Dynamic tests of composite panels of an aircraft wing

Šplíchal, Jan; Píštěk, Antonín; Hlinka, Jiří

doi:10.1016/j.paerosci.2015.05.005

Cited by 11 publications

(7 citation statements)

References 7 publications

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“…Figure (13) shows the variation of acceleration with frequency at attack angle of 20º.From this figure can be observed the decrease in the acceleration values in the case and all the sensors except S 3 record the same values of the previous situation almost. The acceleration values in this case fluctuated between (0.01 m/s 2 to 0.09 m/s 2 ) during the process, the maximum value for S 1 0.12 m/s 2 at period 16 7 Hz, S 2 0.11 m/s 2 at 10 Hz, S3 0.096 m/s 2 at 42 Hz and S 4 0.095 m/s 2 at 40 Hz.…”

Section: Vibration Analysismentioning

confidence: 76%

“…Today, structural weight and stiffness requirements have exceeded the capability of conventional aluminum, and high-performance payloads have demanded extreme thermo-elastic stability in the aircraft design environment (Prabhu et al, 2015). Composite materials with continuous fibers are the most suitable option especially (polymer matrix composites reinforced) because of the requirements that must be provided in structure of UAVs, where must be high-strength and lightweight (Sethunathan et al, 2016, Splichal et al, 2015, these composites are reflected in the UAV industry. In this paper the vibrations generated in the wing of UAVs as a result of wind waves is presented.…”

Section: Introductionmentioning

confidence: 99%

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Pseudorandom Noise Impulsive Response Analysis and Aerodynamic Forces of Unmanned Aerial Vehicle Structure

Salman¹,

Mohsen²,

Abttan³

2019

ujme

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This paper concentrated about the effect of both the pseudorandom or random vibration (wind waves) and aerodynamic forces on the wing of unmanned aerial vehicle, which brought the attention of specialists in this field during last years, the performance of wing is improved on a definitive solution for the vibration problems which cause failure in the wings of UAV. The distribution of stresses and distortions with aerodynamic loads is studied. Factors such as tension, pressure and shear stress showed on wing of UAVs due to vibration which caused the structure of wing to break down and then failure. The experimental study was carried out by using wing made of composite material (foam and cover by lamination plate), where airfoil type (NACA Clark y) installed inside wind tunnel of low velocity. It is found that the vibration acceleration at constant wind velocity with variation of attack angle of the wing, it is obtained the relationship between the acceleration and the frequency using the LABVEIW program which analyzed and identified the distribution of forces on the wing. The stress concentration areas is created and found under failure occurs, the aerodynamic force, torsion torque and magnitude of deformation is calculated. It is concluded that the close areas from the root wing (fixed end) is most likely to collapse or break.

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Section: Vibration Analysismentioning

confidence: 76%

Section: Introductionmentioning

confidence: 99%

Pseudorandom Noise Impulsive Response Analysis and Aerodynamic Forces of Unmanned Aerial Vehicle Structure

Salman¹,

Mohsen²,

Abttan³

2019

ujme

View full text Add to dashboard Cite

show abstract

“…For aerospace applications it can be noticed that the shell elements are common choices for the wing skin, spar and rib models made of the layered composite materials [15][16][17][18]. FEM software can be used for the structural analysis of, for example, the composite wing made of woven carbon epoxy of unmanned aerial vehicle (UAV) [15].…”

Section: Description Of Experimental Resultsmentioning

confidence: 99%

“…Another example of aircraft component which is subjected to finite element analysis can be part of the wing leading edge made of GLARE laminates [16]. Moreover, small segments of the aircraft wing as carbon fiber reinforced composite wing panels can be analyzed using FEM [17]. The finite element analysis (FEA) can be also conducted for the optimization process e.g.…”

Section: Description Of Experimental Resultsmentioning

confidence: 99%

Verification of FEM modelling of composite materials based on the results of static strength test

