2011. № 49

A system of updating of the database for the Internet textbooks on the decision theory is developed and a program created for operational changes and additions to the constantly evolving project of developing a series of textbooks. Test update focuses on results published in [1,2]. The inter-coalition upper level suggests making decision according to one of the following optimality principles: the guaranteed result, the Nash optimality and the Pareto optimality. The multicriteria problem for the lower two-level system is decomposed into the modified problems for the players. The modified convergence of the iteration process is substantiated. PACS: 02.30.Yy

Keywords: сoalition; hierarchy; strategy; decomposition; database; operational update program

The solution of many-electron problem to atoms and molecules physics are realized by density-matrix method. Effective Hamiltonian is introduced. Spectrum of this operator for any pair electrons may be expressed as a set of the own energy value and a set of own wavefunction. Many-configuration approach, which describes the wavefunction of all electrons system by many-determinant sum, details density-matrix and permits to definite their properties. New formulating of electrons problem makes to reduce calculations difficulties.

Keywords: density-matrix method, redused -density-matrix, many-configuration approach, electrons problem, spectrum decomposition density-matrix.

The linearized equations for regular precessions are represented here. The study of motions of this type is very important in rigid body dynamics. The classification of the corresponded linear equations was carried on and the statements on the reaction of a stability with respect to parameter variations was formulated.

Keywords: variation equations, regular precessions, structure stability

The article is devoted to designing the mathematical model,design procedure and calculation of protective characteristics of a high-altitude compensating jacket (ВКЖ), to protect the pilot from influence of the lowered barometric pressure during high-altitude flight. The methods allow to choose jacket design data at a stage of its designing, reducing thereby number of expensive tests.

Keywords: high-altitude compensating jacket, booster compensation, power compensation, sealed camera, power shell, tension device, a soft shell of revolution, balance equation, finite difference method

Solvedthe problem of computingdynamic prioritiesto the input ofa passenger planeat a givenairortrainsystem.At the same timetake into account thepossibility of raisingthis priority,with a limitedstock offuel.

Keywords: safety control, optimal control, flying objects, dynamic programming, function of risk

Describes the construction of the software module approximate investigation of the dynamics of deployment parachute canopy. Discovery process is modeled by the motion of perfectly flexible elastic thread - frame strip, passing in a sling. The equations of motion that Coy-string are replaced by discrete counterparts. At the initial stage of expansion, when the canopy has not yet fulfilled part, applies to "force boost" - the dome probetsya constant pressure differential acting up until the pole is formed executed region. After this drop in the backlog of the dome is assumed to be zero, and the completed parts - a constant in the dome with the addition of the calculated dynamic component. The proposed software module allows the calculation of the basic relations describing the process of opening the dome, determine the values of congestion in the thimble, the pole and on the edges of the dome. The possibility of modification of the module for solving the dynamics of opening the parachute with a dome or cupola rifovannym arbitrary shape.

Keywords: deployment of the canopy, flexible string, ribbon frame, differential pressure, generalized schroud line; psevdoviscosity mechanism, a software module.

Soft the problem of calculating dynamic priority input passenger flight in a given air echelon. In this into account may improve this priority with a limited stock of fuel.

Keywords: safety control, optimal control, aircraft, dynamic programming, function of risk

Consider the motion in the vertical plane Nonrigid Parachute and Playload System. In writing the equations of motion parachute connector and the load are modeled by rigid bodies connected by joints of an ideal. Compiled a simplified nonlinear equations of the perturbed motion of the system that take into account the nonlinear dependence of a normal component of aerodynamic force from the parachute canopy angle attack. The method describing function are expressions for the main parameters of the vibrational modes arising from the movement system.

Keywords: parachute system, nonrigid playload; normal mean aerodynamic force sub-unit; describing function technique; dynamic stability; self-oscillation.

