
Main / Vladimir Nikolaevich Moiseev
Author: "Vladimir Nikolaevich Moiseev"
Aleksandr Vitalevich Grebenkin, Marshal Bugaev Ulyanovsk Civil Aviation Institute, Professor at the Department of Flight Operation and Safety; graduated from the Lenin Komsomol Riga Institute of Civil Aviation Engineers; an author of articles and inventions in the field of flight safety and automated control of flight and thrust. [email: grebenkin58@mail.ru]A. Grebenkin, Aleksandr Aleksandrovich Lushnikov, Federal ResearchandProduction Center Joint Stock Company ‘ResearchandProduction Association ‘Mars’, Postgraduate Student at Marshal Bugaev Ulyanovsk Civil Aviation Institute; graduated from Radioengineering Faculty of Ulyanovsk State Technical University; Deputy Chief Designer at Federal ResearchandProduction Center Joint Stock Company ‘ResearchandProduction Association ‘Mars’. [email: a.lushnikov@mail.ru]A. Lushnikov, Vladimir Nikolaevich Moiseev, Federal ResearchandProduction Center Joint Stock Company ‘ResearchandProduction Association ‘Mars’, Candidate of Engineering; graduated from the Faculty of Economics and Mathematics of Ulyanovsk State Technical University; Software Engineer of the R&D Laboratory at Federal ResearchandProduction Center Joint Stock Company ‘ResearchandProduction Association ‘Mars’; an author of articles and inventions in the field of computeraided facilities for naval and aeronautical engineering control. [email: v.n.moiseev@mail.ru]V. Moiseev


Adaptive Stabilization and Tracking of Specified Flight Altitude and Speed
The article considers simulation of using additional signals of the system of automated control of flight and thrust in the section of spoilers (lifting strength and engine thrust control) in combination with control signals on a divingrudder and control of engine thrust by a pilot of the system. In aid of research, the model of creating control signal on a divingrudder and sections of spoilers of an aircraft in order to specify parameters of a control surface was simulated in MATLAB program with the use of Simulink package. The created models allows to get data about influence of adaptive method of flight speed control on parameters of tracking and stabilization of the specified indicated speed of an aircraft under conditions of wind shear, in breaking mode in forward flight, stabilization of the specified flight altitude in comparison with using of additional signal on spoilers and without using it. The obtained model allows to select necessary parameters for the specific control object at the initial stage of development promptly. Adaptive stabilization, auto throttle, divingrudder.



Sections: Automated control systems
Subjects: Automated control systems, Mathematical modeling. 
Vladimir Nikolaevich Moiseev, , Candidate of Engineering; graduated from the Faculty of Economics and Mathematics of Ulyanovsk State Technical University; Software Engineer of the R&D laboratory at Federal ResearchandProduction Center Joint Stock Company ‘ResearchandProduction Association ‘Mars’; an author of articles and inventions in the field of computeraided facilities for naval and aeronautical engineering control. [email: v.n.moiseev@mail.ru]V. Moiseev


The Methodology of Calculation of an Aircraft Range Capability on the Basis of Tactical Radius Data
The article considers issues on the calculation of an aircraft range capability on the basis of tactical radius data within different altitude and speed ranges. In some cases, it is necessary to calculate the enemy’s aircraft range capability. As a rule, such calculations do not have any documents, parameters (fuel flow rate and consumption per kilometre), and methodologies for fuel consumption calculation. Usually, open information sources also do not have any information about the enemy’s aircraft flight distance and time. Due to this fact, the need in indirect and approximate estimation of the enemy’s aircraft range capability with the use of information from public and common data is driven. Information about tactical radiuses within the enemy’s aircraft different altitude and speed ranges is the example of such public data. The proposed methodology for calculation of the enemy’s aircraft range capability allows to estimate the enemy’s capabilities in target attacks with 10% ratio error and can be used in combat management systems of surface ships and shorebased complexes. The methodology is also of great interest for operational and approximate estimation of own forces capabilities in case of the operational loading choice. More accurate calculations should be carries out on the basis of manuals on flight operation and time if such opportunity exists. Navigation calculation, tactical radius, range capability.



