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scientific edition of Bauman MSTU

SCIENCE & EDUCATION

Bauman Moscow State Technical University.   El № FS 77 - 48211.   ISSN 1994-0408

Aeronautical and Rocket Space Engineering

Units for storing liquids in aviation hydraulic systems.
# 12, December 2012
DOI: 10.7463/0113.0513812
I.S. Shumilov, N.P. Solotenkov, T.G. Vinogradova
This article presents schema and constructions of hydraulic tanks of open and closed types used in passenger and maneuverable aircraft. The authors propose a technique of calculation of the necessary volume of fluid for hydraulic tanks of open and closed types; this method takes into account all flight regimes, including flights with a negative overload. The design procedure of the tank geometry which would have an optimal weight is also presented in the article, along with the scheme of open type tank pressurization with high-pressure dry air and reserve pressure boost from the cabin air-conditioner, the scheme of connection and design of the vent tank.
Experimental research of influence of acoustic noises of different types on results of automatic speech recognition
# 01, January 2013
DOI: 10.7463/0113.0508614
O.N. Korsun, A.A. Yacko, I.M. Finaev, V.Ya. Chuchupal
The article presents estimation results of automatic speech recognition by the system based on the method of hidden Markov models. The research was carried out in the following conditions: in a laboratory in the absence of acoustic noises, under the influence of acoustic noises of different types. The presented results give objective quantitative estimation of such characteristics as speaker-independence and noise-immunity of speech recognition systems with little vocabulary, based on Markov models; recommendations on improving speech recognition characteristics are formulated. The authors propose further development of the techniques developed for estimation of influence of flight overloads on speech characteristics and its automatic recognition.
Analysis of factors affecting safety of flight of unmanned aerial vehicles (UAV). Causes of accidents of UAVs and methods of preventing them
# 12, December 2012
DOI: 10.7463/1212.0500452
S.P. Gulevitch, Yu.G. Veselov, S.P. Pryadkin, S.D. Tyrnov
The authors analyzed characteristics of flight operation of unmanned aerial vehicles (UAV) in the whole phase space of expected operating conditions. They consider basic aspects of the providing trouble-free use of unmanned aerial vehicles which exclude their uncontrolled fall to the ground and the resulting unintended damage to human life, health and their property on the ground. Factors that affect safety of flight of unmanned aerial vehicles were analyzed. The authors identified the causes and consequences of an air crash and proposed methods of preventing it.
Magnetic pulsing compression of high-speed metal elements created by an explosion in free flight
# 12, December 2012
DOI: 10.7463/1212.0496555
S.V. Fedorov, I.A. Bolotina
Accumulation of micro-damages as a result of intensive plastic deformation leads to decrease in average density of the high-speed elements which are created by an explosive crimping of shaped metal cladding. In order to compress such elements while testing meteorite shield withstandability it is proposed to use the longitudinal magnetic field effect on these elements; the magnetic filed is produced on the mechanical trajectory of elements before their interaction with the target. An installation scheme was developed for implementation of magnetic pulsing compression of high-speed metal elements created by an explosion. Influence of the solenoid’s length and intensity of magnetic field on the effect of compression of steel and aluminum elements is determined on the basis of numerical simulation. It was established that the induction of the influencing magnetic field should be equal approximately to 50 T for steel elements, and about 30 T for aluminum elements.
Determination of admissible variable for additional deployment of rotor-type solar sail
# 12, December 2012
DOI: 10.7463/1212.0493439
A.S. Popov, S.M. Tenenbaum
While deploying a rotary solar sail it may be necessary to increase its angular velocity (that is, to make its additional deployment). To achieve this, an additional torque is required (additional deployment torque). Due to fragility of the frameless structure it can lead to considerable displacements of the solar sail wings relative to the stiff part of the spacecraft, even to reeling the wings up on the spacecraft. In this paper the authors propose a mathematical model with two degrees of freedom for estimating the dynamic of the spacecraft with two-blade rotary solar sail with an external torque moment. The model is based on the nonlinear motion equations of two-element pendulum (the first pendulum simulates the stiff part of the spacecraft; second pendulum simulates the blades of the solar sail). This model allows to estimate an admissible torque considering the restriction on the deviation angle of the blades from the stationary position. Software for calculations was developed; dependence of additional deployment on the system parameters and character of the load (suddenness) was analyzed.
Method of calculating aerodynamic characteristics of bodies with arbitrarily curved axis

