Coherent method for realizing of the device for modules-units start monitoring of phased antenna array is suggested. Application area of the coherent method includes radar systems with improved special selectivity within systems for the detection of poorly-observable objects and for monitoring the environment of advanced multi-functional pilotless flying apparatuses. Device of selective detection of poorly-obsevvable objects in radar systems of on-board control set pilotness flying apparatuses is considered.

Philosophy as a frame of reference on world around and as the first science is a fundamental basis, "roots" (R. Descartes) for all branches of the scientific knowledge accumulated and applied in all fields of activity of a human being person. The theory of algorithms as one of the fundamental sections of mathematics, is also based on researches of the gnoseology conducting cognition of a true picture of the world of the buman being. From gnoseology and ontology positions as fundamental sections of philosophy modern innovative projects are inconceivable without development of programs,and algorithms.

Methods of the approximate estimations of fatigue durability of composite airframe component typical elements which can be recommended for application at the stage of outline designing of the airplane are generated and presented.

The wording of key terms established in the practice of mathematical modeling of the aircraft flight dynamics is proposed. We discuss the methods for adequacy checking.

The relationship of linear circulation of radial and azimuthal vortex layers with circulation of bound vortex was created. This circulation of bound vortex varies depending on radius and azimuthal location of blade. Three components of induced velocity in the characteristic points of rotor disk area were calculated for the typical laws of circulation distribution of bound vortexes. Among other characteristic points there are the points lying in the blade chord, when this blade is situated in different azimuthal locations and operating modes of rotor. It is of practical interest in rotor characteristics computation.

The paper considers the linear vortex model of rotor which is the three-dimensional helicoid sheet of given geometry. This three-dimensional helicoid sheet is coated y continuously distributed two-component vortex layer. Triangular panels are the elements of discretization of the sheet. These triangular panels are arbitrarily oriented in space. The method, algorithms and programs of calculation of three components of induced velocity vector. Were created this velocity is induced by the elementary area, which is arbitrarily oriented and coated by a vortex layer. The intensity of the vortex layer varies linearly over the surface of the elementary area. The solution was obtained in elementary functions.

Results of numerical research of aerodynamic characteristics of an airship with and without tail having various form of airship body cross-section when an airship pass es through an ascending air stream of the limited cross-section size. Influence of a relative positioning of an airship and a stream on sizes of aerodynamic factors of an airship is determined.

The article is devoted to the analysis of the trajectory parameters obtained during the flight experiment at the start of meteo-rocket MMP-06, to determine major parameters of motion of a round parachute at subsonic speeds in the range of altitudes from 0 to 60 km. The Reynolds number is changed in the range from 10⁴ to1,5·10⁶.The main parameters of the trajectory were obtained according to the experimental data. Only laboratory research on a model parachute systems in such a wide range of Reynolds numbers are found in the literature on parachute subjects. This article obtained results of flight experiment.

The article is addressed to the analysis of the trajectory parameters and videos obtained during the flight experiment at the launch of meteo-rocket MMP-06 with the purpose to determine major parameters of motion of a round parachute at subsonic speeds in the range of altitudes from 0 to 40 km. The data analysis showed that the trajectory of the parachute represents spiral "stretched" by the wind in the horizontal direction and disturbed by random factors of a non-stationary flow around the parachute. The main parameters of the trajectory are obtained according to the experimental data. Only qualitative analysis of spiral motion paths for round parachutes may be found in the publications on parachute subjects. This article presents the quantitative characteristics of this process.

The results of mathematical modeling of IL-96T interrupted take-off are giren in the article.

This article analyzes different ways to synchronize parallel computing processes in the context of solving the task about a free molecular flow in a rectangular channel by the Monte Carlo method.

Efficiency of air-cushion chassis pitching moment control by nozzles rotation at take-off and landing condition of aircraft experimental research is carried out. Researches were conducted using double circuit air-cushion vehicle nozzle device with rotary sheets-nozzles at “flat cell” test bench. During the experiment parameters, such as: incident flow speed V, pressure at receiver Pp, height of model above the plane h, angle of pitch υ, nozzle mounting angles QUOTE , QUOTE were varied.

The features of the physical modeling in the experimental determination of aerodynamics-cal tubes (WT) of low-velocity steady and unsteady aerodynamic characteristics at takeoff and landing of aircraft (LA) with the chassis air-cushion (ball screw) and in studies to determine the stability of equilibrium regimes of movement and shock-absorbing properties of ball screws. Are conscdered the requirements for the experimental facilities, model aircraft with ball screws and re-test of the latest zhimam on the free stream velocity, flow and pressure blowers VР, the frequencies and amplitudes of the oscillations are formulated.

The principle of "early matching" aircraft aerohydrodynamic layouts with air cushion landing gear is suggested. Application of this principle is considered as an example of adaptation to the ball screw base circuit of light transport aircraft. The principle, other than weight, aerodynamic, technological and operational requirements includes additional project activities related to the installation of ball screws.

A simulation approach is discussed for maneuverable aircraft longitudinal motion as nonlinear controlled dynamical system under multiple and diverse uncertainties including knowledge imperfection concerning simulated plant and its environment exposure. The suggested approach is based on a merging of theoretical knowledge for the plant with training tools of artificial neural network field.

The article deals with the investigation of influence of some aireraft surface roughnesses on increasing its drag (Il-76 as an example).

The results of mathematical modeling of IL-96T prolonged take-off are giren in the article.

Measurements of the spectrum of turbulent pressure fluctuations in the damping cavities under perforated plate were conducted in streamlined turbulent flow.

Methods of calculation of engine gondolas and landing gears resistance are given in the article.

The article examines the impact of the educational environment on the economic development of the University, analyzes the stability factors of the educational institution