Sections: Automated control systems
Subjects: Automated control systems. 
Vladimir Nikolaevich Moiseev, Ulyanovsk State Technical University, Candidate of Engineering; graduated from the Faculty of Economics and Mathematics of Ulyanovsk State Technical University; a software engineer of the department of Federal ResearchandProduction Center Joint Stock Company ‘ResearchandProduction Association ‘Mars’; an author of articles, inventions in the field of computeraided facilities for naval and aeronautical engineering control. [email: v.n.moiseev@mail.ru]V. Moiseev, Mikhail Iurievich Sorokin, Ulyanovsk Instrument Manufacturing Design Bureau, JSC, Candidate of Engineering; graduated from the Faculty of Information Systems and Technologies of Ulyanovsk State Technical University; Head of department at Ulyanovsk Instrument Manufacturing Design Bureau, JSC; an author of articles, inventions in the field of air pressure probes for aircraft data measuring systems. [email: rto@ukbp.ru]M. Sorokin, Ivan Petrovich Efimov, Ulyanovsk State Technical University, Candidate of Engineering; graduated from Ulyanovsk Polytechnical Institute with a specialty in Aircraft Instrument Engineering; Senior Lecturer of the Measuring and Computing Complexes Department of Ulyanovsk State Technical University; an author of articles, inventions in the field of primary pressure sensors of aircraft data measuring systems. [email: eip@ulstu.ru]I. Efimov, Tatiana Ivanovna Davydova, Federal ResearchandProduction Center Joint Stock Company ‘ResearchandProduction Association ‘Mars’, Candidate of Engineering; graduated from the Faculty of Radioengineering of Ulyanovsk State Technical University; lead design engineer at FRPС JSС‘ RPA ‘Mars’; an author of articles in the field of system analysis and information processing. [email: tasha_dav@inbox.ru]T. Davydova


The Mathematical Model of the Static Pressure Flowing Reciever
The article considers the matters of constructing mathematical models of the static pressure following receivers (SPFRS) designated for sensing static pressure on helicopters in a range of airspeeds to 250…350 km/h. SPFRS consist of contracting and diffusing parts. The mathematical model of SPFRS was developed in accordance with results of experimental researches for defining static pressure, dynamic pressure, speed, speed inaccuracy, altitude inaccuracy. The adequacy of the obtained mathematical models is checked through the comparison with the results of experimental researches. The models allow getting reliable data at the contractor convergence angle in 3070 degree, the diffuser aperture angle in 814 degree, the diaphragm coefficient in 0.150.45, windblast speed in 20250 km/h. The influence of separate components (a contractor and a diffuser) on SPFRS pressure coefficient and correlation between experimental data and the results obtained with the mathematical model are considered. With the use of the obtained mathematical models, the process of developing receivers with predicted metrological characteristics can be automated. The ability to take up receivers with required form factors for the specific control object on the original development cycle promptly has been appeared. Mathematical model, static pressure following receiver, contractor, diffuser.



Sections: Mathematical modeling
Subjects: Mathematical modeling, Automated control systems. 
Vladimir Nikolaevich Moiseev, FRPC OJSC ‘RPA ‘MARS, a postgraduate student at Ulyanovsk State Technical University; graduated from the Faculty of Economics and Mathematics of Ulyanovsk State Technical University with a specialty in Applied Mathematics; a software engineer at the department of FRPC OJSC ‘RPA ‘MARS; an author of articles, inventions in the field of air pressure probes of aircraft airdata measuring systems. [email: v.n.moiseev@mail.ru]V. Moiseev, Mikhail Yuryevich Sorokin, Ulyanovsk Instrument Manufacturing Design Bureau, PJSC, Candidate of Engineering; graduated from the Faculty of Information Systems and Technologies of Ulyanovsk State Technical University; a head of a department at Ulyanovsk Instrument Manufacturing Design Bureau, PJSC; an author of articles, inventions in the field of air pressure probes of aircraft airdata measuring systems. [email: rto@ukbp.ru]M. Sorokin, Ivan Petrovich Efimov, Ulyanovsk State Technical University, Candidate of Engineering, graduated from the Ulyanovsk Polytechnical Institute with a specialty in Aircraft Instrument Engineering; Associate Professor of Measuring and Computing Complexes Department of Ulyanovsk State Technical University; an author of articles, inventions in the field of primary pressure sensors of aircraft airdata measuring systems. [email: eip@ulstu.ru]I. Efimov, Nikolay Nikolayevich Makarov, Public Joint Stock Company Ulyanovsk Instrument Manufacturing Design Bureau, Doctor of Engineering, Candidate of Economics; graduated from the Faculty of Aircraft Control Systems and Equipment at Kazan Aiviation Institute named after F. Tupolev, Director General of Public Joint Stock Company Ulyanovsk Instrument Manufacturing Design Bureau; an author of articles and inventions in the field of air pressure probes of aircraft airdata measuring systems. [email: ukbplkv@mv.ru]N. Makarov


