The Methods of Designing a Polymer Composite Wing Using Parametrical Modeling. Part III. Selection and Justification of Optimal Schemes for Reinforcing Load Bearing Elements

In modern airliners, to ensure perfect operation of both lightly loaded elements as well as crucial assemblies such as wings, polymer composite materials are used. These provide characteristics that would be impossible if conventional metal alloys were used. Due to the specifics of geometry, creating a polymer composite wing is a complex engineering task, where a key element is the selection and justification of reinforcing schemes with regard to anisotropy of the material and adaptation of the material characteristics to the acting forces. In this work, a challenging problem of determining and optimizing structural parameters of the main load bearing elements of a carbon fibre wing using rational reinforcing schemes is considered. Wall thickness values, layup patterns of unidirectional layers and safety margins of the elements of the wing structural arrangement are determined with regard to acting operational loads for several angle of attack corresponding to different flight modes. The study results complement the proposed method of designing a polymer composite wing based on parametrical modelling.

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