Contents 4(83)

CONTENTS 4(83)
Yeryomin V.V., Lipnitsky Yu. M., Mikhalin V.A. Numerical Simulation of Free Oscillations. Hypothesis of Harmonicity 5

Kartseva E.Yu., Kolyada E.O., Stroilov A.V., Shmanenkov V.N. A Study of Flow Pattern of First Stages of Launch Vehicles during the Ballistic Descent Phase at High Angles of Attack 11

Kovalyov R.V., Trenyov M.G., Churakov D.A. The Impact of Side Supporting Devices on Heat Transfer in the Bottom Area of a Hypersonic Aircraft Model 16

Babikov A.L., Galaktionov A.Yu., Kislykh V.V., Shmanenkov V.N. Calculation-Experimental Research on the PGU-11 Aerodynamic Installation of Separation Flow before a Three-Dimensional Obstacle during Hypersonic Flow over a Blunt Nosed Cone 22

Ganiyev Yu.Kh., Kovalyov R.V., Kozlovsky V.A., Kudryavtsev V.V., Kusov A.L., Rudin N.F. Thermovision Studies of the Influence of Local Heat Inlet/Outlet on Laminar-Turbulent Transition in the Boundary Layer of the Cone Surface 28

Gorshkov A.B., Lapygin V.I., Mikhalin V.A., Sazonova T.V., Fofonov D.M. A Flow over a Triangular Wing at Minimum Heat Flux to Its Surface 36

Kozlovsky V.A. Requirements to the Quality of Manufacturing Aerodynamic Models 43

Kudryavtsev V.V., Safronov A.V., Dyadkin A.A., Polovnev A.L., Pushkin S.D., Rybak S.P. Results of Experimental Studies of Acoustic Processes during the Start of the «Soyuz-2» Launch Vehicle from Different Launch Facilities 51

Shipilov S.N. Shock-Wave Processes during the Start of a Launch Vehicle from a Launch Pad of Semi-Hardened Type in the Presence of Fine Dust Near the Nozzle Exit 57

Murzinov I.N. The Question of the Century: Where Did the Tunguska Meteorite Fly? 65

Bachin A.A., Mazin I.N., Prochukhayev M.V., Sazhin D.S., Khramov N.E. The U-22 Gas-Dynamic Pressure Chamber of FSUE TsNIImash 73

Avershyev S.P., Lipnitsky Yu.M., Makarevich G.A., Pelipenko L.F., Polovnev A.L., Suntsov G.N., Tretyakov P.V. Electromagnetic Pulse Study of a Meteoroid Hypersonic Impact 81

Lelyushkin N.V., Mishin G.S., Novikov S.B. Thermal Regime Prediction of the Cold Circuit in an Infrared Radiometer with Heat Accumulator Based on Thermal Vacuum Test Results Considering Its Orbital Conditions 86

Gorbunova T.I., Znamensky V.V., Senkevich E.A., Trenyov M.G., Fadeyev V.A. Method for Determining Kinetic Characteristics of Thermally Decomposable Materials 91

Brylkin Yu.V. A Comparative Analysis of the Surface of Titanium Nitride Coatings Obtained by Magnetron Sputtering and Plasma-Chemical Method 99

Bershadsky V.A. Mixing Cryogenic Liquid with Condensable Gas for Simulation of the Fuel Flow Thermal State at the Engine Pump Inlet during Bench Testing 105

Medenovskaya E.A. Efficiency Estimation of Systematic Components of Wind Velocity When Calculating Nominal Ascent Trajectories for «Soyuz-2» Type Launch Vehicles 111

Kolesnikov E.P. Efficiency Evaluation of Energy Transfer from Geostationary Orbit to Earth 117

Zolkin S.N. Conditions of Detachable Equipment Loading of a Generalized Analog of Instrument Section of a Launch Vehicle under Vibroacoustic Impact 123

Kalenichin Yu.S., Komarov I.D., Kharchenko A.P. General Mathematical Parametric Model of Product Reliability Control Optimization at a Newly Built Rocket and Space Complex 128

