Wyniki wyszukiwania - Biblioteka Nauki

1

Harmonical and modal analysis to determine the anisotropic properties of aviation composite materials

100%

Acopyan A. , Axenov V. , Shevtsov V. , Soloviev A. , Tamarkina E.

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tom Vol. 14, No. 3

11-18

EN

The value of all composite elastic modules has the crucial influence on dynamic behaviour of aviation load-bearing structures. Numerous experimental techniques and standards are used to characterize the elastic properties of polymeric composite materials. Among this is the large group of static tests, acoustic methods based on longitudinal, lateral or shear surface sound wave speed measurements and also on vibrating surfaces amplitude measurements. However, preparation specimens for static test with shape required by standards not always possible from already manufactured piece. Again the designated dynamic experiment introduces difficulties of investigated specimen acoustic isolating, impossibility of some required wave type excitation and performing of displacements field measurement with guaranteed precision. In this study an acoustic method is developed using the measure of all specimen's eigenfrequencies in a certain frequency range. Small rectangular composite specimen is excited by glued piezoelectric actuator and response is measured by piezoelectric sensor. Preliminary performed finite-element (FE) analyses serve to think the vibration natural modes of linked mechanical system - specimen and piezoelectric element. In this FE analyse the rough estimations of all elastic constants obtained from other independents (as a rule static) experiments were used. Further the amelioration of initial elastic modules was performed. Thereby the target nonlinear functional dependent on all quest modules was minimized by genetic and (or) Levenberg-Marquardt algorithm.

2

Numerical simulation of fatigue delamination growth under mode I loading conditions

100%

Bajurko P. , Czajkowska K. , Czarnocki P. , Szeląg D.

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tom Vol. 19, No. 2

17-24

EN

Delaminations are common defects that deteriorate strength of laminates. Delaminations can arise in the course of manufacturing due to faulty fabrication process or can result from low energy impacts, (e.g. FOD), that can take place in service. Once a delamination has been detected, a question will arise whether the defective component can still stay in service or should be immediately repaired or replaced. Before the decision is made, one of the factors that must be considered is a possible delamination growth rate under the expected service cyclic loading. One of the most effective tools that help to answer this question is a numerical simulation of delamination growth. Relatively easy way to simulate fatigue delamination growth under Mode I loading conditions is presented. The a=f(n) relationship was simulated. The simulation was performed with the help of FEM. The delamination extension resulted from gradual reduction in the stiffness of cohesive elements of length t that were located along the expected delamination path. It was assumed that the delamination would extend by delta a=t if the cohesive element stiffness dropped to 0. The applied degradation procedure of the initial mechanical properties of the cohesive elements was based on Paris low. For each delamination, extension increment the degradation process was limited to the cohesive element adjacent to the delamination front. In case of laminates, so far, there is no standard procedure available to determine Paris low and the one used to determine it for the purpose of the simulation performed is presented, as well. The simulation was ended when the number of cycles simulated exceeded 1000 000. The numerical results were verified against the experimental ones resulting from the four specimens tested and a satisfactory agreement was found. The difference between the a=f(n) relationship obtained by the simulation and the one being the average of the four tests was smaller than the scatter of the tests results.

3

Skręcanie nieswobodne cienkich zamkniętych profili z kompozytu

72%

Lewiński J. , Wilczyński A.

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tom R. 9, nr 4

384-389

PL

Przedstawiono rozwiązanie problemu nieswobodnego skręcania cienkich, zamkniętych profili kompozytowych. Zagadnienie to, opracowane dla materiałów izotropowych, nie znalazło dostępnych rozwiązań teoretycznych dla gwałtownie rozwijających się konstrukcji kompozytowych, powodując nie zawsze uzasadnione użycie metod numerycznych. W pracy wykorzystano monografie dotyczące materiałów izotropowych, używając podanych tam rozwiązań i metod, do których kieruje się czytelnika, po czym wprowadzono opisy materiałów kompozytowych (anizotropowych). Rozwiązanie polega na wyprowadzeniu zależności analitycznych pozwalających na wyznaczenie rozkładu naprężeń stycznych i normalnych w ściankach profilu, a także kątów skręcenia z uwzględnieniem nieswobodnego spaczenia profilu. Dla uzyskania pełnego opisu problemu rozwiązano kolejno problem skręcania swobodnego, problem ścinania siłami poprzecznymi i skręcanie nieswobodne. Efektem analizy skręcania swobodnego (ze swobodnym spaczeniem profilu) jest wprowadzenie pojęcia uogólnionej współrzędnej wycinkowej, które to pojęcie ma zasadnicze znaczenie w analizie właściwego skręcania nieswobodnego. Rozwiązanie problemu ścinania prowadzi do wyznaczenia środka sił poprzecznych, wokół którego odbywa się właściwe skręcanie. Analiza skręcania nieswobodnego dała końcowe zależności analityczne opisujące problem. Uzyskane zależności różnią się od analogicznych zależności dla izotropii wielkościami charakteryzującymi materiały kompozytowe. Pracę zakończono przykładem rozwiązania.

EN

The paper presents a theoretical solution for torsion of thin, closed composite sections. Such problems, known for isotropic materials are not easily accessible for anisotropic composite structures despite quick development of these materials. This enforces use of not always justifiable laborious numeric methods. Constrained torsion problems and solutions were posed and developed to a great extent in the Soviet Union, starting at the begining of the thirties in the previous century and greatly, without the use of computers and applied mostly by the military aviation industry during the World War II. The presented solution is an exact extension of the known results, to which the reader is directed, to the case of anisotropic polymeric composites, using methods of description presented in several monographs, two of which can be found in the literature list. The solution is based on formulation of analytical relations, allowing for determination of normal and shear stress distributions in the wall of the tube and the angle of torsion, taking into account the warp of the profile. To obtain the full solution the problems of pure torsion, shear by transverse forces and finally the constrained torsion had to be investigated. Analysis of free torsion (with unrestricted warp possibility) led to introduction of a new quantity - the sectorial coordinate, a convenient area description in the cases of constrained torsion, replacing the possible use of higher order moments of inertia. Solution of the shear problem gave coordinates of the axis of rotation of the profile, while the case of constrained torsion allowed for calculation of normal stresses, not existing in pure torsion. Results for composite structures differ from isotropic cases only by the influence of anisotropic elasticity constants and use these values in weighted averages describing material properties. The proposed theory is used in an exemplary solution of an engineering problem, showing the straight applicability in simple cases.