Digital duplicate of the product in information space shows work physical object throughout its life cycle. The implementation this technology will accelerate development new products, reduce time for their testing and certification, start production. This increase competitiveness national aviation industry products. internal component digital twin is a structured multidimensional matrix functional, technical, technological, operational economic properties that are formed manifested at...

An “interferometr” installation with a normal incidence of sound waves has been created in the laboratory “Vibroacoustics and acoustic design aviation technology” at MAI to study characteristics sound-absorbing materials structures. The equipment main are not inferior leading analogues Bruel&Kjaer, BSWA, Mecanum, Acoustic Awareness, Müller-BBM Industry Solutions GmbH, as well previously developed used Russian Federation. A comparison was made samples structures similar geometric...

The paper considers practical aspects of mathematical modeling in predictions the level near-field pressure pulsations a near-future prototype supersonic business aircraft. A numerical technique based on solution Navier-Stokes equations is proposed. method verified by simulations NASA C608 low-boom demonstrator. We consider flight with M=1.4 at altitude 16,215 m. Good convergence our experimental data and results other researchers shown. Near-field sonic-boom aircraft are used to illustrate...

In the offered work basic positions of conception management product life cycle with reference to difficult aircraft building objects are formulated, functional scheme a uniform information space is offered, and structure technologies applicable for its realisation analyzed.

The almost sixfold growth in air cargo transportation that has taken place over seventeen years, their trends and future laws on emissions noise requirements make it possible to create a modern aircraft with increased range carrying capacity. In this work, is proposed consider the design features of such an aircraft, form for it.

The study is dedicated to the peculiarities of implementing flux limiter flow quantity gradient when solving 3D aerodynamic problems using system Navier–Stokes equations on unstructured meshes. paper describes discretisation a finite-volume method and mathematical model including Spalart–Allmaras turbulence Advection Upstream Splitting Method (AUSM+) computational scheme for convective fluxes that use second-order approximation reconstruction solution facet. A with shock wave structures...

The results of in-flight experiments to determine the structure sound field in cabin and pressure fluctuation fields on surface fuselage RRJ-95NEW-100 prototype aircraft are presented here. Wall spectrums obtained for three zones measuring windows (forward, center, rear fuselage) cruising flight mode. effect jet levels tail is considered. For an without interior, contribution main sources total intensity calculated through A-weighted overall determined. It has been determined that noise mode...

Abstract In this paper, the possibilities of improving traction and economic characteristics a by-pass turbojet engine high-speed passenger aircraft due to minimal modifications high-pressure compressor. A thermodynamic model investigated new design in three-dimensional layout was formed using an automated multicriteria optimization process. computational assessment change compressor is carried out based on numerical gas dynamics.

The paper presents two methods to improve the efficiency of supersonic flow simulation using arbitrarily shaped unstructured grids. first method promotes increasing numerical solution convergence rate and is based on geometric multigrid for initialization field. used obtain initial field distributed physical quantity values, which maximally corresponds converged solution. For this purpose, problem performed a series coarse grids beginning from coarsest one in series. Upon completion...

The paper presents the results of studying effects droplet diameters on NACA0012 airfoil ice accretion, which have been obtained in 3D numerical simulation icing. To simulate motion water droplets as a multiphase medium, Eulerian approach is used, assumes that spherical shapes, do not undergo deformation and breakup, interact with each other, coalescence/fragmentation does take place. Both monodisperse (of same size) polydisperse various sizes) are considered; they represented by spectral...

Abstract An advanced computer technology of the thermal stress state and fatigue life analysis turbine engine exhaust support frames based on use licensed engineering software, as well some specialized home codes are presented in paper. The developed allows perform simulations for full model structure, not only typical fragments models, increase an accuracy calculations significantly reduce a design time.

A complex modeling technique is presented in this paper for a numerical analysis of compressed stiffened composite panels with impact damage. The based on the LS-Dyna code application, which simulates both dynamic deformation panel subjected to local and quasi-static uniform compression within damage zone. has been validated by experimental tests panel. obtained results show that can reduce carrying capacity more than 50% damaged compared undamaged panels.

Problems related to the layout of aircraft hydraulically and electrically actuated systems, as well innovative approaches their designing are discussed in this article terms concept fully electrical equipment airplane, impact on performance being developed, with outside mechanical impacts taken into account. Complex aggregate factors must be account when conducting research battle tolerance combat airplanes helicopters. The applicability a method previously analyzed uncertainties intrinsic...