Methods of Accounting Aging of the Main Equipment of Nuclear Power Plants Using the Example of the Control System for the Installation of AM

Accounting for the aging of equipment and analysis of resource characteristics of nuclear technology facilities is an urgent problem. In this paper, we show methods of solving for finding functional reliability. The analysis of the functional reliability of the most important control and protection control (SCP) systems of the AM-1 installation was also carried ou

Verification of the second-order optimality conditions in the modeling of the sc expedition with the returning to the earth based on two Lambert's problems solving

The interplanetary spacecraft (SC) expedition from the Earth to Mars with a returning to the Earth optimization problem is considered. The attraction of the Sun only is taken into account. Two trajectories of interplanetary flights of this mission are approximated by Keplerian orbits and are obtained as solutions of Lambert's problems with the use of universal variable, Stumpff functions and Newton's method. The positions and the velocities of the Earth and Mars are calculated with the use of ephemerides DE424. The SC starts from the Earth for the period of 2020-2030 and stay at field near Mars at least for 30 days to carry out near-Mars scientific investigation. The total time of the expedition is limited to 1500 days. The characteristic velocity is minimized. The 64 local minima of this multiextremal problem are found numerically with the use of the gradient method and examined with the second-order optimality conditions with the use of Sylvesters criterion. Each Lambert's problem is given by two moments of time-moments of start and finish of the SC in this statement. So corresponding matrixes are 4 × 4. The subject of the article is actual in connection with the growing interest in the study of other planets of the Solar System and near-planetary spaces, and accordingly the planning of such missions. This study is the first part of the solving optimization problems in more complex statements- namely, a rough global optimization is performed to find potentially optimal time intervals for such missions with the verification of their optimality. The paper describes the method and gives certain results. © 2017 Univelt Inc. All rights reserved

Verification of the second-order optimality conditions in the modeling of the sc expedition with the returning to the earth based on two Lambert's problems solving

The interplanetary spacecraft (SC) expedition from the Earth to Mars with a returning to the Earth optimization problem is considered. The attraction of the Sun only is taken into account. Two trajectories of interplanetary flights of this mission are approximated by Keplerian orbits and are obtained as solutions of Lambert's problems with the use of universal variable, Stumpff functions and Newton's method. The positions and the velocities of the Earth and Mars are calculated with the use of ephemerides DE424. The SC starts from the Earth for the period of 2020-2030 and stay at field near Mars at least for 30 days to carry out near-Mars scientific investigation. The total time of the expedition is limited to 1500 days. The characteristic velocity is minimized. The 64 local minima of this multiextremal problem are found numerically with the use of the gradient method and examined with the second-order optimality conditions with the use of Sylvesters criterion. Each Lambert's problem is given by two moments of time-moments of start and finish of the SC in this statement. So corresponding matrixes are 4 × 4. The subject of the article is actual in connection with the growing interest in the study of other planets of the Solar System and near-planetary spaces, and accordingly the planning of such missions. This study is the first part of the solving optimization problems in more complex statements- namely, a rough global optimization is performed to find potentially optimal time intervals for such missions with the verification of their optimality. The paper describes the method and gives certain results. © 2017 Univelt Inc. All rights reserved

К вопросу о выстраивании профессиональной карьеры вузовского преподавателя в Российской Федерации

