Abstract: The article presents different methods of control of the lateral motion of aircraft during approach with the use of ILS‐LOC. Results of computer simulations are presented. An assessment of the quality with and without cross‐wind was made with the use of quality coefficients. The control laws are based on PID regulator and its modifications. Moreover, the application of the model‐following control in case of incomplete measurement, i.e. lack of information about the track angle, is presented. For interception, the model is used as the generator of the desired trajectory. The difference between the real and model trajectory is used for wind compensation, instead of the integration in LOC regulator. For control law synthesis for stabilization, linear quadratic regulator method was used.

Abstract: The dynamic growth of general aviation as a mean of transport over medium distances means that people having no extraordinary qualifications or extraordinary physical or mental abilities more often pilot such types of airplanes This phenomenon creates the necessity of giving planes flying qualities that allow them to be safely piloted by ordinary people One way of solving this problem is equipping airplanes with fly‐by‐wire control systems that modify their handling qualities Then the computer included into such control systems modifies the actions taken by the pilot, making the airplane both easier and more comfortable to control This paper presents sample software tools – control algorithms that allowing an airplane's handling qualities to be improved They are prepared by the authors and tested on board an experimental plane That plane was equipped with a prototypical fly‐by‐wire control system, which can modify a plane's responses to a pilot's actions

Abstract: A CAN data bus was used in a project of an experimental Fly‐by‐Wire control system (SPS‐1) mounted on board a PZL‐110 “Koliber” general aviation aircraft. This solution allows the free communication between flight control computers and individual modules of the system. The monitoring of the bus state and data frames is useful during particular hardware tests, system integration, laboratory and in‐flight tests. This report intends to present the specific monitor tool developed with the to SPS‐1. The main part of the CAN monitoring system is software. It realizes acquisition, visualization and conversion of stored data. The monitoring software operates with devices used by an experimental control system and connected to the bus. Particular devices are assigned to separate windows. The operator can control the SPS‐1 system through specialized windows or by virtual cockpit. Apart from this, the CAN monitor controls and simulates selected modules of the SPS‐1 system and works as the bus diagnostics tool.

Abstract: The results of experimental research of acoustic emission signals at destruction of different diameter graphite cylindrical models are considered. It is stated that dependence of area under the curve of acoustic emission signals is directly proportional to the area of an appearing crack.

Abstract: The article considers issues relating to the system of continuous professional training of aviation specialists and formulates fundamental prerequisites of psychological endurance reliability of aircrews in terms of flight safety problems. Analysis is given of factors affecting the efficiency of the “pilot – airplane” interactive system. Results of forecasting the measure of significance of the human factor in aviation for the next 10–15 years viewed in the context of medical and psychological aspects are presented. The structure of personal individuality developed on the basis of psycho‐physiological selection allows the formation of professionally significant qualities in aviation specialists to be influenced and the actions of every crewmember in case of an emergency to be forecast.

Abstract: This article describes the results of research of the acoustic emission of friction pairs in the process of their operation. The dependences of the parameters of acoustic emission that correspond to the alteration of the energy dissipation mechanism of the superficial layers of friction pairs at the transition to “quasiwearless” mode of their operation are obtained.

Abstract: Having overcome a deep crisis, airlines and airports now report continuously growing passenger numbers, and existing infrastructural capacities at many airports reach their limit. At the same time, security requirements have been increasing since 2001, causing additional use of capacity and costs and declining efficiency.

Abstract: This research addresses the issue of conflict detection in Air Traffic Control (ATC) and in Airborne Separation Assurance System (ASAS) domains. Stochastic methods of conflict situation detection and conflict probability evaluation are presented. These methods can be used for air traffic conflict alert and avoidance systems for mid‐range monitoring of air traffic and for flight safety. The mathematical formulation of the problem and the procedure of evaluation are presented. Two methods are introduced. One is based on fast statistical simulation of predicted violations of safe separation standards, and the other gives a closed‐form analytic expression that can be applied to numerical evaluation methods. The next method proposed is a method of sequential evaluation of decision‐making time limit to prevent a dangerous approach of the aircraft for short‐range monitoring. The problem is solved by assuming that the estimation and prediction of trajectory are based on the spline‐function method. The ev...

Abstract: An infantry attack over a specific terrain is modeled. A stochastic method described in our previous study is used. In this model, the position of each soldier during the attack is approximately defined by a square [10 × 10 m] on the battlefield. Making use of the possibilities inherent in a three‐dimensional digital map, a visibility matrix is made up, i. e. the indication whether the enemy sees the soldier in a specific case is given.