Mathematical Model for Pitotstatic Probe
The article deals with mathematical modeling problems of the air pressure probes composed of the front cylindrical receiving tube having inside conical flow stagnation chamber and static pressure holes. Basic mathematical models for the air pressure probes were derived from the mathematical modeling intended for determination of static pressure, dynamic pressure, velocity, velocity and altitude errors. The adequacy of the received mathematical models is checked by comparison against the experimental research findings. Experimental studies were carried out in the T129 wind tunnel of TsAGI with nozzlejet simulator. These models allow to get true data at such parameters as the cylindrical tube radius over the range 6.5 to 8.5 mm, start tube distance to the static pressure holes of 45 to 70 mm, downwash angle of 0 to 90 degrees, incident airflow velocity at 50 to 250 kmh. The received mathematical models enable to automate the engineering process of Pitotstatic probe with metrological performance predictions. This gives the ability to make a quick selection of probes with design parameters required for a specific control object at the initial development stage. Mathematical modeling, pitotstatic probe, mathematical model.



Sections: Mathematical modeling
Subjects: Mathematical modeling. 
Vladimir Nikolaevich Moiseev, Ulyanovsk Instrument Manufacturing Design
Bureau, PJSC, postgraduate student at Ulyanovsk State Technical University; graduated from
the Faculty of Economics and Mathematics of Ulyanovsk State Technical University in the profession Applied
Mathematics; engineer at a calculation and theory department of Ulyanovsk Instrument Manufacturing Design
Bureau, PJSC; author of articles, inventions in the field of air pressure probes of aircraft airdata measuring systems [email: v.n.moiseev@mail.ru]V. Moiseev, Ivan Petrovich Efimov, Ulyanovsk State Technical University, Candidate of engineering sciences, has graduated from the Ulyanovsk Polytechnical Institute
with a speciality Aircraft instrument engineering. The senior lecturer of Measuring and Computing Complexes
Department of Ulyanovsk State Technical University. He has articles, inventions in the field of primary pressure
sensors of aircraft airdata measuring systems [email: еmail: eip@ulstu.ru]I. Efimov, Mikhail Iurievich Sorokin, Ulyanovsk Instrument Manufacturing
Design Bureau, PJSC, Candidate of Engineering; graduated from the Faculty of Information Systems and
Technology of Ulyanovsk State Technical University; head of a department at Ulyanovsk Instrument Manufacturing
Design Bureau, PJSC; author of articles, inventions in the field of air pressure probes of aircraft airdata measuring
systems [email: rto@ukbp.ru]M. Sorokin, Alexander Andreevich Pavlovsky, Ulyanovsk Instrument Manufacturing
Design Bureau, PJSC, graduated from the Faculty of Aircraft Construction of Kharkov Space University;
head of a crew at Ulyanovsk Instrument Manufacturing Design Bureau, PJSC; author of inventions in the field of air
pressure probes of aircraft airdata measuring systems [email: rto@ukbp.ru]A. Pavlovsky


Comparison of Results of Simulation and Experimental Study of the Total Pressure Head Ппдс1
The article compares results of a simulation and an experimental study of the onboard total air pressure head ППДС1 and
evaluates the applicability of a simulation software for gas flow OpenFOAM for a task of total air pressure head. The paper also
considers impact of flow skew to measurement error of total pressure. Simulation, total pressure head, turbulence model.



Sections: Mathematical modeling, calculi of approximations and software systems
Subjects: Mathematical modeling, Electrical engineering and electronics. 