# 11, November 2012
DOI: 10.7463/1112.0492155
I.K. Romanova, V.S. Soloviev
The study of aerodynamics of bodies that received permanent deformation in the process of movement is a very important task. The authors developed an efficient matrix method for describing the geometry of bodies with an arbitrarily curved axis; this method was used as the basis for creating a general method for calculating aerodynamic characteristics of such bodies; this general technique is based on the physical "Newtonian inhibition" hypothesis. This approach allows to calculate not only aerodynamic but inertial characteristics of curved bodies; also it can serve as a basis for formation of a combined method of deformed bodies with head and tail surfaces.
Thermo-electrical motor for small and xsmall space vehicles
# 11, November 2012
DOI: 10.7463/1112.0492149
A.M. Pavlov, A.S. Popov
Nowadays small and minute space vehicles become more and more useful. It is possible to conduct a complex experiment, using such kind of satellites, at the same time launch of these satellites wouldn’t be too expensive. But deficiency of suitable motors makes usage of small satellites less effective. For solving this problem design of a compact thermo-electrical thruster for small space vehicles was developed and some results of laboratory experiments proving theoretical conclusions were published.
Experimental and mathematical simulation of fairing aircraft with braking devices
# 11, November 2012
DOI: 10.7463/1112.0489665
V.T. Kalugin, P.A. Chernuha, Ch.H. Chin
The purpose of this work is to determine the influence of design parameters, such as a form of the fairing, lengthening of the body, type of brakes, on aerodynamic characteristics and flow structure of an aircraft. This paper presents the results of physical experiments on the flow around aircraft with different configurations of the bow and braking. Numerical calculations of the studied bodies and comparative analysis of the results were conducted. Problem formulation and method of calculation were described. The Reynolds equations were closed using the k-omega SST turbulence model. The solution method is based on the finite method algorithm. The influence of gas flow between the plates on the value of the base drag was revealed.
Building a rational scheme of preparation of hydrocarbon fuels according to temperature and moisture content with use of liquid and gaseous nitrogen at launch and technical spaceport complexes
# 10, October 2012
DOI: 10.7463/1012.0486647
S.V. Kobyzev, A.V. Zolin, V.V. Chugunkov
The authors present results of theoretical investigations of heat and mass transfer processes in devices applicable to perform cooling and dehydration of hydrocarbon fuel in the start and technical space center complex. According to the results of the research the authors built a rational scheme of hydrocarbon fuel preparation system with due regard to temperature and moisture content, using storage tanks and storage containers, barbotage machines for preparation of fuel according to moisture content and temperature with use of cold of liquid nitrogen and the cold produced by evaporation of liquid nitrogen of gas nitrogen in the contact heat exchanger. The authors outline advantages of the proposed system over the systems based on the use of vapor-compression refrigeration machines.
Experimental demonstration of azimuthal ion deviation effect in engines with anode layer
# 11, November 2012
DOI: 10.7463/1112.0483882
M.K. Marahtanov, D.V. Duhopel'nikov, S.G. Ivakhnenko, E.V. Vorob'ev
This article considers experimental demonstration of the effect of azimuthal ion deflection in the magnetic field. Deflection of a beam in the magnetic field of opposite polarity was shown. Theoretical dependences for values of an angle of azimuthal deviation obtained in the previous works were confirmed.
The influence of the azimuthal deviation ion plasma jet on the traction motor efficiency with anode layer
# 12, December 2012
DOI: 10.7463/1212.0483944
M.K. Marahtanov, D.V. Duhopel'nikov, S.G. Ivakhnenko, E.V. Vorob'ev, V.I. Krylov
The paper considers problems of changes in tractive coefficient of efficiency of a motor with anode layer by using different working substances. The authors obtained dependences describing the effect of the azimuthal deviation to the specified coefficient of efficiency, confirmed by the results of the experiment. The authors propose assessment criteria of using different working substances to increase tractive efficiency propulsion.
Influence of azimuthal deflection of ions on the beam shape of the engine with anode layer
# 10, October 2012
DOI: 10.7463/1012.0483832
D.V. Duhopel'nikov, S.G. Ivakhnenko
The authors consider influence of azimuthal spin of ions on ion beam divergence in the engine with an anode layer. It is shown that the ion beam takes the form of a one-sheet hyperboloid. The authors obtained dependences describing the hyperboloid, bounding curves and asymptotes, depending on the geometry of the engine and the azimuthal deviation angle. Calculation results in the form of graphic dependencies are given.
Structuring and use of knowledge in the operational monitoring of manned spacecraft
# 10, October 2012
DOI: 10.7463/1012.0479653
M.M. Matyushin, N.V. Mishurova, A.V. Donskov
In this article the authors consider the problem of structuring knowledge about the control process and control object and their application in monitoring manned space vehicles. The authors identified and justified the need to unite the accumulated experience of controlling flights of manned spaceships as a single subject area. Basing on the study, the authors propose a new approach to structuring knowledge about the control process and control objects ; they also consider methods of solving the task and practical application.
