Samara University

Samara, Ethiopia

Samara University

Samara, Ethiopia
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-- There is an urgent need for efficient labour markets, for generating employment, poverty alleviation and wealth creation in different economies of the world, as generating employment and alleviation of poverty are among the most important priorities of any government in the world, said IIF Professor Aman Agarwal, while delivering the Plenary Keynote Speech as a Guest of Honour at State University of Aerospace Instrumentations, (SUAI), St. Petersburg,in the SUAI International Week on Knowledge Economy : Challenges and Opportunities today 22May, 2017. Professor Agarwal is currently Professor of Finance and Dean, Indian Institute of Finance and Executive Editor, Finance India.To create efficient labour markets, there is a need to setup a National Labour Exchange, urged Professor Agarwal. His speech was based upon "Theory of Employment, Wealth and Efficient labour Market through National Labour Exchange" developed at the Indian Institute of Finance by its four senior economists: Professor J.D.Agarwal, Professor Manju Agarwal, Professor Aman Agarwal and Professor Yamini Agarwal.Efficient labour market will help the nation, a firm and the labour in reducing poverty, easy access to information by removing information asymmetry, facilitate nearly perfect mobility of labour and reduce unemployment said Prof. Agarwal while addressing a large audience at State University of Aerospace Instrumentations, Russia.To create efficient labour market, digitization of labour records is requiredfeels Prof. Agarwal.Prof. Agarwal was critical of Keynsian'sGeneralTheory of Employment as it was a result of the great depression of 1931-36. Keynsian theory is irrelevant in today's context.Prof. Agarwal is of the opinion that Labour in itself is wealth of a nation and required to be utilized effectively but suffer from lack of employment opportunities, poverty, poor wage, income variations, immobility and many other problemsAccording to him the labour market today is far from perfect due to lack of necessary information. Prof. Agarwal stated that the payment to labour should be based upon on the basis of value addition rather than wages as currently done. The return to labourshould be directly linked to productivity. An efficient labour market can best be developed through setting up of National Labour Exchange. It would help save employment cost in the market driven economic system with asymmetric information and help solve the problems of laying off in the adverse economic conditions.Thein the international week was delivered by Prof. Dr. Yulia A. Antokhina, Rektor, State University of Aerospace Instrumentations,and Prof. Dr. Ovodenko Anatoly Arkadevich, President and UNESCO Head of Chair, State University of Aerospace Instrumentations,. Other key speakers were Dr. KseniiaBaimakova, State University of Aerospace Instrumentations,; Dr. Arthur Colin, Samara University,; Dr. Nadine Hackmann, Westphalian University of Applied Sciences,; Dr. Harm Hilvers, Christian University of Applied Sciencess, The, Dr. Peter Holicza, Obuda University,; Dr. Mikhail Krichevsky, State University of Aerospace Instrumentations,Dr. Pascal Ricordel, Universite Le Havre Normandie, France and Dr. Anna Sankina, State University of Aerospace Instrumentations,It is an honour for IIF that one of the authors of the theory and its professor is invited as a guest of honour and plenary key note speaker by SUAI, RUSSIA in International Week on Knowledge Economy; Challenges and Opportunities. Professor Agarwal would deliver a series of lectures on different subjects including Financial inclusion, digital economy etc. during the week.


Starinova O.,Samara University
AIP Conference Proceedings | Year: 2017

The developed method of iterative optimization of interplanetary missions with the low thrust, using sequence of movement specified mathematical models and design shape spacecraft, is realized. The new articular analytical decision describing planar movement of spacecraft with solar electric propulsion is described, allowing to construct initial approach in the iterative scheme of optimization. Developed a method of modelling and optimization of interplanetary missions ballistic schemes, based on a combination of Pontryagin's maximum principle formalism conditions of transversality and methods of the mathematical programming, allowing to consider restrictions characteristic for concrete interplanetary missions. Recommendations for choice design-ballistic parameters of the interplanetary missions spacecraft, received taking into account features nuclear and solar power plant for missions on delivery of a payload to orbits of Mars, expeditions the Earth-Mars-Earth are received. © 2017 Author(s).


Zabolotnov Yu.M.,Samara University
Procedia Engineering | Year: 2017

The dynamics of the process of forming the rotating orbital tether system, which is a bundle of two small satellites, is analyzed. The cases of transition deployed tether system in rotation by means of two electric jet engines located on the end bodies are considered. Engines together form a pair of forces required sign, the control program includes active and passive portions of the motion system. Satellites are material points whose masses are comparable in magnitude, and the tether is weightless. The control program is formed by a relatively simple model in the mobile orbital coordinate system in the case of inextensible tether. The elongation effect of the tether, which leads to its eventual sagging is analyzed by a more complete model in a fixed geocentric coordinate system. © 2017 The Authors. Published by Elsevier Ltd.


