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• DETERMINATION OF TARGET COORDINATE ERRORS IN MULTI-POSITION RADAR USING GROUPS OF UNMANNED AIRCRAFT

  I.V. Borisov , А.S. Kuzmenko , V. Е. Kuryan , Е. М. Levchenko , М.V. Kuryan

  273-284

  2025-07-24

  Abstract ▼

  The article proposes and develops an algebraic method for determining the coordinates of targets and their errors as part of a group of unmanned aerial vehicles. The main assumptions of the developed model of the functioning of a group of unmanned aerial vehicles: The speeds of aircraft do not exceed the speed of sound in the air, and the speeds of targets do not exceed the first space were justified. The main assumptions of the model of operation of a group of unmanned aerial vehicles: the UAV speeds do not exceed the speed of sound in the air, and the target speeds do not exceed the first space one, are justified in the article. Qualitative estimates of the radar signal reception time for a given spatial error of the target coordinates were presented. The conditions for the number of aircraft in the group are formulated, which increase the accuracy of determining the location of the target in space. The various types of errors that arise when organizing the search for targets by a group of aircraft are analyzed. The issues of dependence of the resulting error in calculating the coordinates of the search target on the error in measuring the distance between the aircraft in the group and the target itself, depending on their mutual spatial orientation, are investigated. An algorithm has been developed, calculations and analysis of the results for this task have been carried out. The simulation is based on the proposed algorithm, taking into account random coordinates of the target in a fixed sector and taking into account random errors in the measured distance between a group of aircraft and the search object. The results of modeling the influence of the configuration of a group of unmanned aerial vehicles and the location of the target on the error in determining its coordinates are presented. An assessment was carried out to determine the coordinates of the goals and an error estimate of the proposed algebraic approach. The ways of further research are determined. The issues of estimating the amount of calculation for a large number of goals are considered.
  The scope and effectiveness of the proposed algorithm and method for solving the problem as a whole are determined.

• EVALUATION OF THE SHIELDING COEFFICIENT BY CRITICAL SYSTEM FUSELAGE IN THE COMPOSITION OF THE AIRCRAFT

  V.P. Mozhaytsev, D.V. Semenikhina

  2021-02-13

  Abstract ▼

  This article discusses the problems of ensuring the flight safety of aircraft using electrical /
  electronic systems when exposed to high-intensity electromagnetic fields. A method is being developed
  for analyzing the impact of high-intensity radiated fields that create an electromagnetic environment
  in the aircraft location area, based on the main factors of the aircraft electromagnetic
  compatibility, such as the electromagnetic environment, the mechanism of communication or action,
  the sensitivity or susceptibility of electromagnetic radiation receivers with threshold values of
  interference in the frequency and time domains. Two methods for assessing the aircraft resistance
  to high-intensity electromagnetic fields are analyzed: high-level scan tests and low-level scan
  tests. The purpose of this article is to estimate the fuselage shielding coefficient in the places
  where critical systems units are installed using software for numerical electrodynamic modeling.
  The objective of the study is to create and calculate a mathematical model of the critical system as
  part of an aircraft. The article developed electrodynamic models of the critical system of the aircraft
  – a multifunctional liquid crystal indicator, and the calculation is carried out in the Ansys
  HFSS full-wave electrodynamic design package. Reasonable simplifications are made to the HFSS
  cockpit model for calculating the fuselage-shielding factor. Simplifying the model means eliminating
  small parts and objects that are much shorter than the wavelength and reducing the model's
  area of study, since the critical system blocks are located in the front of the cockpit. The estimation
  of the fuselage-shielding factor in the frequency range from 100 MHz to 1 GHz is carried out, the
  analysis and comparison of the results obtained with the tests in the aircraft are carried out. The
  results are of a similar nature, however, the calculated values of the shielding factor are 5–15 dB
  lower in the frequency range from 400 to 850 MHz. Also in the frequency range up to 400 MHz,
  there are characteristic resonant "dips" of the screening coefficient. The results obtained will
  make it possible to single out the most dangerous sources and zones of excitation of electromagnetic
  interference for subsequent detailed analysis, and to reduce the time and cost of testing.

