TAXATION OF LABOR INCOME IN DIFFERENT COUNTRIES THAT ARE NOT MEMBERS OF THE EUROPEAN UNION

A proper understanding of the "coordinate" system of labor income taxation of individuals in our country can be made aware of the essential elements of similar systems of taxation both in European countries, States or the European Union and most developed countries outside Europe. To draw accurate conclusions from the performance level comparisons of rates of labor income of individuals from different countries must be taken into account the specificities and characteristics of tax systems in those countries. In making such comparisons must take into account the fact that there is no official source, no national or international, to the matter of taxes, social contributions and taxes in the countries under analysis. The following is presented in the following taxation of labor income countries that are not members of the European Union: Albania. Bosnia - Herzegovina. Croatia. Switzerland. Iceland. Macedonia. Moldova. Norway. Ukraine. Kazakhstan. Japan. Canada. China. Australia. United States of America.taxes, social contributions, tax, tax system, tax system, income from employment, individuals, taxation of labor income, the tax rate, tax base, tax base, deductions; matter taxable taxpayers, tax progressive flat tax base.

Precision Improvement in Inertial Miniaturized Navigators Based on Fuzzy Logic Denoising of Sensors Signals

The chapter presents a new strategy to improve the precision of the inertial navigators processing in a fuzzy manner the signals provided by the miniaturized sensors equipping their inertial measurement units (IMU). To apply the developed technique, the hardware component of the inertial measurement units was specifically designed to include some redundant clusters of inertial sensors disposed in linear configurations on the measurement axes. The algorithm acts at the level of each detection cluster designed to measure an acceleration or angular speed along with an IMU axis by fusing the data obtained from the sensors in respective cluster. Based on the standard deviations of the sensors signals estimated for a data frame with a well-known size, the fuzzy logic mechanism provides a set of weights associated with each sensor in cluster, which are further used to fuse the data acquired from sensors at the current time. The algorithm has an adaptive character, the data frame used to estimate the standard deviations of the sensors signals being permanently updated with the new sensors measurements, and, in this way, the weights associated with each sensor are reestimated at each measurement step

A new non-linear vortex lattice method : applications to wing aerodynamic optimizations

This paper presents a new non-linear formulation of the classical Vortex Lattice Method (VLM) approach for calculating the aerodynamic properties of lifting surfaces. The method accounts for the effects of viscosity, and due to its low computational cost, it represents a very good tool to perform rapid and accurate wing design and optimization procedures. The mathematical model is constructed by using two-dimensional viscous analyses of the wing span-wise sections, according to strip theory, and then coupling the strip viscous forces with the forces generated by the vortex rings distributed on the wing camber surface, calculated with a fully three-dimensional vortex lifting law. The numerical results obtained with the proposed method are validated with experimental data and show good agreement in predicting both the lift and pitching moment, as well as in predicting the wing drag. The method is applied to modifying the wing of an Unmanned Aerial System to increase its aerodynamic efficiency and to calculate the drag reductions obtained by an upper surface morphing technique for an adaptable regional aircraft wing

Design and experimental testing of a control system for a morphing wing model actuated with miniature BLDC motors

Abstract The paper deals with the design and experimental validation of the actuation mechanism control system for a morphing wing model. The experimental morphable wing model manufactured in this project is a full-size scale wing tip for a real aircraft equipped with an aileron. The morphing actuation of the model is based on a mechanism with four similar in house designed and manufactured actuators, positioned inside the wing on two parallel lines. Each of the four actuators used a BrushLess Direct Current (BLDC) electric motor integrated with a mechanical part performing the conversion of the angular displacements into linear displacements. The following have been chosen as successive steps in the design of the actuator control system: (A) Mathematical and software modelling of the actuator; (B) Design of the control system architecture and tuning using Internal Model Control (IMC) methodology; (C) Numerical simulation of the controlled actuator and its testing on bench and wind tunnel. The morphing wing experimental model is tested both at the laboratory level, with no airflow, to evaluate the components integration and the whole system functioning, but also in the wind tunnel, in the presence of airflow, to evaluate its behavior and the aerodynamic gain

Optimization and design of an aircraft's morphing wing-tip demonstrator for drag reduction at low speeds, Part II - Experimental validation using Infra-Red transition measurement from Wind Tunnel tests

In the present paper, an ‘in-house’ genetic algorithm was numerically and experimentally validated. The genetic algorithm was applied to an optimization problem for improving the aerodynamic performances of an aircraft wing tip through upper surface morphing. The optimization was performed for 16 flight cases expressed in terms of various combinations of speeds, angles of attack and aileron deflections. The displacements resulted from the optimization were used during the wind tunnel tests of the wing tip demonstrator for the actuators control to change the upper surface shape of the wing. The results of the optimization of the flow behavior for the airfoil morphing upper-surface problem were validated with wind tunnel experimental transition results obtained with infra-red Thermography on the wing-tip demonstrator. The validation proved that the 2D numerical optimization using the ‘in-house’ genetic algorithm was an appropriate tool in improving various aspects of a wing’s aerodynamic performances

Voluminous hepatic hemangioma of the left lobe

Institutul de boli digestive si transplant hepatic Fundeni, Bucureşti, RomâniaHemangiomul este o formaţiune tumorală benignă cu localizarea cea mai frecventa la nivel hepatic [1]. Articolul prezentat se referă la cazul unei paciente în vârsta de 8 ani care este investigată în clinica de pediatrie pentru dureri abdominale localizate în etajul abdominal superior şi este decelata imagistic cu o formaţiune tumorală, voluminoasă, localizată la nivelul lobului stâng hepatic. Se intervine chirurgical; intraoperator se decelează formaţiune tumorală voluminoasă de lob stâng hepatic extinsă la lobul caudat pentru care se practică hepatectomie stânga reglata în bloc cu rezecţie de lob caudat. Particularitatea cazului constă în vârsta tânăra a pacientei precum şi dimensiunile crescute ale tumorii.Hemangioma is a benign tumor most frequently located in the liver. The article describes a case of an 8 year old girl, which was investigated in a pediatric clinic for upper abdominal pain and imagistic a voluminous tumor situated in the left lobe of the liver was detected. During the surgical intervention a voluminous tumor of the left hepatic lobe extended to the caudate lobe was detected. A left hepatectomy with resection of caudate lobe was performed. The particularity of the case consists in the young age of the patient and vast volume of the tumor