts are extracted. Results show that this method is a low-cost method with reasonable accuracy to estimate the flutter speed and frequency in the presence of uncertainties.
引用
收藏
页码:2185 / 2197
页数:13
相关论文
共 39 条
  • [1] Analytical nonlinear flutter and sensitivity analysis of aircraft wings subjected to a transverse follower force
    Zafari, E.
    Jalili, M. M.
    Mazidi, A.
    [J]. PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING, 2019, 233 (04) : 1503 - 1515
  • [2] Flight loads and flutter analysis of the joined wing aircraft
    Zhang, Bo-Cheng
    Wan, Zhi-Qiang
    Yang, Chao
    [J]. Gongcheng Lixue/Engineering Mechanics, 2010, 27 (08): : 229 - 233
  • [3] Bending-Torsional Flutter of a Composite Rectangular Cantilever Wing Subjected To Engine Thrust
    Amoozgar, Mohammad Reza
    Irani, Saied
    [J]. ADVANCED MATERIALS RESEARCH II, PTS 1 AND 2, 2012, 463-464 : 1568 - 1572
  • [4] Aeroelastic response of an aircraft wing with mounted engine subjected to time-dependent thrust
    Mazidi, A.
    Kalantari, H.
    Fazelzadeh, S. A.
    [J]. JOURNAL OF FLUIDS AND STRUCTURES, 2013, 39 : 292 - 305
  • [5] AEROELASTIC ANALYSIS OF A THIN-WALLED COMPOSITE AIRCRAFT WING WITH AN EXTERNAL STORE SUBJECTED TO A FOLLOWER FORCE
    Aksongur, Alev Kacar
    Eken, Seher
    Kaya, Metin O.
    [J]. PROCEEDINGS OF THE ASME INTERNATIONAL MECHANICAL ENGINEERING CONGRESS AND EXPOSITION, 2014, VOL 1, 2015,
  • [6] RESPONSE CHARACTERISTICS OF A 2-DIMENSIONAL WING SUBJECTED TO TURBULENCE NEAR THE FLUTTER BOUNDARY
    MATSUZAKI, Y
    TORII, H
    [J]. JOURNAL OF SOUND AND VIBRATION, 1990, 136 (02) : 187 - 199
  • [7] Flutter Analysis of a 3D Box-Wing Aircraft Configuration
    Ghasemikaram, Amirhossein
    Mazidi, Abbas
    Fazelzadeh, S. Ahmad
    Scholz, Dieter
    [J]. INTERNATIONAL JOURNAL OF STRUCTURAL STABILITY AND DYNAMICS, 2022, 22 (02)
  • [8] BENDING-TORSIONAL FLUTTER OF A CANTILEVERED WING CONTAINING A TIP MASS AND SUBJECTED TO A TRANSVERSE FOLLOWER FORCE
    FELDT, WT
    HERRMANN, G
    [J]. JOURNAL OF THE FRANKLIN INSTITUTE-ENGINEERING AND APPLIED MATHEMATICS, 1974, 297 (06): : 467 - 478
  • [9] Modeling and analysis of a geometrically nonlinear joined wing under thrust force
    Liang, Jiahua
    Bai, Junqiang
    Sun, Zhiwei
    Wang, Hui
    Zhang, Bo
    Chang, Min
    [J]. JOURNAL OF SOUND AND VIBRATION, 2023, 544
  • [10] SUPERSONIC BOUNDARY-LAYER STABILITY ANALYSIS ON AN AIRCRAFT WING
    AGRAWAL, S
    KINARD, TA
    POWELL, AG
    [J]. JOURNAL OF AIRCRAFT, 1991, 28 (11): : 721 - 727