Abstract: For low‐velocity impact, drop‐weight impact tests performed by EADS (European Aeronautic Defence and Space Company) Corporate Research Center Germany have been carried out for 2‐D woven E‐Glass/epoxy composite systems to determine material response as a function of absorbed energy and damaged area. Nondestructive techniques like visual inspection and analysis of impact response of the woven fabric laminates at different energy levels are utilized to assess the initiation and progression of interlaminar and intralaminar damage. The dominant damage modes for woven reinforced composite systems were found to be matrix cracking with branching into the adjacent layers, intralaminar cracking by mixture of localized matrix shear and matrix/fibre interfacial debonding, front face indentation, and back face fibre damage. The use of woven fabrics as opposed to cross‐ply unidirectional prepreg tapes is specifically discussed from the point view of microstructure and property. In the case of low‐energy impact...

Abstract: A method to reduce vibration in a helicopter blade under a variable harmonic pressure loading using piezoelectric actuators is presented. The model of a helicopter blade is an equivalent aluminum plate. To decrease the amplitude in the resonant frequency range, piezoelectric actuators are set on the top of the plate. The results were obtained by using the ANSYS finite element code. The temperature analogy method instead of a variable pressure load is assumed for numerical analysis. The influence of piezoelectric actuators on the plate is considered. It is shown that the use of piezoelectric actuators to decrease the vibration of the plate is highly efficient. The most rational arrangements of piezoelectric actuators and the required amount of electric voltage are determined.

Abstract: The work contains the use of Holland's method to optimize the process of picking students to study aviation. In the first stage of research, scientific literature was analyzed. Factors influencing the choice of profession were discussed and methods of research were chosen. In the second stage of research, a survey using Holland's free choice questionnaire and a questionnaire (in shortened form) prepared by Prof. D. Beresneviciene and related to favorite subjects, courses and electives, value orientations, and self‐assessment were conducted in the 10th and 12th forms of four secondary schools in Vilnius. Two hundred pupils were questioned. In the third stage of research, statistical analysis of the data gathered was done.

Abstract: One of the most basic methods of reducing maintenance costs in civil aviation is discussed in this paper. This method, which is used by transport carriers, is a reliability programme. The parameters applied in this programme are described in case as they express the numerical evaluation of failure of aircraft components. Nevertheless, such evaluation permits to assess only the selected components. Other statistical methods must be used to assess the reliability of an entire technical system. For this purpose, a correlation and regression analyses are applied to analyse an entire aircraft system, and some results of this investigation are presented here.

Abstract: The numerical finite element method was used to identify the stress concentration factor of the structure of foamed polymer material under tensile loading by constant strain and depending on cell form, orientation, and geometrical parameters It was determined that the value of the stress concentration factor depends upon both the form and the orientation of the cell with respect to the loading direction It was also determined that the higher ratio of the thickness to the length of the edge of the cell is, the higher the stress concentration factor is The low stress concentration factor is when the angle between edges is approximately 90° and the rounding radius of this angle is from 025R to 04R (R is maximal rounding radius), angle between cell edges, and the direction of loading is equal to 45°

Abstract: The article deals with a non‐linear method of correlation function and spectrum power density estimation for which analogies of A Shuster's periodic diagrams have been used The effect of frequency expansion particularly compensates well‐known aliasing frequency effect It was shown that if different properties of a random process are taking into account, it will allow to get the estimation of spectrum power density, the order of decrease of which corresponds to these differential properties

Abstract: In the article an example of using the Finite Element Method to determine the air distribution that is used in the atomization of fuel by the aerial injector is presented. In detail, Finite Element Method analysis appeared to be helpful in verifying the geometrical parameter of the injector – the two‐flow parameter. The Finite Element Method results data of airflow distributions at the end of sections of an aerial injector allows a real geometric parameter to be verified. Full information about this parameter has shown the need to change other geometrical parameters. This work was made within the framework of a research project financed by State Committee for Scientific Research no. 5T12D 027 24.

Abstract: This paper presents work performed by the Institute of Aerospace Engineering at the Brno University of Technology. The main purpose of the project was to compare the results obtained from complex numerical simulation and analytical solutions of the aeroelastic response of an airplane. Numerical simulations provide a integrated description of the dynamic processes analyzed and monitoring of selected quantities in the time domain. This represents a tool for the visual qualification of the investigated process. Utilization of a simplified beam‐stick model represents an industrial standard in the field of computational aeroelasticity/flight mechanics. The need for complex aeroelastic simulations leads to a concept of an advanced aeroelastic model that integrates an advanced 3D dynamic part (model) with proven aerodynamic theory.

Abstract: This paper is concerned with an analysis of the mechanical phenomena occurring in the process of blind riveting. Blind rivets are commonly used in the aviation industry and allow riveting with one‐sided access. To solve this problem, the finite element method was used. In results of the nonlinear computation performed for a joint containing one rivet, the stress distribution in the separate phases of riveting were analyzed. The plots of riveting force in function of rivet core displacement for different friction coefficients between the rivet and the core and the plastic strain distribution also were obtained. The main purpose of this work was to obtain the initial stress distribution occurring in the rivet and sheets after the mandrel was broken. This analysis showed that after finishing the riveting process the initial stresses occurring in the rivet have high values.