Selection of aerodynamic configuration of a probe streamlined by a turbulent swirling gas flow
# 10, October 2012
DOI: 10.7463/1012.0461853
V.T. Kalugin, S.V. Strijak
The purpose of the study is to select an optimum componentry for the device "Scanliner". The authors present results of numerical calculations of streamlining of the probe with different componentry in a swirling gas flow. The problem and solution method are described. Reynolds equations are closed by Menter turbulence model. The basis of the calculation method is a method of control volume. The authors provide a calculation of ADF of different componentry of the bodies at changing the angle of the attack and angular velocity of the spin flow. The authors compare experimental results obtained in the installation 'screw-ring'. Basing on these results, a recommendation can be given re optimal componentry for the device which has a form of a blunt cylinder with two disks.
Numerical simulation of aeroelastic vibrations of profiles using the vortex element
# 08, August 2012
DOI: 10.7463/0812.0445353
A.V. Ermakov
The author studies a model problem of aeroelasticity in which a profile is flown by a two-dimensional flow of an incompressible medium. The profile contour is elastodeformed. To determine elastic deformation of the contour profile the finite element method is used. A beam with six degrees of freedom and a constant cross-section is considered as the final element. For numerical solution of the equations of the profile dynamics the method of expanding to their own forms is used. To calculate the parameters of the flow and unsteady aerodynamic load of the profile the vortex element method is used, it is based on the Lighthill-Chorin model of flow vorticity. Profiles of ellipse and wing are considered as model problems. The main parameters of the design scheme were selected on the basis of aerodynamic characteristics of rigid profiles. The results obtained for the elastic profile show the impact of elastic deformation of the profile on emerging unsteady aerodynamic forces.
New approach to cooling of rocket oxygen-kerosene engine
# 06, June 2012
DOI: 10.7463/0612.0431608
F.V. Pelevin, N.I. Avraamov, P.Yu. Semenov
 The authors analyzed modernization of oxygen-kerosene engines. It was shown that the traditional ribbed cooling channel couldn’t increase efficiency of the first stage oxygen-kerosene engines. New methods of LPE cooling are considered.
77-30569/353104 Double-pulse flights from near-earth waiting orbits to F-orbits of the three-body-problem
# 04, April 2012
F.V. Zvyagin
The article provides the results of the author’s study of the possibility of a double-pulse flight to F-orbits of the Earth-Sun system of the three-body-problem from circular waiting orbits near the Earth. It is indicated that F-orbits are stable, which leads to creation of many various possible applications both for research and practical purposes of deep space exploration. The author gives the F-orbit’s energy characteristic and presents possible flight schemes with quantitative estimations of needful impulses of characteristical speed for flights. Typically, the total required impulse of the characteristical speed for the orbital injection of a spacecraft into F-orbit is less than the total expenditure on the ascent to the parabolic orbit. Variants of possible application are generalized in the conclusion.
77-30569/352636 Double-pulse flights to halo-orbits in the three-body problem
# 03, March 2012
F.V. Zvyagin
During preliminary ballistic design possible flights of spacecrafts (SC) to the neighborhood of collinear libration points of the Earth-Sun system with a monopulse scheme are usually considered. However, such a flight handler has significant radial restrictions of the obtained halo-orbit. The article presents the results of the study illustrating the possibility of extraction of a spacecraft to halo-orbit of an arbitrarily small radius as a part of a double-pulse flight from the Earth’s vicinity. The author provides results of numerical simulation which show that the total expenditure on the extraction with double-pulse schemes was significantly lower than the total expenditure on the extraction to the parabolic orbit from the waiting orbit.
77-30569/345773 Mathematic rollover model in LNG storage tank
# 03, March 2012
N.S. Korolev
The author considers approaches to creating a mathematical model for describing the phenomenon of rollover; the model consists of fast emission of liquefied natural gas (LNG) vapour from the storage tank when the emission was caused by mixing of LNG layers which have different temperatures. Quantitative results of LNG layers behavior in fueling system storage tanks in starting complexes are shown. The analysis of LNG parameters at refuiling in storage tanks allows to predict temperature and pressure levels and to avoid construction damages during operation.
77-30569/332009 The calculating analysis of strength of elements of ground equipment truss structures loaded with intensive high temperature jet
# 02, February 2012
V.A. Igrickii, V.F. Hlybov, A.V. Yazykov
The article describes aspects of the design analysis of strength of ground equipment truss structure loaded with the high temperature jet of launch vehicle engines. The reasonable limitations and calculating model development concepts for the thermal strength calculations were analyzed. Basics of the overall strength analysis were given. The truss structure local thermal strength analysis was considered by the example of joint of piped elements.
 
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