Sharitkin Yu.N. Building Features of Onboard Control Complexes for Team Flight Space Systems 135

Kutomanov A.Yu., Kudryavtsev S.I. Results of Real Efficiency Analysis of Satellite Navigation Equipment Applied to the Development of High Precision Descent Control System of a Perspective Manned Spacecraft 142

Androsov V.Ya., Britova Yu.A., Lyanzburg V.P., Plotnikov A.V., Tveryakov O.V. A Test Bed for Experimental Testing of Force-Torque Characteristics of Electromechanical Executive Bodies 148

V.V. Yeryomin, Yu. M. Lipnitsky, V.A. Mikhalin.
Numerical Simulation of Free Oscillations. Hypothesis of Harmonicity.
The article presents results of mathematical modeling of movement of bodies committing plane angular fluctuations in a gas stream under the influence of aerodynamic forces. It estimates the effect of the inertia moment magnitude on the nature of movement, considering the possibility of finding the values of static and damping moments as part of movement simulation based on the hypothesis of harmonicity. The article proves the admissibility of application of the harmonicity hypothesis in determining the torque characteristics, and its significant impact on the character of the body’s motion.

Key words: stationary and unsteady aerodynamics, numerical simulation, gas-dynamic flow.

E.Yu. Kartseva, E.O. Kolyada, A.V. Stroilov, V.N. Shmanenkov.
A Study of Flow Pattern of First Stages of Launch Vehicles during the Ballistic Descent Phase at High Angles of Attack.
The article presents results of numerical solution of the Reynolds Equations on the basis of various programs in relation to three-dimensional flotation during supersonic flow over the spent stages of launch vehicles (LV) flying at high angle of attack. (α ~ 180°).

Key words: spent stages of launch vehicles, high angles of attack, propulsion system nozzles, unsteady separate areas.

R.V. Kovalyov, M.G. Trenyov, D.A. Churakov.
The Impact of Side Supporting Devices on Heat Transfer in the Bottom Area of a Hypersonic Aircraft Model.
The article presents results of numerical modeling of heat transfer in the cone-shaped base area of the model, obtained in the course of experiments at supersonic piston gas-dynamic units PGU-15 (at Mach number M = 10), and in the wind tunnel U306-3 (М = 6). It analyses the influence of the model’s supporting devices on distribution of heat transfer parameters in its base area. It is shown that the results of flow and heat transfer calculations in a model with side supporting devices obtained by numerical solution of the full system of Navier-Stokes equation are consistent with experimental data.

Key words: hypersonic aircraft (AC) model, piston type gas-dynamic unit (PGU), wind tunnel (WT), heat flow, heat transfer, Navier – Stokes equation.

A.L. Babikov, A.Yu. Galaktionov, V.V. Kislykh, V.N. Shmanenkov.
Calculation-Experimental Research on the PGU-11 Aerodynamic Installation of Separation Flow before a Three-Dimensional Obstacle during Hypersonic Flow over a Blunt Nosed Cone.
The article presents results of research of laminar, transitional and turbulent boundary layers separation on the side surface of aircraft (AC) during factorial modeling with full-scale numbers of Mach M_ = 9,5; Reynolds Re_L = 5^.10⁶ ÷ 3^.10⁷, and the temperature factor = 0,25 ÷ 0,36.

Key words: hypersonic flow, laminar-turbulent transition, separation areas, Navier – Stokes equations.

Yu.Kh. Ganiyev, R.V. Kovalyov, V.A. Kozlovsky, V.V. Kudryavtsev, A.L. Kusov, N.F. Rudin.
Thermovision Studies of the Influence of Local Heat Inlet/Outlet on Laminar-Turbulent Transition in the Boundary Layer of the Cone Surface.
The article presents results of experimental thermovision studies of the effect of local heating or cooling of a wall on the laminar-turbulent transition (LTT) of the boundary layer on the surface of the cone with a half angle of 7°, performed in the wind tunnel U-6 of FSUE TsNIImash.

