
Main / Mikhail Iurievich Sorokin
Author: "Mikhail Iurievich Sorokin"
Artem Igorevich Ponomarev,, graduated from Ulyanovsk State Technical University with a degree in Instrumentation; Postgraduate Student at the Department of Measuring and Computing Systems of UlSTU; his research interests are in the field of designing aerometric equipment. email: artem_lsp@mail.ruA.I. Ponomarev,
Mikhail Iurievich Sorokin, Candidate of Sciences in Engineering; graduated from UlSTU with a degree in Aviation Devices and MeasuringCalculating Complexes; Associate Professor at the Department of Measuring and Computing Systems of UlSTU; his research interests are in the field of aerometric equipment development. email: minich80@mail.ruM.I. Sorokin 

Integration of the measured altitudespeed performances in the system
The air data system used by modern aircrafts is a soft hardware designed to measure, compute, and display the altitudespeed performances as well as other parameters such as air temperature, angles of attack and slip; and to provide to aircrew and consumers (various onboard systems) with this information.
The speed and altitude are one of the most important flight parameters of an aircraft. The operating principle of modern on board equipment for measuring the aircraft movement parameters while in flight is based on an aerometric method.
This article deals with a method for increasing the accuracy and the reliability of aerodynamic angleofattack measurements.
Measurement, pressure, pressure probe, sensor, air data, angle of attack, aircraft, mathematical model, air data system.



Sections: Information systems
Subjects: Information 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. 
Maria Mikhailovna Dubinina, DesignTheoretical Department at Ulyanovsk Instrument Manufacturing Design Bureau (UIMDB) JointStock Company, Postgraduate Student of the Department of Measuring and Computing Complexes; got the Master’s Degree in Instrument Engineering of Ulyanovsk State Technical University; a designengineer of the DesignTheoretical Department at Ulyanovsk Instrument Manufacturing Design Bureau (UIMDB) JointStock Company; an author of articles and inventions in the field of sensors for pressure perception of aircraft aerometric systems. [email: masha_dubinina.73@mail.ru]M. Dubinina, Mikhail Iurievich Sorokin, Ulyanovsk Instrument Manufacturing Design Bureau (UIMDB) JointStock Company, Candidate of Engineering, Associate Professor at the Department of Measuring and Computing Complexes; graduated from the Faculty of Information Systems and Technologies of Ulyanovsk State Technical University; Head of a department at Ulyanovsk Instrument Manufacturing Design Bureau (UIMDB) JointStock Company; an author of articles and inventions in the field of sensors for pressure perception of aircraft aerometric systems. [email: rto@ukbp.ru]M. Sorokin


A Mathematical Model of Pressure Traverse of a Pitotstatic System Cross Section
The article considers the results of researching pitotstatic systems. The authors have been created mathematical model of pressure traverse of a pitotstatic system crosssection. The model has shown that shifting the arrangements of static pressure tap holes along the receiver length has no effect on pressure distribution over the receiver surface essentially. From the results of mathematical modelling, the authors have obtained the data array for a model of a pitotstatic system in order to detect surface pressure. The method of pressure perception compensation on the basis of mass balance has been suggested. Due to this, improvement of static pressure perception accuracy can be provided not only by shifting the arrangements of static pressure tap holes along the receiver cross section perimeter but also by changing the diameter of holes. This can eventually help to achieve required characteristics of static pressure perception of a chamfer angle and incident flow speed. Mathematical modelling, pitotstatic system, pressure traverse, air consumption.



Sections: Mathematical modeling
Subjects: Mathematical modeling. 
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. 
Dmitry Alexanderovich Istomin, PJSC 'Ulyanovsk Instrument Manufacturing Design Bureau', Postgraduate student at Ulyanovsk State Technical University; graduated from the Faculty of RadioEngineering of Ulyanovsk State Technical University; head of a department of PJSC 'Ulyanovsk Instrument Manufacturing Design Bureau'; author of articles, inventions in the field of probes for pressure perception of aerometric systems of aircraft. [email: nio24@ukbp.ru]D. Istomin, Ivan Petrovich Efimov, Ulyanovsk State Technical University, Candidate of Engineering; graduated from Ulyanovsk Polytechnic Institute in the profession 'Aircraft Instrument Making'; Associate Professor at the Chair 'Measuring and Computational Systems' of Ulyanovsk State Technical University; author of articles, inventions in the field of primary pressure transducers of aerodynamic systems of aircraft. [email: eip@ulstu.ru]I. Efimov, Mikhail Iurievich Sorokin, PJSC 'Ulyanovsk Instrument Manufacturing Design Bureau', Candidate of Engineering; graduated from the Faculty of Information Systems and Technology of Ulyanovsk State Technical University; head of a department of PJSC 'Ulyanovsk Instrument Manufacturing Design Bureau'; author of articles, inventions in the field of probes for pressure perception of aerometric systems of aircraft. [email: rto@ukbp.ru]M. Sorokin


A Study of Air Pressure Probes With Aerodynamic Compensation
The paper presents results of trials and a mathematical modeling of air pressure probes with corrugated surface aerodynamic compensation, and gives a rationale to use mathematical modeling for further design of such air pressure probes. Static pressure, mathematical modeling, air pressure probe, aerodynamic compensation.



Sections: Mathematical modeling, calculus of approximations and software systems
Subjects: Mathematical modeling. 