• THE UNMANNED AMPHIBIAN AIRCRAFT’S TECHNOLOGIES OF COMPLEX NAVIGATION IN THE AVIATION WATER AREA

  E.V. Voloshchenko, V.Y. Voloshchenko

  2021-02-13

  Abstract ▼

  The paper considers the development of technologies for integrated high-precision navigation
  of unmanned amphibian aircraft (UAA) to ensure both positioning and navigation on the surface in
  conditions of limited atmospheric visibility (low cloudiness, masking effect of hydrometeors, night
  time, etc.) in the seadrome’s water area using hydroacoustic a remote control channel operating
  through the use of a bottom network structure of original transmitter-receiver antenna assemblies
  (TAA). Each individual TAA is proposed to be used as an "omnidirectional" sonar bottom beacon in
  the upper hemisphere, consisting of electroacoustic transducers (ET), each of which operates in the
  mode of the parametric transmitting array. The statically generated "partial" lobes of the resulting
  DP of single TAA are uniformly quantized over the bodily sectors in the hemisphere; moreover, due
  to the use of nonlinear acoustics effects, an individual "frequency coloration" of each of the bodily
  sectors is possible. As a result, an individual distribution of “frequency-colored spots” of local ultrasonic
  irradiation can be formed at the “water - air” interface of a given section of the aviation water
  area, and, both continuous and discrete, the latter can be considered as separate points of the required
  trajectory of the UAA, radio electronic equipment which tracks the "acoustically marked"
  section of the required direction of the wiring located ahead of the course.

• AIRCRAFT FLIGHT PATH PREDICTION UNDER COMPLETE PARAMETRIC UNCERTAINTY

  V.V. Kosyanchuk, V.V. Glasov, E.Y. Zybin, Liguo Tan

  2021-04-04

  Abstract ▼

  Most of the methods for predicting the behavior of dynamic systems are based on the information
  about the parameters of their mathematical models. However, the problems of
  nonstationarity, nonlinearity and nonidentifiability of models of real complex systems lead to the
  fact that traditional parametric methods are applicable in practice only when the parameters and
  structure of models of systems are reliably known, and the uncertainties in the formulation of the
  problem are significantly limited. The article describes an original nonparametric method for
  predicting the aircraft flight path under absence of a priori information about the parameters of its
  mathematical flight dynamics model. The proposed method, unlike similar widely known ones,
  does not use logical or statistical calculations and does not require its preliminary training or
  long-term tuning. It is based only on the basis of a retrospective analysis of several sequential
  values of the spatial coordinates of the aircraft and its control signals, therefore it is not subject to
  model errors and can be used to predict the flight path of the aircraft under complete parametric
  uncertainty, even in the case of non-identifiability of its flight dynamics model. The results of numerical
  simulation of the solution to the problem of predicting the flight path of an unmanned
  aerial vehicle of the most common type of quadrocopter under complete uncertainty in parameters
  of its mathematical model are presented. The results obtained confirm the efficiency of the developed
  method and show high performances of the accuracy of solving the problem and the speed of
  tuning the algorithm. The described approach can be used to predict the motion path of any other
  vehicle (car, ship, etc.), if its model is linearizable over the observed time interval and there is
  information about its control signals. Practical implementation of the described nonparametric
  method together with traditional parametric ones will improve the accuracy of flight path predicting
  and solve the problem of high-precision landing of an unmanned aerial vehicle on an actively
  maneuvering ship, and specifically in the event of various critical situations.