Key words: boundary layer, the laminar-turbulent transition, local heat inlet/outlet to the wall.

A.B. Gorshkov, V.I. Lapygin, V.A. Mikhalin, T.V. Sazonova, D.M. Fofonov.
A Flow over a Triangular Wing at Minimum Heat Flux to Its Surface.
The article presents results of flow calculation of vicious non-equilibrium hypersonic air flow over a blunt triangular wing, providing approximations to determine the friction coefficient and the Stanton number St. As part of the wing shape task at the minimum heat flux, its configuration and forms of bodies with minimum longitudinal force and maximum aerodynamic quality are determined. It is shown that for given aerodynamic quality, volume, planform, and blunting radius, the total value of heat flux to the surface of the bodies with optimal configurations are close. The values of maximum aerodynamic quality of optimal wings are close to each other, as well.

Key words: non-equilibrium flow, heat flux, friction coefficient, Reynolds Re number, Stanton number.

V.A. Kozlovsky.
Requirements to the Quality of Manufacturing Aerodynamic Models.
The article considers the task of ensuring the accuracy of manufacturing aerodynamic models. It assesses the impact of differences of geometric similarity of the model and a full-scale aircraft, caused by the manufacturing quality of such models, on the accuracy error in determination of aerodynamic characteristics (ADC) in wind tunnels. It also provides recommendations regarding the quality of manufactured models depending on their overall dimensions.

Key words: aerodynamic model, aerodynamic characteristics, accuracy of the model, accuracy error.

V.V. Kudryavtsev, A.V. Safronov, A.A. Dyadkin, A.L. Polovnev, S.D. Pushkin, S.P. Rybak.
Results of Experi-mental Studies of Acoustic Processes during the Start of the «Soyuz-2» Launch Vehicle from Different Launch Facilities.
The article presents research methodology of acoustic processes during the start of launch vehicles with the use of full-scale models and examples of their application. It gives results of experiments with a model of the «Soyuz-2» launch vehicle with the scale of M1:30 at the UV-102 FSUE TsNIImash unit, and the М1:60 model at the unit of the S.P. Korolyov RSC «Energia». The article shows the coordination of the M1:30 model acoustic pressure spectra with test results of the M1:60 model and the field measurements data available, indicating the effectiveness of the described method.

Key words: gasdynamics at the start, aeroacoustics, launch vehicles, launch facilities (LF).

S.N. Shipilov.

Shock-Wave Processes during the Start of a Launch Vehicle from a Launch Pad of Semi-Hardened Type in the Presence of Fine Dust Near the Nozzle Exit.
The article presents results of research of the impact of dust clouds under the nozzle of the launch vehicle (LV) on the values of unsteady pressure, acting on its bottom. With the use of numerical calculations conducted in the framework of a two-speed model of environment, it is shown that the presence of finely dispersed solid phase in the gas under the nozzle during startup of the rocket engine is an intensifying factor for the shock-wave pressure acting on the LV.

Key words: shock-wave processes, startup of the engine, semi-hardened launch facility, two-phase, difference scheme, axisymmetric position, launch vehicle.

I.N. Murzinov.
The Question of the Century: Where Did the Tunguska Meteorite Fly?
The article presents an attempt to give an explanation of certain aspects relating to the ballistics and trajectory of the Tunguska meteorite.

Key words: atmospheric part of the trajectory, meteoroid, bolide, explosion, fragmentation.

A.A. Bachin, I.N. Mazin, M.V. Prochukhayev, D.S. Sazhin, N.E. Khramov.
The U-22 Gas-Dynamic Pressure Chamber of FSUE TsNIImash.
The article describes the current state of the U-22 pressure chamber, presenting a series of results achieved by it.

Key words: pressure chamber, vacuum, dimensions, abnormality, aerodynamic characteristics.

