Design Computations Procedure of the Dynamically Similar Model of a Composite Wing with the Torsion-Box Type Configuration

Design of the Flying Vehicles Elements from Polymer Composite Materials


Аuthors

Komissarova A. O.*, Ishmuratov F. Z.**

Central Aerohydrodynamic Institute named after N.E. Zhukovsky (TsAGI), 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia

*e-mail: Vyacheslav.chedric@tsagi.ru
**e-mail: fanil.ishmuratov@tsagi.ru

Abstract

The article deals with the procedure development for the stiffness characteristics designing of a dynamically similar wing model from composite materials by a box-beam scheme. The research relevance is driven by the need for rapid estimation of bending and torsional stiffness at early design stages, where application of, for example, a full-scale finite element models is impractical due to high labor intensity and time costs.
The developed methodology is based on the beam idealization for computational studies of flutter in the high-aspect-ratio wings. To achieve this, the stiffness characteristics in each section are specified by the bending stiffness in two planes and torsional stiffness. The beam stiffness computing is being conducted by the formulas for geometric characteristics determining of the cross-sections from the courses on strength of materials and structural mechanics. As the result of this procedure running, the following data is being determined: the required number of laminates and reinforcing angles for each control section.
The computational procedure includes several sequential stages. At the first stage, the geometry is prepared, namely the check sections are selected, and the wing box position is defined. At the second stage, the effective elastic characteristics of the laminate (multilayer composite material) are being determined by the classical lamination theory. The next stage is responsible for the bending and torsional stiffness computing, following which an equation (or system of equations) is being solved and the required thickness, or in other words, the required number of laminates, is being determined. At the final stage, the layup angles are being determined by an optimization method based on a genetic algorithm.
For the proposed technique implementation, a computational procedure, developed with MATLAB, which automates the laminate parameters selection and their quantity has been developed. The box wing of a dynamically scaled model with a high aspect ratio of λ = 11.5 was selected as the object for numerical simulation. The algorithm allows the designer to select a permissible box-beam scheme based on the design and technological constraints. The presented article proposes and considers two typical cross-section configurations. The second cross-section option ensures the best approximation to the required stiffness characteristics for the presented numerical wing model. It may be concluded by the numerical simulation results that this procedure is capable of ensuring the results convergence up to 10%. This allows ensuring the necessary accuracy for the aeroelastic phenomena correct modeling.
The developed technique verification was performed by comparing the computational results with the data obtained by the finite element method with the Nastran software. The comparative analysis revealed that the discrepancy in the bending stiffness did not exceed 6%, and 10% in the torsional stiffness, which confirms correctness of the adopted assumptions and sufficient engineering accuracy of the proposed approach for application at early design stages. The design calculation execution time herewith takes several minutes, which significantly reduces the “manual enumeration” time or full-scale finite element modeling.

Keywords:

dynamically scaled wing model, composite materials, stiffness characteristics, spar box designing procedure

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