The problem of building a professional career of a University teacher in modern Russia is considered. The relevance of the study is determined by the fact that this problem is actively developed by supporters of the personal activity theory, which is currently the basis for planning the educational process in the substantive and methodological aspects. The basic concept of “education for career” is interpreted by the authors as a volume of knowledge, applied skills, cognitive activity scenarios, which is out-of-work in relation to the specialty and aimed at achieving high results in the profession (recognition by society, well-paid and socially significant positions) and obtaining positive emotions from their own work. In the study of support systems for career growth, the authors rely on the concept of the Russian professional education proposed by A. M. Novikov. Four main principles are taken into account: the humanization of education, its democratization and the emphasis on continuity and advance. The novelty of the research and its theoretical and practical significance lies in the allocation of three conditions for the career growth of a teacher of the University: the integration of pedagogical work into the system of life meanings and value hierarchy of the individual as their most important component; constant creative search, determined by the critical attitude to own professional level; readiness of a teacher to implement the activities of an innovative nature.Рассматривается проблема выстраивания профессиональной карьеры преподавателя вуза в современной России. Актуальность исследования обусловлена тем, что данная проблематика активно разрабатывается сторонниками личностно-деятельностной теории, которая в настоящее время является основой проектирования учебно-воспитательного процесса в содержательном и методологическом аспектах. Базовое понятие «образование для карьеры» истолковывается авторами как внеситуативный по отношению к полученной специальности объем знаний, прикладных умений, сценариев когнитивной деятельности, нацеленных на достижение высоких результатов в профессии (признания социумом, хорошо оплачиваемых и социально значимых должностей) и получение положительных эмоций от собственного труда. При изучении системы поддержки карьерного роста авторы опираются на концепцию российского профессионального образования, предложенную А. М. Новиковым. Учитываются четыре главных принципа: придание образованию гуманистического характера, его демократизация, а также акцент на непрерывности и опережении. Новизна исследования и его теоретико-практическая значимость заключаются в выделении трех условий карьерного роста преподавателя вуза: интеграции педагогического труда в систему жизненных смыслов и ценностную иерархию личности в качестве их важнейшего компонента; постоянного творческого поиска, обусловленного критическим отношением к своему профессиональному уровню; готовности педагога к осуществлению деятельности инновационного характера

Genetic algorithms for nuclear reactor fuel load and reload optimization problems

Approaches are examined in the present paper to the application of genetic algorithms for optimization of initial reactor load and subsequent reloading and reshuffling of fuel assemblies in the nuclear reactor core. The issues associated with selection of the optimization criterion, which was chosen to be the nuclear fuel burnup depth, are discussed. The burnup depth is estimated after the fuel assembly is unloaded from the core, i.e. after residence in the reactor core during 3 fuel irradiation campaigns. An important aspect determining the efficiency of the use of the genetic algorithm in the problem under examination is that the neutronics calculation of the reactor core is to be performed in sufficient details allowing "feeling" the change in the location of the fuel assemblies relative to each other. The use of low-precision instrument results in the uselessness of the proposed approach to the optimization of reactor core loading. The opposite extreme, i.e. the excessive degree of details, is associated with significant increase of expended computer CPU time. In the presented paper, the TRIGEX [1,2] application software package was used in the analysis of neutronics characteristics of the reactor core providing acceptable degree of details and capable to demonstrate sensitivity of the results to the changes in the reactor load arrangement. The genetic algorithm incorporates the use of at least two basic procedures—selection and mutation. One of the most important issues in the application of the genetic algorithm is the definition of the basic concepts, namely the concepts of mutation, crossing, and specimen. The answers to these questions as applicable to the problem under discussion are provided in the present paper. In addition, the main recommendations for the organization of crossing and mutation procedures are also given. The efficiency of use of the developed model of the genetic algorithm is demonstrated by the test example of a BN type reactor. The results of the test run demonstrated that the use of the proposed approach allows searching for optimal reactor load mapping for each separate core reshuffling operation. The main objective of the performed study was to demonstrate the applicability and efficiency of the new up-to-date approach to solving the problem of fuel loading into a nuclear reactor

К вопросу о выстраивании профессиональной карьеры вузовского преподавателя в Российской Федерации