S.P. Avershyev, Yu.M. Lipnitsky, G.A. Makarevich, L.F. Pelipenko, A.L. Polovnev, G.N. Suntsov, P.V. Tretyakov.
Electromagnetic Pulse Study of a Meteoroid Hypersonic Impact. The article provides results of experiments on the measurement of electromagnetic impulse (EMI) in modeling of a meteoroid impact at a speed of 6-8 km/s to the pressurized section of the International Space Station (ISS) with the use of multifunctional ballistic installation (MBI) of FSUE TsNIImash, proving the regularity of EMI and the possibility of its registration.

Key words: spacecraft (SC), pressurized section of the space station, meteoroid particles, high-speed impact of a sample, breakdown, acoustic waves, multifunctional ballistic installation, electromagnetic impulse, Rogowski coil.

N.V. Lelyushkin, G.S. Mishin, S.B. Novikov.
Thermal Regime Prediction of the Cold Circuit in an Infrared Radiometer with Heat Accumulator Based on Thermal Vacuum Test Results Considering its Orbital Conditions.
The article presents methodology for thermal regime prediction of the cold circuit (CC) in an infrared (IR) radiometer with a heat accumulator (HA) based on thermal vacuum test (TVT) results of its model considering given orbital conditions. For calculation of the thermal regime isothermal node method is used. It is shown that the thermal mathematical model (TMM) developed and refined according to the TVT results of the cold circuit, and corresponding to the investigated regime, allows to predict the thermal regime of the circuit and the HA and to optimize their design and parameters in relation to the orbital conditions.

Key words: model, circuit, heat accumulator, thermal vacuum test, thermal mathematical model, phase change material.

T.I. Gorbunova, V.V. Znamensky, E.A. Senkevich, M.G. Trenyov, V.A. Fadeyev.
Method for Determining Kinetic Characteristics of Thermally Decomposable Materials.
The article presents methodology based on comparative analysis of methods to determine the rate constants of the thermal decomposition reaction К₀ and the activation energy Е_а of materials on the results of thermogravimetric tests, which allows to authentically define kinetic characteristics as properties of materials regardless of the testing conditions.

Key words: thermal decomposition, kinetics, the rate of heating, ravine function.

Yu.V. Brylkin.
A Comparative Analysis of the Surface of Titanium Nitride Coatings Obtained by Magnetron Sputtering and Plasma-Chemical Method.
The article presents a comparative analysis of the surface of titanium nitride coatings obtained by deposition on a substrate of copper alloy M1 in the high-frequency (HF) induction heating installation (FSUE TsNIImash HF plasma torch) and ionic bombardment of an AISI 304 alloy substrate in a gateway vacuum facility of continuous action (unbalanced magnetron by LLC «Tekhnoprofil-2000»). It is shown that changes of the surface topography, therefore a decrease of the parameter value of the fractal dimension, determines the uniformity of particle deposition on microdefects of the surface, which allows filling faulted regions developed during previous machining process.

Key words: fractal, scanning tunneling microscopy, surface topology, structure of the surface topography.

V.A. Bershadsky.
Mixing Cryogenic Liquid with Condensable Gas for Simulation of the Fuel Flow Thermal State at the Engine Pump Inlet during Bench Testing.
The article considers the experience of application of a method of mixing condensable gas with a flow of cryogenic fluid to control the temperature and steam content at the inlet to the fuel pumps of the engine during bench tests with simulation of flight operation conditions.

Key words: fuel pump, cryogenic liquid, two-phase flow, the vapor content of hydrogen, cavitation characteristics.

E.A. Medenovskaya.
Efficiency Estimation of Systematic Components of Wind Velocity When Calculating Nominal Ascent Trajectories for «Soyuz-2» Type Launch Vehicles.
The article considers the possibility of using a nominal ascent trajectory and a common flight task (FT) applied to any launch date of a «Soyuz-2» type launch vehicle (LV). It analyzes the sounding results of the wind during preparation for launches in the period from 2006 to 2014. As examples, values of wind disturbance components that create aerodynamic loading of the «Soyuz-2» rocket structure in yaw plane, obtained during several launches of the LV are mentioned. Proceeding from the analysis of existing winds during launch preparation and preflight simulation, the probability Р of launch cancelation due to meteorological conditions for different methods of registering the systematic component of the wind during the calculation of the nominal ascent trajectory, specified in the FT, is determined.

