Russian Aeronautics
Russian Aeronautics is a peer-reviewed journal that publishes articles addressing fundamental research, applications, and advancements within the domains of aeronautics, space exploration, rocket science, and engineering. These contributions emanate from academic institutions, research institutes, design bureaus, and research and development units. Subjects covered in the journal are aircraft and rocket equipment design; aerodynamics, strength, dynamics, and control of flight vehicles; aircraft and rocket engine theory and design; technology, automation of aircraft/rocket equipment design and production; aircraft instruments and instrumentation computer complexes. The journal welcomes manuscripts from all countries. The journal covers a wide range of subjects, including the design of aircraft and rocket equipment, aerodynamics, structural integrity, dynamics, flight vehicle control; the theory and design of aircraft and rocket engines; technological aspects and automation involved in the design and production of aircraft and rocket equipment; and aircraft instrumentation and related computational units. Previously focused on translation, the journal now has the aim to become an international publication and accepts manuscripts originally submitted in English from all countries, along with translated works.
PEER REVIEW AND EDITORIAL POLICY
The journal follows the Springer Nature Peer Review Policy, Process and Guidance, Springer Nature Journal Editors' Code of Conduct, and COPE's Ethical Guidelines for Peer-reviewers.
Approximately 5% of the manuscripts are rejected without review based on formal criteria as they do not comply with the submission guidelines. Each manuscript is assigned to at least one peer reviewer. The journal follows a single-blind reviewing procedure. The period from submission to the first decision is up to 33 days. The approximate rejection rate is 10%. The final decision on the acceptance of a manuscript for publication is made by the meeting of the most active members of the Editorial Board.
If Editors, including the Editor-in-Chief, publish in the journal, they do not participate in the decision-making process for manuscripts where they are listed as co-authors. Special issues published in the journal follow the same procedures as all other issues. If not stated otherwise, special issues are prepared by the members of the editorial board without guest editors.
Current Issue
Vol 62, No 4 (2019)
- Year: 2019
- Articles: 28
- URL: https://journals.rcsi.science/1068-7998/issue/view/14310
Aircraft Equipment
Structural Mechanics and Strength of Flight Vehicles
Analysis of the Impact of Fan Blade Geometric Deviations on the Strength Properties
Abstract
The paper presents the results of calculating the strength properties for the fan blades of a regional aircraft gas turbine engine under consideration of manufacturing deviations. The models of blades with different geometric deviations on the airfoil being analyzed, the design model of the fan assembly, the strength properties being estimated, and the design scheme for a set of blades are described. An example of the calculation results is given.
On Estimating the Bearing Capacity of Spiral Wire Clamps
Abstract
The interaction of a spiral wire clamp and a line conductor (cable, rope) is considered to estimate the bearing capacity of the wire clamp and to determine its structural and technological properties. The corresponding boundary and initial value problems are formulated to compute the structural properties of multilayer tension and connecting spiral clamps of various finite lengths. The paper presents an algorithm for estimating the bearing capacity of the connecting clamp with conducting aluminum layer and external protective steel wire layer.
Structural Optimization of Load-Bearing Heated Structures
Abstract
The paper considers the solution of the problem of determining the topology of the heated load-bearing structure and the size of the load-carrying elements that provide minimum compliance within a given mass using the criteria method of evolutionary optimization. The test cases are solved.
An Integral Method of Surface Damping of Bending Vibrations for Thin-Walled Structures
Abstract
The paper discusses the effectiveness of currently used methods of surface damping of bending vibrations for thin-walled structures. The special features of surface damping of vibrations using a free and constraining layer damping are analyzed from a physical point of view and practical application. A combined damping coating is proposed, which allows integrating the positive qualities of both of the above methods. An experimental comparison of the effectiveness of the known and proposed methods for damping of bending vibrations of thin-walled structures is made using the method of free damped oscillations.
Flight Dynamics and Control of Flight Vehicles
Effect of the Mission and Supporting Equipment on Operation of the Magnetometer Sensors of the Foton-M No. 2 Spacecraft
Abstract
The measurement data of three magnetometer sensors were analyzed in order to assess the significance of effect of the mission and supporting equipment operation on the adequacy of measurements of the Earth’s magnetic field by airborne means of the technological Foton-M no. 2 spacecraft. The research results demonstrate the significance of the problem of such effect and allow us to develop measures to eliminate it. It is especially relevant for designing new small spacecraft.
