Vol 11, No 5-2 (2012): Special Issue

The problem of constructing asymptotically stability arbitrarily given flat program motions of the helicopter with tethered payload is solved. Program control and stabilizing control is done in the form of an exact analytical solution in the class of continuous functions. The problem is solved by direct method of Lyapunov stability theory with Lyapunov’s functions with constant sign of the derivatives.

The problem of a longitudinal flow of a flat plate by the airflow is proposed. On the plate surface is located liquid film, course of which occurs due to gravity and the oncoming flow. Shear stress at the interface is calculated. According The results of solving the problem, reduction the friction stress is obtained.

Basics of calculation of magnetic fluid dampers aimed to improve operational characteristics of damping elements of aircraft’s chassis are considered.

Calculation procedure of maximum allowable by the fatigue life value of the stress concentration factor (SCF) in reinforced airframe panels containing notches is presented. The problem of reducing the SCF in the passenger airplane wing panel with notches and holes is discussed. The problem is solved by means of interactive simulation and search for the reasonable design alternate basing on the 3D finite element model of the panel.

In the three-dimensional formulation is presented the solution of the problem of determining the elastic stressstrain state of solid clamped rod of arbitrary cross section loaded by concentrated torque at the free end.

Presents the results of the analysis of various ways to eliminate the effect of skewing the geometrical axes element valve system at its output characteristics. In is based on the accounting of engineering-technological and operational factors, with the necessary sealing ability and resource.

This paper presents research on the effect of the error of the mechanical properties of the material on the formation of the initial workpiece shape accuracy of the working surfaces of parts. Also considered are changes in the form of error in the subsequent stages of production.

The mathematical model is submitted for definition of rational conditions of processing at the end-milling, consisting of linear objective function and linear restrictions – inequalities. As objective function the equation determining machine time of processing is used, and as restrictions – inequalities, the restrictions connected in functional parameters and parameters, determining quality of processing.

At present, for the manufacture of complex structural elements of aircraft in a small-scale production with high accuracy requirements are effective ways of shaping parts explosive processes.

This paper deals with out-of-flatness detection in case of control on CMM. As samples the flat surfaces after grinding, electrical discharge machining and milling are considered. The research of different machining on our-offlatness detecting results is done.

This article is about local thermoplastic hardening of large parts GTE.

The main characteristics of modern loading systems for fatigue tests of full-scale aircraft, determining the error of programs loading, were shown. The simulation of the loading system of the stand at tests was conducted. The possibility of selecting the geometric parameters of load the system to compensate for errors introduced by various factors when playing loads spectrum loading was found. Such a simulation and an informed approach to the selection of setting angles loading devices were used on a stand of fatigue certification test SuperJet-100 in establishing a system of loading of the wing.

Methods of combining surface-plasto deformation pieces from titanium alIoy ВТ9. Research of quality of surface layer is fulfilled. Functional dependence is determined between hardiness limit, fine crystalline structure parameters and intensity of exoelectronic emission.

It is shown that for fracture resistance criteria implementation while securing reliability of aircrafts structural components during design stage can be used.

Results theoretical and experimental researches of influence of power{force} factors on frequency characteristics of the rotor rotating with the big speed are resulted. Importance of the account of this influence is shown at the decision of dynamic problems{tasks}.

In this paper, the technique of creating a "virtual engine". The first step is the calculation of the indicator diagram is used. How to create three-dimensional model and its analysis is performed shall be considered a finiteelement model of the gas-dynamic processes in the cylinder combustion engine based, kinematic, dynamic and strength calculations, as well as specialized calculations.

New method for the determination of blades oscillation parameters is proposed. The approach is based on the analysis of primary transducers signals distortions using nonlinear approximation techniques. Blades oscillations lead to distortions of primary transducer output signal, non-linear approximation techniques allow to determine blade oscillation parameters. The system for the determination of blades oscillation parameters with front-end processing module and succeeding processing on PC is described.

This article examines the solutions of some problems of using computer technologies in designing of combustion chambers GTE.

The article describes the method of determining the actual natural frequencies of the pipeline in the environment ANSYS, evaluated its frequency detuning.

The paper presents the test results and mathematical modeling data of air pressure probes and gives justification of using mathematical modeling in further design of similar air pressure probes, as well as provides estimate of applicability of OpenFOAM program for modeling air pressure probe. The paper also gives impact of air stream wash on measurement error of air pressure.

With aim to eliminate the drawbacks of certain methods of structure formation of high strength materials it is suggested to obtain nanocrystal structure at the expense of increasing strain ratio by application of more up-to-date equipment.

Purpose of this work was to study the influence of temperature on the quality and corrosion resistance of zinc coatings on silicon-containing steels. For the studies we used samples of steel St3sp and 09G2S.The research results allowed to determine the optimum temperature dip zinc coating and to obtain high-quality zinc coatings on siliconcontaining steels.

The article addresses the problem of influence unequal curing caused by the temperature gradient in the thickness of the material anisotropy on the strength properties of PCM. The authors studied the influence of the catalysts for curing epoxy binder EDT-69N to be used for the manufacture of multilayer polymer composite materials (PCM). According to the dielectric spectroscopy proved ac-celerating effect of selected compounds on the curing process of epoxy binder EDT-69N with the forming of fiberglass. The authors show the possibility of regulating the process of curing with the aid of catalysts to reduce the influence of temperature gradient on the anisotropy of strength properties of the matrix in the manufacture of PCM.

This article reports the experience in conducting strength tests of folded cores reinforced composite materials. In order to increase the stability of the experimental results are given tips on how to test. Examples of types of fracture fillings such as z-crimp made of different materials are given.

The article describes the life cycle model of high-tech aircraft instrument-making industry products. On the basis of this model is created design automation software package unified information space of the enterprise. Created software package allows us to describe business processes, key generated and used artifacts, types and data formats used by tools, and determine the best set of tools for building an effective unified information space of the enterprise and information support of aviation embedded information and control systems lifecycle.

The coupled three dimensional chains defining the precision parameters of assembly was built for the mounting of power plant on the helicopter’s airframe. For the assembled structure the dimensional forward and inverse problems were stated and numerical algorithm of its resolving was developed. Considering as the “grey box” the 3D dimensional chain with known architecture but unknown sizes of each parts we created the database of the virtual assemblies which was used to find the assembly – analog, and further to the synthesis of one step setting of the moving compensators at mounting of the real world aggregate.

Creation of scientific methods of aviation accidents prevention is important for reduce of accident rate in civil aviation. The development of the automated system of forecasting and prevention of aviation accidents is considered in the present paper.

The work is devoted to the study and creation of software-operative scheduling (MES), developing an algorithm to optimize the machine utilization and reduction of plant downtime of machines.

A method of optimal parameters for electrothermal and jet protection of the airliner cockpit windows from fogging based on the use of the cockpit thermal state mathematical model is developed. Development of methods for solving of direct and inverse problems of heat exchange and determination of confidence intervals of parametrical identification assessment is implemented. The required characteristics of electrothermal and jet protection of the airliner cockpit windows from fogging are obtained.

The features of modern aerospace engineering education defining requirements to modern aerospace education and its contents are formulated.

The numerical integration of differential equations of motion of small bodies in the solar system is considered in the form of Encke . For short-period comets and asteroids Apollo and Aten, a comparison of the results of numerical integration of the equations of motion in standard form and shape of the Encke is conducted. In this article has shown that the equations of Enke is preferable to use for celestial bodies, with close rapprochement with perturbing planets, as well as the use of methods of numerical integration of the low order.