The article deals with the management goal defeat at the expense of purposeful change the relative position of means of destruction, and goals. A mathematical description of the dynamics of the vector of the relative position of aircraft ordnance (TSA) and goals in the attack as a system with random change in the structure. We formulate the problem of aiming and tracking of managed ASP and determined their place in the task of destroying the target. The question of quality review process and formed a common sight, and private aviation quality sighting system

Keywords: defeat, aiming, guidance, control, random structure, guality, weaponizatio

Consider the problem of automatic traffic control system of manned and unmanned aircraft. Discussed the design principles and structure of systems management systems. Proposed a method for organizing virtual host systems. The examples of control systems by the relative position of objects and prevent dangerous approaches

Keywords: operation, team, aircraft, leading, led, management, system

This article deals with actual issue of flight test programming of an unmanned aerial vehicle during its try-out sessions. Also, the article gives insight into evaluation method of flight test completeness. This method could be a pretext for justifyng a nessecity of a new flight test. The method is based on a recovery of a polinomial model from a statistical sample of a telemetry data. The following model will be evaluated by statistical criteria. The main specialty of statistical criteria is in knowing criteria's values for particular cases, when virtually every consistent pattern could be described by the polynomial model. Which means that these criteria could be a measure of completeness for the experimental model as well as a pretext for continuation of a test flight.

Keywords: statistical synthesis; flight-test aircraft; aerodynamic coefficients; statistical criteria; optimization; polynomial model; statistical sampling.

In this paper the multi-channel queuing system simple group povogo flow requirements with exponentially distributed service time with the group and queue of unlimited length. The investigated system has a distinctive feature: the requirements to receive services and are managed in groups, after all the requirements of service at the same time leave the system. For the cha-stnogo case - two-channel system queuing singles and doubles Zaya wok - are labeled graph states and the system of differential equations. We consider the steady-state behavior of the system. Describes the proce-fool to obtain the system of equilibrium equations in terms of generating functions, finding solutions-assertion is to be carried out numerically. The results obtained can be used Gut-for probabilistic analysis of avionics systems.

Keywords: queuing system, indivisible group application, a simple flow group, group care, the state graph, the system of equilibrium equations, the generating function.

The article provides the basic concepts, definitions and provisions of unification and replication of technical systems. The methods for assessing the impact of unification on economic feasibility for systems equipment. Presented alogoritm, models, justification criterion for types of technical systems.

Keywords: system equipment; standardization; economic feasibility indicators; optimality criterion; classification.

The paper analyzes the methods of structural and parametric synthesis of shape unmanned aerial vehicle (UAV). Presents a block diagram of decomposition of the research object of the task and quality criteria for the design decisions. Consider the matrix signs appearance UAV technology solutions to them and their design parameters. Structural logic of forming a rational aspect of the aircraft is given. Formulated the problem – solving methods are given of structural synthesis and optimization of design parameters.

Keywords: aircraft, the signs appearance, structural synthesis, parametric optimization, the quality criteria.

Studied sufficient conditions for stability of nonlinear dynamical systems with optimal management of production. Proposed to use the Lyapunov method and applied in calculations of the Bellman function.

Keywords: critical situation ,variable efficiency, optimal control , dynamic stability

Structure and restructuring algorithms of unmanned aerial vehicle integrated landing system is presented. Main modes, including approach and landing are considered. A switch-over from full-size filter to a decomposed form for approach mode is shown.

Keywords: inertial navigation system; global navigation system; MEMS; pseudolite; optimal information processing; unmanned aerial vehicle.

Production expert system with fuzzy rules for brain bioelectrical activity research by ultrasound doppler and electroencephalography methods was developed. Possibilities, features and benefits of using developed expert system with fuzzy rules for brain bioelectrical activity research at flight and control staff presented.

Keywords: medical system; production expert system; fuzzy logic; electroencephalograph; ultrasound doppler system; integrating of information; brain bioelectrical activity; flight and control staff

The article shows the influence of geometrical parameters of the outer surface of the design of aviation technology to its consumer qualities. All of these require the development of effective geometrical model of the outer surface. The use of parametric models provides the real basis for multi-objective optimization of the surface and shape of the aircraft. It is shown that the technology of complete electronic product definition provides a consistent movement from the external outlines to the design and systems products. External outlines in this case are the restrictions with different levels of priority if necessary rework the outer surface of the product in the study of technological products.

Keywords: geometric modeling, computer graphics, aviation technology, external outlines, optimization of surface and shape, parametric models, electronic model.

A mathematical model is given for computation of radiation heat exchange in the working part of the test bench, in which the halogen incandescent lamps are used for heating the test object. Variants of computation in spectral and integral statementare considered. The contribution to the total radiation flux from its constituents in the form of luminous-element radiation and the inherent radiation of the halogen incandescent-lamp shell is taken into consideration. Their influence on its temperature state is estimated.

Keywords: heat exchange, radiation, flux, spectrum, tests, material, construction, method, temperature.

