Московский авиационный институт (Национальный исследовательский университет) Предложена аналитическая уточненная методика проектирования сжатых подкрепленных композитных панелей, основанная на условии равноустойчивости. Модификация исходной методики проведена за счет учета ударных повреждений обшивки. На основе результатов параметрического анализа сделан вывод об ограничении энергии ударного воздействия для программ испытаний панелей крыла легкого самолета. An analytical refined technique for designing compressed stiffened composite panels based on the condition of equal to stability. Modification of the original technique was carried out by taking into account regulated damage to the skin. Based on the results of parametric analysis, it is concluded that the impact energy is limited for testing programs of light aircraft wing panels.

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Приведены исследования устойчивости композитных панелей с учетом сквозных трещин (надрезов) при нагружении сжимающими потоками. Полученные результаты могут являться понижающими коэффициентами при оценке местной устойчивости обшивки подкрепленных композитных панелей. Investigations of the stability of composite panels, taking into account full depth crack (incisions) when loaded with compressive flows, are presented. The results obtained can be reducing coefficients in assessing the local stability of the skin of stiffened composite panels.

Предложена уточненная аналитическая методика проектирования сжатых подкрепленных металлических панелей, основанная на условии равноустойчивости, и модифицированная за счет учета сквозных повреждений в обшивке. Проведены параметрических исследований влияния расположения сквозного отверстия на критические напряжения обшивки при сжатии. The paper proposes analytical techniques for designing stiffened metal panels the use of the condition of uniform stability and modified by taking into account through damage in the skin. Parametric studies of the effect of the location of the through hole on the critical stresses of the skin during compression have been carried out.

When designing thin-walled aircraft structures, as a rule, the main limitations are associated with ensuring stability. The objects of research in this work are composite z-shaped reinforced panels of the wing box of an aircraft. For the early stages of the design of load-bearing panels, it is necessary to evaluate the weight of the design decisions made, taking into account possible defects. The paper proposes an analytical technique for designing reinforced panels, taking into account the use of the condition of uniform stability and the presence of possible regulated defects in the skin that may occur in further operation. The task of determining the parameters of panels of minimum weight is reduced to minimizing the function of one variable, which is the ratio of the height to the reinforcement step. To take into account the indicated regulated defects, parametric studies were carried out using the finite element method, on the basis of which refinement coefficients were added to the analytical ratios of the stiffness parameters of the reinforced panels. The paper presents the results of studies of orthotropic panels with defects in the form of through holes under loading with compressive and tangential forces. The results are presented in the form of graphs that show possible changes in the critical stresses of thin skins with defects.