Separation Algorithm of the Soyuz MS Spacecraft from Nonstabilized International Space Station
Abstract
We propose an easy-to-implement algorithm providing the safe (collision-free) separation of the Soyuz MS crew transfer vehicle from the ports of the Rassvet (MRM-1) and Poisk (MRM-2) mini-research modules of the International Space Station at an arbitrary station attitude at the time of separation and angular velocities exceeding the maximum permissible for the current undocking algorithm. A criterion of collision-free separation process is described and a comprehensive mathematical model used for calculation is presented.
Robust Controller Synthesis for Airborne Electro-Optical Device Line-of-Sight Stabilization System with Saturating Actuators
Abstract
A technique of multiobjective robust controller synthesis for an electro-optical device line-of-sight stabilization system with saturating actuators is developed on the basis of polytopic linear parameter-varying system theory. From the computational point of view, the synthesis procedure is reduced to convex optimization under constraints expressed in the form of linear matrix inequalities. The multiobjective synthesis of the robust control law for the stabilization system being considered is performed.
Calculation of Main Design Parameters of a Reactive Penetrator Intended for Movement in Lunar Soil
Abstract
The possibility of using penetrators to study the Moon’s subsurface is considered and possible launch options are indicated. Dependencies are given that allow calculating the penetrator mass, penetration depth, and arising overloads with sufficient accuracy. The use of a solid propellant engine on a penetrator is demonstrated.
Aero- and Gas-Dynamics of Flight Vehicles and Their Engines
A Method to Improve the Aircraft Aerodynamic Characteristics at High Angles of Attack and in Spin
Abstract
Based on the experimental studies of models in a vertical wind tunnel, an aerodynamic solution was found in the form of an extension in front of the horizontal tail of certain geometry, allowing considerable improvement of spin characteristics and ensuring the spin recovery by various methods that is especially important for a trainer aircraft. The paper presents the results of experiments on dynamically similar free-flying models confirming the improvement of spin characteristics and experiments on weight models proving the positive effects obtained.
Selection of the Turbulent Viscosity Model for Numerical Calculation of the Ejector with a Curvilinear Section of the Mixing Chamber
Abstract
The paper presents the calculation results for ejectors with a curvilinear section of the mixing chamber. The choice of a turbulence model is reasoned. The effect of the relative radius of the bleed-off curvature on the pressure loss is analyzed and the application of the methodology developed for calculating ejectors with a curvilinear section of the mixing chamber is justified.
Impact Analysis of Sharp Cone Shape Small Changes on the Position of its Pressure Center at Supersonic and Hypersonic Flow with a Small Angle of Attack
Abstract
The problem of evaluating the maximum possible variations on position of the pressure center is considered for a given limitation of the surface variation values of the sharp cone. An integral expression for the change in the position of the pressure center for a given change in the shape of the cone is obtained. Numerical estimates of possible changes in the position of the pressure center of a sharp cone with small surface distortions at various Mach numbers are presented. The main dimensionless parameters, the “similarity criteria”, characterizing and determining the solution of problem, are indicated.
Application of the Implicit MacCormack Scheme for Computation of Supersonic Turbulent Jets Using the Parabolized Navier—Stokes Equations
Abstract
An effective unconditionally stable numerical method for solving equations describing the flow of supersonic turbulent jets is developed. The method does not require the inversion of block tridiagonal systems of algebraic equations. The results obtained according to this method are in fairly close agreement with the calculations results on the basis of other methods and experimental data.
Aircraft and Rocket Engine Design and Development
Assessment of Technical Risks (Reliability) of Aerospace Equipment in the Process of Design and Development
Abstract
Achieving the accuracy and reliability of the entire range of requirements for samples of aerospace equipment involves the use of system coordination of tasks across the spectrum of indicators and parameters with risk analysis. The theoretical and applied basis for the implementation of system coordination is the approach based on innovative information system methodology of risk management.
Micro Gas Turbine Engine for Unmanned Aerial Vehicles
Abstract
The results of development and manufacture of a micro gas turbine engine for an unmanned aerial vehicle are presented. The calculation features of the main elements of the engine blading section, namely, a centrifugal compressor, a reverse-flow combustor, and a radial-axial turbine are considered. The design of the inlet and output duct, rotor bearings, and lubrication system is described.