The problem of building a professional career of a University teacher in modern Russia is considered. The relevance of the study is determined by the fact that this problem is actively developed by supporters of the personal activity theory, which is currently the basis for planning the educational process in the substantive and methodological aspects. The basic concept of “education for career” is interpreted by the authors as a volume of knowledge, applied skills, cognitive activity scenarios, which is out-of-work in relation to the specialty and aimed at achieving high results in the profession (recognition by society, well-paid and socially significant positions) and obtaining positive emotions from their own work. In the study of support systems for career growth, the authors rely on the concept of the Russian professional education proposed by A. M. Novikov. Four main principles are taken into account: the humanization of education, its democratization and the emphasis on continuity and advance. The novelty of the research and its theoretical and practical significance lies in the allocation of three conditions for the career growth of a teacher of the University: the integration of pedagogical work into the system of life meanings and value hierarchy of the individual as their most important component; constant creative search, determined by the critical attitude to own professional level; readiness of a teacher to implement the activities of an innovative nature.Рассматривается проблема выстраивания профессиональной карьеры преподавателя вуза в современной России. Актуальность исследования обусловлена тем, что данная проблематика активно разрабатывается сторонниками личностно-деятельностной теории, которая в настоящее время является основой проектирования учебно-воспитательного процесса в содержательном и методологическом аспектах. Базовое понятие «образование для карьеры» истолковывается авторами как внеситуативный по отношению к полученной специальности объем знаний, прикладных умений, сценариев когнитивной деятельности, нацеленных на достижение высоких результатов в профессии (признания социумом, хорошо оплачиваемых и социально значимых должностей) и получение положительных эмоций от собственного труда. При изучении системы поддержки карьерного роста авторы опираются на концепцию российского профессионального образования, предложенную А. М. Новиковым. Учитываются четыре главных принципа: придание образованию гуманистического характера, его демократизация, а также акцент на непрерывности и опережении. Новизна исследования и его теоретико-практическая значимость заключаются в выделении трех условий карьерного роста преподавателя вуза: интеграции педагогического труда в систему жизненных смыслов и ценностную иерархию личности в качестве их важнейшего компонента; постоянного творческого поиска, обусловленного критическим отношением к своему профессиональному уровню; готовности педагога к осуществлению деятельности инновационного характера

О возможности гравитационного захвата небесных тел в Солнечной системе

In this paper, we study the possibility of capturing the cosmic mass (asteroid or comet) by the Sun, if this mass falls within the scope of Jupiter.The task of determining possible zones of material accumulation bodies is extremely important for the safety of space flights. The perturbed Kepler problem is considered in the following statement. Let the cosmic mass fall into the Solar system at a parabolic speed relative to the sSun. Using computer modeling, the possibility of the transition of cosmic mass to periodic orbits due to the gravitational influence of Jupiter was studied. As a result of numerical simulations, areas of possible particle accumulation were found. The proposed method for studying the capture phenomenon can be applied to various objects in the model of the limited three-body problem.В настоящей работе изучается вопрос о возможности захвата космической массы (астероида или кометы) Солнцем, если эта масса попадает в сферу действия Юпитера. Задача определения возможных зон накопления материальных тел чрезвычайно важна для безопасности космических полётов. Рассматривается возмущенная задача Кеплера в следующей постановке. Пусть космическая масса попадает в Солнечную систему с параболической относительно Солнца скоростью. Посредством компьютерного моделирования изучается возможность перехода космической массы на периодические орбиты вследствие гравитационного влияния Юпитера. В результате многочисленных экспериментов найдены области возможного скопления частиц. Предлагаемый способ исследования явления захвата может быть применен к различным объектам в рамках ограниченной задачи трех тел

Optimal interplanetary spacecraft flights design with many-revolution braking maneuver by a low thrust jet engine

The optimal control problem of the spacecraft (SC) interplanetary transfer from the Earth to Mars is considered. The orbits of the Earth and Mars are necessary to be circular and noncoplanar. The SC starts from the artificial Earth satellite circular orbit (AESCO) and finishes at the artificial Mars satellite circular orbit (AMSCO). The SC position on an initial AESCO at the starting point and position on an AMSCO at the finish are optimized. Acceleration of the SC near the Earth and braking near Mars, that are carried out by jet engines of big thrust, are approximated by pulse excitations. On the rest of the trajectory the control of the SC is realized by a low thrust jet engine vector. In connection with the taking into account the loss of accuracy effect, the inertial heliocentric and the noninertial rotating marsand geocentric reference frames are used at the solution creation. Total flight time is minimized. The considered problem is formalized as a variable structure dynamic system optimal control problem. On the basis of the Pontryagins maximum principle its solving is reduced to the 42nd order boundary value problem solving. The boundary value problem is solved numerically by a shooting method with selection of 13 parameters. The vector function root is found with the use of Newton's method with Isaev-Sonin's modification and Fedorenko's normalization in the convergence conditions. The Cauchy problems of shooting method are solved numerically by the explicit 8th order Runge-Kutta's method based on Dormand-Prince's 8(7) calculating formula with the automatic step choice. Main result: The original problem has been solved. Pontryagin's extremals are defined out as a boundary value problem solution result. The analysis depending on problem parameters is carried out. Various AMSCO were considered during calculating. Particularly we succeed constructed Pontryagin's extremals in problems of transition to AMSCO which are close approximates Phobos and Deimos orbits without pulse influences at the finish moment. The SC performs a sixty-six and a nineteen many-revolution brakings near Mars respectively at these constructed trajectories on the final part of flight. The parameters continuation of the planar case of problem solution is used to construct trajectories in the major case. Using of high and low thrust propulsion in combination for space missions allows increase the useful weight and makes the project cheaper, that is actual now. Expeditions to Mars and its natural satellites can help to provide solution of a wide range of scientific physics problems of the Solar system. © 2017 Univelt Inc. All rights reserved