A mathematical model for computation of radiation heat exchange in the working part of the test bench with gas-discharge radiation sources is given, which makes it possible to determine the radiation fluxes on the surfaces forming the inner circuit of the working part.

Keywords: heat exchange, radiation, model, computation, material, construction, spectrum, tests, experiment.

An analytical approach and proposed mathematical models to assess the effectiveness of promising areas of modernization of unmanned aerial vehicles (UAVs), based on common concepts of efficiency, such as quality, technical excellence. An example of an assessment of the efficiency of the replacement of metal materials in the design of UAV in composite materials, confirming that proposed models.

Keywords: unmanned aerial vehicles; modernization; efficiency; technical perfection; quality; the technical level, composite materials.

In the paper there are the results of Power Analysis of the Unmanned Aerial Vehicle (UAV) with Lifted System of Shrouded Rotor on the hover mode and horizontal flight. There was the estimation of the Power Characteristics of UAV of this type depending on the parameters of its aerodynamic layout.

Keywords: unmanned aerial vehicle, shrouded rotor, aerodynamic design.

The paper contains the Method of Lift Calculation of the Unmanned Aerial Vehicle (UAV) with Lifted System of Shrouded Rotor in the condition of Ground Effect. There was the investigation of the correlation of the elements of the total thrust (ring, rotor, bottom part) for the various ground clearance.

Keywords: unmanned aerial vehicle, shrouded rotor, ground effect, aerodynamic characteristics.

The principles, methods and algorithms of formation a composites of a dynamic system that models target mission of UAV with a given accuracy are discussed. Evaluation of accuracy of this model is based on gualitative criteria which include in addition to accuracy of the model, and the cost of implementation at all stages of the mission. The sources of diversity of models: describing forms of UAVs dynamics, external disturbances are considered.

Keywords: unmanned aircraft vehicle (UAV), simulation, mathematical models, target mission, simulation gualitative criteria.

We consider the elastic small-sized aircraft, rotating around its axis with a velocity of 3-5 M, is taken into account the intensive longitudinal loading and, consequently, the longitudinal acceleration of the aircraft. This takes into account the effect on the dynamic behavior of a model aircraft electromechanical rudder drive. A mathematical model simulating the operation of the major elements of the steering gear was developed. Dynamic equations of the spatial motion of an elastic aircraft modified in view of the developed mathematical model of rudder drive.

Keywords: mathematical modelling; fluctuations; a steering drive; flight control

The problem of formation of the stabilization loop of the maneuver unmanned aircraft for classes "air - to - surface” and "air - to - air" with the account of requirements of the aeroelastic stability with the automatic control system (ACS) is considered; the models and methods that are designed to solve this problem are given; the example of solving the problem, as well as the recommendations to provide the aeroelastic stability of the maneuver unmanned aircraft with ACS are considered.

Keywords: unmanned aircraft, construction, automatic control system, stabilization loop, aeroelastic stability

The paper shows the basic methods and means of creation of the prototypes of the projected parts of the objects of aerospace technigue at the stages of planning of constaction. Rapid prototyping technology allows to check the correctness of the created construction, to optimize it, what can provide the reguiredguality of products at the early stages of the life cycle. It is showed in the paper the possible field of application of rapid prototyping technology at the stages of planning.

Keywords: rapidprototyping and production, product guality, technological preproduction

Keywords: control systems; gas turbine engine models; gas turbine acceleration; simulation of unsteady conditions; unsteady flow; gas turbine CFD; OpenFOAM

In this paper we describe a method of quantifying the environmental safety of aerospace objects. The methodology is the calculation of individual assessments of environmental danger of the object, obtaining values of the overall environmental risk assessment and the transition to environmental safety. A sequence of calculations are given an algorithm for obtaining private evaluations and assess the overall environmental hazard of the object.

Keywords: аerospace objects, environment, pollution, environment, quantitative assessment of the algorithm

Theoretical justification of climatic chambers parameter choice for thermal tests for miniature onboard equipment (MOE) operating in spacecraft nonpressurized modules is discussed. It allows us to change the numerous expensive thermal tests for MOE in heat vacuum chamber by much more cheaper thermal tests in climatic chamber at the phase of acceptance tests.

Keywords: thermal tests, miniature onboard equipment, nonpressurized module, climatic chamber

In the article the substantiation of the tendency of the space vehicles’ mass-size characteristics improvement under modern conditions of intensive space market development and is given. Actuality of the implementation of small-scale space vehicles in the sphere of navigation, satellite communication, monitoring and Earth remote sensing is described by comparison to the space vehicles of the same functionality but considerably exceeding them in mass-size characteristics.