Gojny

2019

Mechanik

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The article presents the verification of FEM modelling of composite materials based on the results of static strength test. The aim of the work was to examine whether the applied modelling of composite materials is correct and verify it with finite element method (FEM). The composite structure of the PW-6U glider was used as a model. In the program the numerical model (geometry and finite element mesh) of the glider’s wing was created. The wing is made of glass fabrics and a spar with flanges with a glass roving. The composite structure of the wing, including composition, layout and thickness of laminate layers, fiber arrangement was exactly modelled in the program and then subjected to loads. Having the measurements from the static strength tests of the glider, the numerical results were compared with the experimental results. Thanks to the applied modelling, the obtained numerical results were satisfactory and very close to the experimental results from the structural static tests of the glider. Therefore, it can be concluded that the conducted verification of FEM modelling of composite materials is correct. Nowadays application of composite materials is increasingly expanding. Therefore, the modelling of composites becomes a significant issue. FEM modeling allows verification of the structure. At the stage of modelling modifications can be implemented and thus time and costs associated with subsequent changes in the production process may be saved. This is a very good solution which already at the design stage of the structure allows examination of its strength.

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“…Для снижения импульсных и вибрационных нагрузок в конструкциях применяют пористые элементы в виде гранулированных слоев, проволочных решеток, экранов, сеток, перфорированных перегородок [1][2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19]. В частности, для защиты силовых корпусов взрывных камер от осколочного повреждения в настоящее время применяются многослойные металлические сетки тканого плетения [20,21].…”

Section: Introductionunclassified

Numerical modeling of nonlinear dynamic and static compression of the metal mesh

Kochetkov

Modin

Leont’ev

et al. 2019

PNRPU Mechanics Bulletin

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Simulation of elastoplastic compression of a symmetric fragment of a bundle of woven steel grids was carried out. The simulation was carried out under static and dynamic loading modes in ANSYS and ANSYS LS-DYNA computing systems. A porous mesh package is formed by overlaying the layers on top of each other while maintaining the directions of wires. Such a packet has a quasiperiodic structure; therefore, a certain symmetric fragment can be distinguished. The compression was carried out by a pair of absolutely rigid plates moving symmetrically towards each other. In the calculations, a multilinear plasticity model with isotropic hardening was used. The diagram of static deformation of the material was used which was obtained experimentally. The calculations were carried out according to the algorithm of a perfect symmetric contact of bodies without friction and with friction. The dynamic loading of a fragment of the mesh packet was carried out at a constant speed. The characteristics of the pulse and the loading rate correspond to those observed in previous experimental studies. The dynamic strain diagram was assumed to be similar to a static one with an increased yield strength. Calculations showed that in all loading modes there is a high level of internal stresses, and complex inhomogeneous stress-strain state. We investigated two factors that could cause differences in the behavior of the curves of deformation of a porous medium - the finite length of the acting pulse and the differences in the dynamic and static compression diagrams of the initial mesh material. The main influence on the dynamic behavior of a fragment of a porous packet of a steel mesh is exerted by the dynamic properties of the wire material. The strain curves of the porous fragment qualitatively change in accordance with the behavior observed in static and dynamic experiments. The final duration of the loading pulse and the friction between the wires for this type of mesh do not have a significant effect. The numerical dependences of the relative area of the normal and lateral through sections of the symmetric fragment of the grid packet on the compression deformation are obtained.

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Dynamic tests of composite panels of an aircraft wing

Cited by 11 publications

References 7 publications

Pseudorandom Noise Impulsive Response Analysis and Aerodynamic Forces of Unmanned Aerial Vehicle Structure

Pseudorandom Noise Impulsive Response Analysis and Aerodynamic Forces of Unmanned Aerial Vehicle Structure

Verification of FEM modelling of composite materials based on the results of static strength test

Numerical modeling of nonlinear dynamic and static compression of the metal mesh

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