In the design process, when placing the on-board equipment of a spacecraft in the compartments of a minimum volume, along with the design and technological constraints the possible impact of the space environment must be taken into account. These are classified in the literature as a means of impact energy directed at the spacecraft transmission during its intended operation. As such, damaging factors most often considered are a means of mechanical action of meteoric and man-made particles. The energy released in the surface layer structure from the effects of other power transmission means or penetrating its material (different types of beam funds), as well as the energy of the electromagnetic pulse can disrupt the normal functioning of the onboard spacecraft equipment Protection of aircraft equipment by means of energy transfer napavlennoy determines the reliability of the spacecraft functioning and efficiency of the performance of the flight plan. In this paper the mathematical formulation and method of solving the problem of finding dense layouts spacecraft through proper allocation of the onboard equipment inside compartments for the effect on the spacecraft factors directed energy transfer. © 2017 The Authors.


The ballistic optimization of the L1-L2 and L2-L1 missions in the Earth-Moon system using electric propulsion is considered. The motion control is studied using the Fedorenko's successful linearization method to estimate the derivatives and the gradient method to optimize the control laws. The transfers are designed in frames of the restricted circular three-body problem. The mathematical model of the missions is described within the barycentric system of coordinates. The perturbation from the Earth, the Moon and the Sun are taking into account. The impact factor of the shaded areas, produced by the Earth and the Moon, is also accounted for. As for the results, the optimization of the optimal control laws and corresponding trajectories were obtained. © 2017 The Authors. Published by Elsevier Ltd.


Phylonin O.,Samara University
Procedia Engineering | Year: 2017

Methods, algorithms and means of few projections spectral and tomographic diagnostics of parameters of plasma flows, such as space distribution of local temperatures, concentration, etc. of small-size plasma ejectors (engines of orientation, low thrust) are described. © 2017 The Authors. Published by Elsevier Ltd.


The problem of electro rocket engine type and its main design parameters optimization for spacecraft located at low circular Earth orbit is studied. The efficiency of chemical (impulse) and electro rocket engine of low-thrust is analyzed. Introduced criteria of efficiency - payload mass maximization, introduced assumption that engine exhaust velocity is constant. In accordance with criteria and assumption, the analytical solution for spacecraft design parameters of spacecraft is obtained. Also, analytical solution for area of efficiency of electro rocket low-thrust engine is obtained. Calculation of spacecraft design parameters equipped with electro rocket low-thrust engine and area of its efficiency applying is carried out. © 2016 Published by Elsevier Ltd.


Myasnikov E.,Samara University
Lecture Notes in Computer Science (including subseries Lecture Notes in Artificial Intelligence and Lecture Notes in Bioinformatics) | Year: 2017

The paper proposes three novel nonlinear dimensionality reduction methods for hyperspectral image analysis. The first two methods are based on the principle of preserving pairwise spectral angle mapper (SAM) measures for pixels in a hyperspectral image. The first method is derived in Cartesian coordinates, and the second one in hypersherical coordinates. The third method is based on the approximation of SAM measures by Euclidean distances. For the proposed methods, the paper provides both the theoretical background and fast numerical optimization algorithms based on the stochastic gradient descent technique. The experimental study of the proposed methods is conducted using publicly available hyperspectral images. The study compares the proposed nonlinear dimensionality reduction methods with the principal component analysis (PCA) technique that belongs to linear dimensionality reduction methods. The experimental results show that the proposed approaches provide higher classification accuracy compared to the linear technique when the nearest neighbor classifier using SAM measure is used for classification. © Springer International Publishing AG 2017.


This paper outlines the nonlinear flight simulation of a low thrust spacecraft and a solar sail spacecraft. The main purpose of the work is ballistic comparison of solar sail spacecraft flight and low thrust spacecraft flight. The mathematical motion model for such types of spacecraft is formulated and described. The work considers the mathematical motion models within the heliocentric system of coordinates. Motion simulation process is the best way to assess the reasonableness of the mathematical model. On the basis of the formulated mathematical models, a special software for nonlinear flight simulation is developed. In particular, the flight of the low thrust spacecraft from Earth's orbit to the potentially hazardous asteroid is simulated. The findings of the work consist of heliocentric trajectories, time dependency graphs of flight parameters, the values of flight duration and the value of propellant consumption. © 2017 The Authors. Published by Elsevier Ltd.


Myasnikov E.,Samara University
Lecture Notes in Computer Science (including subseries Lecture Notes in Artificial Intelligence and Lecture Notes in Bioinformatics) | Year: 2016

In this paper we consider the possibility of using several multivariate interpolation methods as a supplement to existing dimensionality reduction techniques. Analyzed methods including nearest neighbor interpolation, inverse distance weighting, radial basis functions, and data mapping error minimization are evaluated using well-known datasets. Conducted experiments showed that radial basis functions and interpolation by the data mapping error minimization outperformed other considered methods in terms of the data mapping error yielding slightly worse quality then using stochastic gradient descent method for the whole data sets without interpolation. © Springer International Publishing AG 2016.

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