Aircraft and Rocket Engine Theory
A Method for Express Analysis of Mechanical, Erosion, and Contaminating Impact of Plasma Jet of Electric Propulsion Thruster onto the Large Object of Space Debris
Abstract
A method for express analysis of mechanical, erosion and contaminating impact of plasma jet of an electric propulsion thruster onto the large object of space debris during its de-orbiting from a protected orbit to the disposal one is presented. The results of analytical and numerical calculations agree that verifies the method validity.
Thermionic Methods of Cooling for Thermostressed Elements of Advanced Reusable Launch Vehicles
Abstract
The technology of thermionic thermal protection of thermostressed elements for aviation and space equipment is discussed. This technology is based on the thermionic emission phenomenon. Estimations of temperature decrease of the surface of thermostressed subsystems of reusable spacecraft and orbital launch vehicles at the thermionic thermal protection application are given.
Study of Mechanical Properties Stability in the Production of Turbine Disks for Gas Compressor Units
Abstract
A statistical analysis of the baseline strength characteristics of the EI698-VD alloy disks of high-pressure turbines of the NK family engines operating as a part of gas compressor units is performed. The results of the assessment of mechanical properties stability in the disk production during the period 1998–2015 are presented.
Regasification of Low-Boiling Hydrocarbon Fuels
Abstract
Methods of transformation of liquefied hydrocarbon fuels on the basis of methane and hydrogen in a gaseous state are considered. The hydrogen and methane regasification condition parameters are numerically studied that allows defining the production characteristics of regasification plant.
Aircraft Production Technology
Sulfide Oxide Corrosion of Modern Heat-Resistant Alloys
Abstract
The influence of the corrosive environment on strength characteristics of heat-resistant alloys at high temperatures is discussed. The results of corrosion tests for two heat-resistant nickelbased alloys simulating the processes of alloy sulfide-oxide corrosion during operation are presented. Extrapolated values of specific mass changes for 5000 h at temperatures of 600–750 °C were determined using the mathematical models obtained for tests lasted up to 1000 h.
Wear and Erosion Resistance of Aircraft Engine Composite Elements in a Gas Abrasive Flow
Abstract
The results of the experimental study of the structural carbon fiber reinforced plastic (CFRP) erosion resistance applied to gas turbine engine structural elements are presented. A methodology for characterizing the process of gas abrasive wear of thin-walled structures made of polymer composite materials has been developed. The factors are found that determine the level of the abrasive effect of dust and gas mixture formed at the take-off and landing. A criterion for material erosion resistance assessment is presented.
Investigation into the Effect of Vibration on the Durability of End Mills at Machining Titanium Alloys
Abstract
The paper considers the effect of vibrations on operability of the end mills at machining titanium alloy blanks. Investigations into the effect of vibrations on the durability of end mills and dependences of the durability on the cutting condition parameters are presented. The paper investigates a problem of the mill teeth run-out and methods of its reduction.
Technical Notes
Risk of Passenger Injuries in the Virtual Certification Tests of an Aircraft Seat Unit
Abstract
An equivalent scheme of finite element modeling of dummy injury in dynamic longitudinal tests of aircraft seats is developed. The proposed scheme of virtual testing allows the injury criteria of a dummy to be evaluated using a simplified computational model that includes a belt, a joint coupling and a shock absorber.
Investigation of Modeling Possibility for Lagging of a Helicopter Operating in Transient Flight Regimes
Abstract
An invitational method is proposed for modeling transient loading processes of a helicopter during a flight. Formulas are presented, which allow performing imitation of lagging. An example of numerical modeling for a transient flight regime is presented.
Stabilization System for the Camera Optical Axis in a Gimbal on a Moving Platform
Abstract
We propose a method of constructing a stabilization system for the camera optical axis using PI controllers and cascaded observers of estimate of the reduced disturbances caused by external and parametric disturbances. The obtained disturbance estimates are used in the control law of brushless direct current motors to increase the stabilization accuracy of the absolute angular velocity of the camera optical axis. The simulation results confirm the effectiveness of the proposed stabilization system.
Labor Rating: Special Aspects of Batch and Pilot Production
Abstract
Some results related to the development and implementation of the NORMA Labor Standards CAD system are given. The system is designed for improving the efficiency of aircraft production technologies in terms of mechanical processing management. A brief review of computer based standardization methods used by aircraft production companies is carried out. The special aspects of integration of process-oriented automation systems are given. The result of research on the development of integrated standards for pilot production is presented.