Key words: launch vehicle, atmospheric sounding, wind impact, sustainability, controllability, preflight modeling.

E.P. Kolesnikov.
Efficiency Evaluation of Energy Transfer from Geostationary Orbit to Earth.
The article presents results of efficiency calculations of power transmission lines with the use of microwave (UHF) and laser antennas, considering the impossibility of practical implementation of energy transfers via such lines from a geostationary orbit (GSO) to Earth. It is noted that the given relations within the antenna theory may serve as reference materials for specialists and power engineering students who intend to use microwave and laser power transmission lines.

Key words: space-based solar power station (SLPS), microwave energy transfer, laser radiation.

S.N. Zolkin.
Conditions of Detachable Equipment Loading of a Generalized Analog of Instrument Section of a Launch Vehicle under Vibroacoustic Impact.
The article presents results of calculation study of acoustic loading conditions of onboard systems section of a launch vehicle (LV) instrument bay (IB) generalized analog during the powered flight phase. It gives a comparative analysis of overloads obtained by random vibration, acoustic, and harmonic external impacts.

Key words: instrument section, acoustic loading, spectral plane (SP), random vibration and harmonic impact, correlation, root mean square.
Yu.S. Kalenichin, I.D. Komarov, A.P. Kharchenko.
General Mathematical Parametric Model of Product Reliability Control Optimization at a Newly Built Rocket and Space Complex.
The article considers tasks of risk optimization related to taking erroneous decisions when controlling the reliability characterized by a set of technical parameters of the newly built rocket and space complex (RSC) and its products. It presents an analytical model of loss and costs function due to erroneous decisions related to the emergence of risks when monitoring the technical condition of products. An optimal control plan is suggested to be formed on the basis of minimization of the target function of value expenses for conducting monitoring and ensuring the specified reliability requirements for the RSC by construction phases and hierarchical levels of its products, as well as cost losses due to risks of taking erroneous decisions.

Key words: rocket and space complex products, technical control, risks, model, risk minimization, control plan.

Yu.N. Sharitkin.

Building Features of Onboard Control Complexes for Team Flight Space Systems.

The article considers features of building onboard control complexes (OCC) for the so-called team flight space systems (TFSS). It analyzes basic parameters controlled by the onboard control complex and required for building the TFSS, presenting the most relevant structural schemes of onboard control complexes in dealing with tasks of forming the considered space systems.

Key words: team flight, trawl, cluster, constellation, onboard control complex.

A.Yu. Kutomanov, S.I. Kudryavtsev.
Results of Real Efficiency Analysis of Satellite Navigation Equipment Applied to the Development of High Precision Descent Control System of a Perspective Manned Spacecraft.
The article considers tasks of development of high precision descent control system for the implementation of a perspective manned spacecraft (PMSC) soft landing at Russia’s small-sized launch sites. It provides a relevance assessment of the development of such a system, describing features of high precision descent control using external trajectory information. The article presents sensitivity analysis of accuracy characteristics of satellite navigation equipment (SNE) depending on the angular velocities of the PMSC, assessing the applicability of the existing SNE to control the descent of the spacecraft. Proposals to improve the SNE for solving the task of high precision descent control of the PMSC are also under consideration.

Key words: landing on the territory of the Russian Federation, combined control system, high precision descent control, satellite navigation.

V.Ya. Androsov, Yu.A. Britova, V.P. Lyanzburg, A.V. Plotnikov, O.V. Tveryakov.

A Test Bed for Experimental Testing of Force-Torque Characteristics of Electromechanical Executive Bodies.

The article describes a test bed designed for experimental determination and control of dynamic and force-torque (FT) characteristics of electromechanical executive bodies of spacecraft (SC) in order to ensure the compliance with requirements related to the frequency range and levels of disturbing moments transmitted to the platform of the SC.

Key words: electromechanical executive body, force-torque characteristics, modal imbalance, experimental test, test bed.