Abstract
At designing aircraft, much attention is given to the wing, as one of the most critical elements of the airframe. It is necessary to have a clear-eyed outlook at response sequence, efficiency of various factors and calculation features on the receipt timing and quality of the result. In addition, the design of a structural element is a complex multidisciplinary task affecting various fields of science, which is complicated by the use of polymer composite materials. In the furtherance of solving the urgent task of the methods of designing of a polymer composite wing, it is necessary to determine the influence of wing deformation on the airload used in the calculation and determination of product parameters. Methods of designing of a polymer composite wing used at the initial stages and taking into account the choice of the external appearance, justification of the structural arrangement and load-bearing elements. The paper considers the flow of air over the wing of a passenger airliner and analyzes the pressure values for various flight modes. A comparison is made of the initial theoretical wing surface and deformed during flight, and the difference in loading of the considered options is determined. A future methodology of polymer composite wing design based on parametric modelling will take these results into account and make use of them.
Highlights
much attention is given to the wing
which is complicated by the use of polymer composite materials
necessary to determine the influence of wing deformation on the airload used in the calculation
Summary
В рамках решения актуальной задачи по составлению методики проектирования крыла из ПКМ, применяемой на начальных этапах и учитывающей выбор внешнего облика, обоснование конструктивно-силовой схемы и отдельных силовых элементов, необходимо определить степень влияния деформации крыла на получаемые нагрузки, используемые при расчете и определении параметров изделия. В работе рассмотрено обтекание воздушным потоком крыла пассажирского авиалайнера и проанализированы величины давления при различных режимах полета. Проведено сравнение исходной теоретической поверхности крыла и деформированной при полете, а также определено различие в нагружении рассмотренных вариантов. Результаты будут учтены и использованы при составлении методики проектирования крыла из ПКМ на основе параметрического моделирования. На аэродинамические характеристики оказывают влияния такие факторы, как компоновка [1] с учетом двигателя [2] и механизации [3], обледенение поверхности при полетах в облаках с различным фазовым составом [4; 5].
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