Different types of techniques are used in joining of aircraft structures. The classical solutions are mechanical or bonding joining. A prospective alternative to the currently used connections (e.g. mechanical, adhesive and hybrid ones) is a socket - pin connection type. Generally, they are purely mechanical joints. Depending on the shape, they have different commercial names such as: Interlock, Snaplock, Snapfit Gridlock. The idea of these connections relies on the fact, that between the socket and the pin we need a suitable interference fit or specially formed clip to carry the load. The advantages of this type of connection of different structural parts is very fast assembly after pressing joined parts together. The use of socket - pin connection eliminates the presence of the human error and reduces production costs as an individual connection is made by CNC machine tools.The paper presents an analysis of the influence of a several technological problems concerning the socket and the pin manufacturing, on the value of force required for the joint connection and disconnection. A number of numerical simulations was made in ABAQUS program to examine the effect of such parameters as: the presence of interference fit, the use of spherical latches, the use of different rigidity in the shaft by making cuts with variable width and length, the use of different angles of inclination of the working part of the slot.
We consider one or two collinear cracks in a pre-stressed, orthotropic, linear elastic material representing a fiber reinforced elastic composite. Elastic incremental fields in the composite material, using Guzs representation theory, Cauchy-Riemann problem and critical values of incremental tangential stresses that producing crack propagation are obtained using Sihs generalized criterion.
Although aircraft carriers operating in the seas have developed considerably from a constructive point of view, naval aviation continues to face significant challenges due to short runways, often in motion or unpredictable weather conditions, as a rule. This paper aims to analyze the concept of aircraft's rapid deceleration to landing, as well as to study the dynamic behavior of the aircraft restraint system used by aircraft carriers.
In this paper is presented a study of stresses and strains due ramification to consumers of main gas pipeline. It's numerically analyzed the influence of main pipe's ramification due to modification of mechanical and geometrical parameters.
Modeled loads are based on evaluation of internal forces of thin shell and induced loads by circular weld thermal field. The study of stresses and strain it's made using finite elements method by a static tri dimensional analysis performed both for evaluation of stresses and strains in presence and absence of internal pressure.
The obtained results represent a comparative factor for technical regulation in the safety assessment in operation of natural gas pipelines.
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