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Weight optimization of a composite wing-panel with flutter stability constraints by ply-drop

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Abstract

The existing approach in aircraft wing design optimizes the structure for strength and buckling design criteria followed by a flutter stability check, which leads to design that may not be optimal. This study proposes the flutter stability as an integral of weight optimization by a two-step procedure. Step 1 comprises series of flutter and static analyses of finite element (FE) models with different weapon configurations and aerodynamic loads, which give limiting values of wing tip deflection and wing twist as flutter constraints. Step 2 focuses on weight optimization of the laminate for strength and stiffness design parameters along with the flutter constraints. The algorithm minimizes structural weight by ply drop, which is based on evaluation of the fitness value of laminates generated by a stochastic operator. The ply drop design algorithm is applied to optimize the FE model of a fourth-generation fighter aircraft wing box with three representative aerodynamic loads and three weapon configurations. The application evolved optimal laminate with seamless and symmetric plies, which has 35% lesser weight compared with the initial model having quasi-isotropic laminates for given strength and flutter stability design requirement. The application of genetic algorithm (GA) to get an initial laminate instead of quasi-isotropic laminates further improved the design by 2.5% weight reduction.

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Authors and Affiliations

  1. Department of Aerospace Engineering, Indian Institute of Technology Kanpur, Kanpur, UP, 208016, India

    Sachin Shrivastava & P. M. Mohite

  2. AURDC, Hindustan Aeronautics Limited, Nasik, MH, 422207, India

    Hitesh Tilala

  3. R&D Engineers, DRDO, Pune, MH, 411015, India

    M. D. Limaye

Authors
  1. Sachin Shrivastava
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  2. Hitesh Tilala
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  3. P. M. Mohite
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  4. M. D. Limaye
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Correspondence to P. M. Mohite.

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Responsible Editor: Yoojeong Noh

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Replication of results

The FE model files for replication of results at the initial and final design point, Optimization Code, Python-Scripts, ABAQUS UMAT to evaluate Tsai-Wu Failure Index, the internal function of optimization code viz. SOLVECAE, PLOTTING will be made available to the readers on request for non-commercial purpose only.

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Shrivastava, S., Tilala, H., Mohite, P.M. et al. Weight optimization of a composite wing-panel with flutter stability constraints by ply-drop. Struct Multidisc Optim 62, 2181–2195 (2020). https://doi.org/10.1007/s00158-020-02569-5

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  • DOI: https://doi.org/10.1007/s00158-020-02569-5

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