Keywords: small-scale space vehicles; micro space vehicles; nano space vehicles; expendable launch systems; mass-size characteristics of the space vehicles

In the article innovative approaches to small-scale space vehicles development on an example of the Earth remote sensing satellite "MONITOR-E", created on the basis of the unified space platform (UKP) "Yakhta" are described. Correctness of the put in pawn and chosen principles and the constructive-technological decisions in working out of the considered objects is confirmed. Characteristics of the "MONITOR-E" and UKP "Yakhta" are given. The application of small-scale space vehicles in space activity is described.

Keywords: small-scale space vehicles; unified space platform; Earth remote sensing satellite

In this article are issued basis principals of a method development of the automated scheduling of the automated spacecrafts mission. There are three types of plan, two of which are the initial data for drawing up of the primary type of plan - a plan that is used to control the flight of the unmanned spacecraft. There is considered the structure of the plan and its components. A procedure of drawing up of the plan that based on the cause-and-effect relationship is disclosed. The algorithm of schedule development in automated mode is formulated.

Keywords: spacecraft, mission schedule, control commands, target fragments, cause-and-effect relations, relations tables

This article discusses four key operations defining the purpose of automatic near-earth spacecraft control procedure: determination of targeting devices operation program, planning of space-time actions, planning of spacecraft devices and systems functioning and spacecraft flight plan realization. It is shown that every of these operations are executed for almost all of automatic spacecrafts functioning on near-earth orbits. The first three of them are informative and define the structure of spacecraft control system. The system which solve the problems of these key operations will be called Information system of automatic spacecrafts flight control support.

Keywords: flight control system, spacecraft as vehicle, spacecraft key operations, plan of targeting device functioning, plan of space-stime actions, spacecraft flight plan

In the article the processes of development of the space system engineering and possible forms and stages of that processes are considered. The types of influence of the space system engineering are marked on other industries.

Keywords: space system engineering; scientific and technical progress; pilot-controlled space vehicle; development.

The article investigates the effectiveness of a new type of heat-accumulating devices, known as frameless, in which, unlike in traditional ones, the working body does not require the sealing of its volume during phase transitions from solid to liquid and back.

Keywords: heat storage (HS), form-stable phase-transition material (PTM), melting filler.

The system approach of synthesis of optimum interplanetary trajectories on the basis of modern space technologies for a wide range of the distant space missions planned for immediate prospects is offered. High power possibilities of received interplanetary trajectories and rather low cost of space missions are reached at the expense of use of repeated gravitational maneuvers at planets and application of electrojet engines. For the decision of a challenge of optimum control of compound dynamic system with functional restrictions the original technique is offered.

Keywords: an interplanetary trajectory, distant space mission, gravitational maneuvers, electrojet engines, optimization, management, compound dynamic system, functionals, restrictions

In the article are considered some questions of dynamics of operated flight of rockets on a passive site of a trajectory namely – the problem by definition of an angle of attack, an angle of slope of a vector of speed, pitch angle. The solution of this problem under certain conditions below, apparently, is not a fundamental difficulties. Nevertheless, in the published works, as far as it is known to authors, it isn’t present the decision. Thus authors recognize that in the course of designing and development of control systems of aircraft of certain type the knowledge of dependences of noted angels from time is not only useful, but in some cases simply necessary. Therefore, the considered problem according to authors is actual and attractive.

Keywords: equations of motion, passive part, vertical plane, the static stability, the analytical solutions, the angle of attack, pitch angle.

The mathematical model of the three-dimensional motion of the combined system of a soft landing (CSSL) reentry of spacecraft (SC), consisting of spacecraft, a parachute system (PS) and the braking propulsion system (BPS). In writing the equations of motion CSSL considered it a simplified physical model in the form of two solids (PS and SC dome with BPS), connected by weightless slings and suspension system. The rate of air expressed as a sum of three components of wind, standing, and turbulent wind. In determining the projections of the principal vector and principal moment of the thrust forces BPS is that brake motors are located on a ring centered on the axis of symmetry of the spacecraft, and they create traction parallel and directed in one direction. The proposed mathematical model can be used for both numerical and analytical study of the dynamics CSSL.

Keywords: parachute system; spacecraft; retropropulsion; a gust of wind; a random variable; the Rayleigh law; the mass flow of fuel.