Method of optimal trajectories design for a spacecraft with a jet engine of a large limited thrust in problems with the phasing condition

The optimization of the spacecraft (SC) interplanetary space flight trajectory is considered. Rigid conditions of phasing are supposed on one of the trajectory bound point. The SC docks to/undocks from the existing station or lands on/flies up from the natural satellite of the planet. On another end hit the point type rendezvous condition is considered. The SC and the station/the planet natural satellite are relied to be non-Attracting material points. The control of the SC is realized by a large limited jet engine thrust. The start, the finish, the moments of inclusion and switching off of the SC jet engine thrust are optimized. Weight losses are minimized. The problem is formalized as an optimal control problem and decides on the basis of the Pontryagin's maximum principle. The boundary value problem is solved numerically with the use of shooting method, Newton's method and the parameters continuation method. Transversality conditions of a maximum principle are effective for the time optimization on the trajectory end with hit the point condition. And for time optimization on the bound point with a phasing condition -The external optimization with the use of a combination of gradient methods and a method of continuation of the decision on parameter is made. One of the main difficulties in solving of such problems is constructing good initial parameter values approximation. As example, technique of creation extremals in the problem is showed on the SC returning with samples of soil from the Mars satellite Phobos to the Earth optimization, with taking into account ephemerides. The original problem is multiextremal, a launch window to the Earth from Mars opens each two years. Besides, for each round of Phobos around Mars exists a local optimum trajectory. Therefore, in the beginning of solution global optimization is made: The SC flight is approximated with series of close Lambert's problems. Then the problem is solved in pulse statement on the basis of the Lagrange principle with consideration of the Sun, and Mars attraction on each part of the trajectory. © 2017 Univelt Inc. All rights reserved

Method of optimal trajectories design for a spacecraft with a jet engine of a large limited thrust in problems with the phasing condition

The optimization of the spacecraft (SC) interplanetary space flight trajectory is considered. Rigid conditions of phasing are supposed on one of the trajectory bound point. The SC docks to/undocks from the existing station or lands on/flies up from the natural satellite of the planet. On another end hit the point type rendezvous condition is considered. The SC and the station/the planet natural satellite are relied to be non-Attracting material points. The control of the SC is realized by a large limited jet engine thrust. The start, the finish, the moments of inclusion and switching off of the SC jet engine thrust are optimized. Weight losses are minimized. The problem is formalized as an optimal control problem and decides on the basis of the Pontryagin's maximum principle. The boundary value problem is solved numerically with the use of shooting method, Newton's method and the parameters continuation method. Transversality conditions of a maximum principle are effective for the time optimization on the trajectory end with hit the point condition. And for time optimization on the bound point with a phasing condition -The external optimization with the use of a combination of gradient methods and a method of continuation of the decision on parameter is made. One of the main difficulties in solving of such problems is constructing good initial parameter values approximation. As example, technique of creation extremals in the problem is showed on the SC returning with samples of soil from the Mars satellite Phobos to the Earth optimization, with taking into account ephemerides. The original problem is multiextremal, a launch window to the Earth from Mars opens each two years. Besides, for each round of Phobos around Mars exists a local optimum trajectory. Therefore, in the beginning of solution global optimization is made: The SC flight is approximated with series of close Lambert's problems. Then the problem is solved in pulse statement on the basis of the Lagrange principle with consideration of the Sun, and Mars attraction on each part of the trajectory. © 2017 Univelt Inc. All rights reserved