In this paper a versatile and easy to use approximate procedure was used for the estimation of mode I stress intensity factors in case multiple surface cracks three dimensional elastic body, subjected remote uniaxial tensile loading. The mentioned method uses known solutions either 2D or 3D configurations containing only one crack, takes into consideration interaction effect between cracks. This procedure, which is based on principle superposition, applied configuration with coplanar...

In this paper determination of mechanical properties composite material using experimental and numerical approach is presented. The a laminate obtained in the experiment are used for verification numerically values, as well estimation load-carrying capacities engine cover light aircraft. Composite specimens, consisting epoxy matrix glass fibers with orientation angles 0º, 450, 900, have been made according to standards, were investigated tensile three-point bending tests. strength,...

The main goal of this paper is to expand previously conducted study and consequently upgrade the proposed multimodular numerical framework developed for fluid–structure interaction simulation (FSI) multidisciplinary design optimization (MDO) purposes, in a manner that thermal–structure observed implemented into established framework. upgraded considerably improved algorithm was used MDO short-range ballistic missile (SRBM) model. Because its high-speed regimes, aircraft model selected...

Attention in this work is focused on aerodynamic heating and aero-thermo-mechanical analysis of fin type structures the missile at supersonic flight. At high Mach number heat due to friction between body flow, i.e. viscous must be taken into account because velocity field coupled with temperature field. The flow around fins especially distribution its surface, as well aerodynamic-thermal-structural analyses are numerically modeled ANSYS Workbench environment. investigation was carried out...

Paper explores some aspects of 3D modeling ‘aircraft cable’ as mostly used sling wire rope. First, the 1×19 stainless steel core was investigated. The analysis carried out by finite element method based computer program. software allowed two different types contacts, including friction. rope subjected to axial loading. obtained results were compared with solutions calculated from literature (Costello 2012). Finally, using advanced techniques, parametric model 7×19 analyzed method, in order...

This paper presents the application of extended finite element method (XFEM) in crack propagation simulation on integral wing spar that should replace existing differential light aircraft UTVA 75.Numerical model was developed software Abaqus.Stress intensity factors (SIFs) were calculated using add-in Morfeo/Crack for Abaqus and obtained number cycles would propagate to certain length compared experimentally spar.Numerical analysis showed with same dimensions as has significant increase...

The aim of this paper is to explore and demonstrate the capacity, performances difficulties stress intensity factors (SIFs) calculations in a case multiple cracks on curved panels analyzed by means different computational methods. So-called bulging effect, which occurring cracked panels, increases effective stress-intensity factor, making SIFs assessment more challenging. Here, are considered using two methods: extended finite element method (XFEM) approximate based superposition, has been...

This paper deals with the damage growth in High-Pressure Turbine (HPT) cooling holes of case assembly made Inconel 718. Several marks (cuts) were on into parent material during service due to non-skilled use Electrical Discharge Machining (EDM) workshop. After a certain time, returned workshop all EDM cracked. Since HPT is not repairable and only method for fixing this issue its replacement new or used one (which might be pretty expensive), it was decided numerical analysis estimate Paris...

Aircraft structure is the most obvious example where functional requirements demand light weight and strong structures. Shape sizing optimization are being increasingly used nowadays for designing lightweight structural components. The aim of this paper to present I-section integral wing spar made aluminum 2024-T3. efficient design, based on optimum fatigue life, was achieved using Extended Finite Element Method (XFEM) its ability simulate crack growth in complex geometry. computations were...

The aim of this paper was to establish and demonstrate significant capacity performances extended finite element method (XFEM) calculate stress intensity factors (SIFs) histories versus crack length for problems involving multiple, interacting cracks resulting from multiple site damage (MSD).A typical aero structural configuration analysed: unstiffened flat panel made aluminium Al 2024-T3, containing 11 holes, each which is a growth.Analysed model makes unique 3D with 22 cracks, propagating...

Three different wing spar designs (differential, equivalent integral, and optimized integral) are analysed, in order to establish the optimum one. Numerical analysis was carried out by extended finite element method (XFEM) verified using experimental data for differential spar, followed of both integral spar. The design regarding fatigue life obtained analysing three cross sections