• METHODOLOGY FOR ANALYZING THE FAULT SAFETY OF SYSTEMS AND AGGREGATES OF A MULTI-AGENT GROUP OF AIRCRAFT

  A.S. Boldyrev, A.L. Verevkin, L.C. Verevkina

  2022-01-31

  Abstract ▼

  Areas of application of CALS technologies are considered to be: improvement of activities
  in the field of heterogeneous processes occurring at all stages of the life cycle (LC) of products;
  supply chain management throughout the entire LC of products (from the creation of the product
  concept to its disposal); electronic integration of organizations (enterprises) involved in these
  processes at various stages of LC; management of support for LC products One of the most relevant
  areas of development in the aviation industry are: multi-agent technologies for improving the
  efficiency of aircraft (aircraft of various types in a group and a single mission) and CALS technologies.
  The article proposes a methodology for analyzing the fault safety of systems and aggregates
  of the multi-agent group of aircraft as a whole, by types of aircraft, their systems, and aggregates.
  The methodology is given on the example of statistical data of AP and PAP 16 systems: flight navigation,
  exhaust, ignition, fuel, control, power supply, air conditioning; hydraulic, radio communication
  equipment, control devices, and aggregates: engine, propellers, wings, windows, lantern,
  ten aircraft AN-2, L-410, Yak-40, An-24, Tu-134, Yak-42, Tu-154, IL-62, IL-62M, IL-86. In the
  proposed methodology for analyzing statistical data of AP and PAP, transformations with matrices
  are used, which allow not to be limited to the number of systems, aggregates, and the aircraft
  themselves. The operating time before the functional failure of systems and aggregates by types of
  aircraft was calculated, the average probability of functional failure of each of the systems and
  aggregates in a multi-agent group was determined, and the time before the functional failure of a
  multi-agent group of 10 aircraft as a whole, which was 132.5 hours, and it was determined that
  PAP and AP are more likely to occur with the chassis and engine of the aircraft. The given methodology
  allows: to correlate quantitative reliability requirements for systems and aggregates,
  taking into account random factors and uncertainty factors; to assess the feasibility of the established
  reliability requirements; to conduct a comparative analysis and justification of the choice of
  a rational variant of the composition of the aircraft group.

• COMPUTER SIMULATION OF AVIATION SPRAYING WHEN IMPROVING THE TECHNOLOGY OF AERIAL-CHEMICAL WORKS

  V.P. Asovsky, A.S. Kuzmenko

  2021-12-24

  Abstract ▼

  The article considers some practical issues of solving the problems of improving the technology
  of aerial-chemical works using methods of computer modeling of its processes, in particular, on
  non-traditional modes of aviation spraying. These modes are typical for the treatment of areas with
  obstacles at the borders, when the introduction of working fluids is carried out when the aircraft
  descends in the approach to the production passage over the area at the required flight altitude and
  climb after its end. The carried out computational and theoretical studies on the example of the An-2
  biplane aircraft using the previously developed and tested multifactor software tools for modeling the
  processes of forming a vortex trace of an aircraft and depositing in it a spectrum of drops of working
  fluids characteristic of aviation spraying have shown that the use of unconventional technological
  treatment modes can significantly increase the productivity, safety and integral efficiency of aerialchemical
  works and measures for chemicalization of agricultural production in general. It is shown
  that to increase the efficiency of aviation spraying of areas limited by obstacles, it is technically possible
  and economically feasible to use a work scheme that provides for the beginning and end of processing
  of such areas at the stage of descent and climb at distances from obstacles corresponding to
  1-2 seconds of the aircraft flight (for An-2 aircraft at distances of 50–150 m at a flight altitude of up
  to 20 m). Such a scheme provides an increase in the productivity of aviation spraying up to 10–15 %,
  a reduction in the prime cost of treatments by 3–5 % and an increase in economic efficiency by
  2–3 % with an increase in their total effect by 6–8 %.

• ANALYTICAL SYNTHESIS OF THE CONTROL ALGORITHM FOR THE ELECTRIC BRAKING SYSTEM OF THE AIRCRAFT LANDING GEAR

  A.Z. Asanov, A.V. Kukovinets, A.Y. Chekin

  2022-03-02

  Abstract ▼

  Nowadays, researchers are developing technologies in the aviation industry related to the
  electrification of aircraft functional systems. The braking system has a direct impact on the safety,
  stability and functionality of the aircraft. Therefore, the motivation for replacing the hydraulic
  system is accompanied by the results of comprehensive studies of the architectures of electric
  braking systems, including the possibility of improving the quality of such systems through the
  introduction of effective control. The work is devoted to the methodology of analytical synthesis of
  the control algorithm for the electric braking system of the aircraft landing gear, as a multiconnected
  control object, based on the theory of embedded systems. The mathematical model contains
  a description of the electrical, mechanical and thermal processes of the system. The require ments for the quality of transients in terms of the angular velocity of the wheel and the temperature
  on the surface of the frictional disc are set in the form of restrictions on the settling time and overshoot
  and then transformed into the form of a reference model. The results of computer simulation
  of the dynamics of the initial and linearized systems, as well as a system with a synthesized regulator
  by the full vector of states are shown. The discussion about the robustness of the resulting solution
  are presented and the results of computer simulation of a system with a "simplified" regulator
  are shown.

• SPATIAL SEPARATION OF INFORMATION IN THE AIRCRAFT COMMUNICATION DEVICE

  V.N. Nosulenko, I.A. Basul, E.Y. Zybin, М.А. Lelikov

  2022-03-02

  Abstract ▼

  The article presents some results of research aimed at the design of human-machine interfaces,
  taking into account the multimodal nature of human perception, for use in the on-board
  equipment of an aircraft. In particular, we are talking about the possibility of a wider use of audio
  channels for input and output of information. The advantages of sound interfaces in relation to
  visual and tactile ones are, first of all, in the absence of the need for directed attention of the pilot,
  in the ability to create auditory objects in three-dimensional space and indicate the direction to
  several different objects at the same time. In the experiments, the possibilities of spatial separation
  of speech information flows in an aircraft intercom in situations where the level of interference
  significantly exceeded the level of the target speech message were tested. The indicators of target
  message recognition were evaluated in the presence of two types of sound interference: the sound of
  another speech message and the noise of an aircraft engine. The results showed that spatial separation
  of audio messages significantly improves the operator’s ability to recognize their content, regardless
  of the type of interference. The maximum number of errors when recognizing a target message
  corresponds to its spatial position in the same direction as the noise of the interference. At the
  same time, message recognition is significantly better if it is pronounced in a female voice. The fact of
  spatial asymmetry of correct recognitions was also revealed: messages arriving from the right are recognized better than in cases of their arrival from the left. The practical significance of the research
  concerns the possibility of creating intercom with increased security against conflicts between
  different information flows, as well as against the impact of external acoustic noise. The prospect is
  seen in the use of three-dimensional audio interfaces not only as part of an intercom, but also for
  navigation and aircraft control systems, as well as monitoring its state.

• ANALYTICAL REDUNDANCY IN THE AUTOMATIC CONTROL SYSTEM OF AN AIRCRAFT TURBOJET BYPASS ENGINE BASED ON OPTIMAL OBSERVERS

  А. А. Inozemtsev, А.S. Pleshivykh, I.N. Gribkov, А.N. Sazhenkov, N.G. Lamanova

  2022-05-26

  Abstract ▼

  An analytical redundancy in the automatic control system of a bypass turbojet engine
  (ACS turbofan engine) based on optimal observers is proposed. This article is based on previously
  obtained results in previous author's works and is a generalization and analysis of these results in
  order to develop a methodology for improving the fault tolerance of ACS turbofan engines. This
  method is based on the use of optimal observers: the Kalman filter and the Yazvinsky filter, consistent
  with the mathematical model of the ACS turbofan engine. The analysis of the mathematical model of
  the ACS was carried out using the least squares method in a moving window. The accuracy of identification
  of the mathematical model and the required delay time are ensured by optimizing the width
  of the moving window. Estimated with the help of optimal observers, the output vector of the ACS
  turbofan engine includes the following parameters: the rotor speed of the low-pressure compressor
  rotor nв, the rotor speed of the high-pressure compressor nk, the air pressure behind the highpressure
  compressor PK, the gas temperature behind the low-pressure turbine TT. When modeling the
  Kalman filter, a correlation analysis of the input signals was preliminarily carried out. The rationale
  for the advantage of the adaptive Yazvinsky filter compared to the Kalman filter is given. The results
  of mathematical modeling of the algorithmic method of reserving the measurement channel of the
  ACS turbofan engine based on the data of flight tests of a bypass engine of the PS-90A type as part of
  the main narrow-body aircraft TU-214 both in stationary and transient modes are presented. Statistical
  analysis of errors in estimation of the output vector of ACS turbofan engines based on the Kalman
  and Yazvinsky filter has been carried out. It is shown that the proposed analytical redundancy algorithm
  ensures the fulfillment of the requirements for the accuracy and stability of estimates of the
  output vector of ACS turbofan engines when using the Yazvinsky filter and can be recommended for
  use in advanced ACS turbofan engines. Based on the results proposed redundancy method, a direction
  for further research has been formed.