dr inż. Krzysztof Kaźmierczak


Doktorat
2015-11-25Modelowanie i symulacja dynamiki lotu na potrzeby syntezy systemów sterowania bezpilotowych statków powietrznych  (WAT)
promotor -- prof. dr hab. inż. Wiesław Sobieraj, WAT
1239 
Ostatnie publikacje
1.Kurnyta-Mazurek P., Kurnyta A., Pręgowska A., Kaźmierczak K., Frąś L.J., Application concept of the active magnetic suspension technology in the aircraft engine, Aviation Advances & Maintenance, ISSN: 2543-9456, DOI: 10.2478/afit-2018-0006, Vol.41, No.1, pp.161-193, 2018
2.Brzozowski B., Kawka K., Kaźmierczak K., Rochala Z., Wojtowicz K., Supporting the Process of Aircraft Maintenance with Mobile Devices, Transactions of the INSTITUTE of AVIATION, ISSN: 0509-6669, DOI: 10.2478/tar-2017-0011, Vol.2017, No.2, pp.247-7-18, 2017

Streszczenie:

Maintenance of aircraft is a complex process and therefore, in order to optimize the process, integrated information systems are increasingly used. Rapid development and wide availability of mobile devices equipped with powerful processors and with a wide range of modern communication connections suggests their high usability for enterprise IT systems. In the Department of Avionics and Air Armament of the Military University of Technology (WAT) an ERP-class (Enterprise Resource Planning) system, intended to support aircraft maintenance [4] has been designed and developed. The main concept of the system is to store the aircraft related and maintenance information in a central repository, i.e. in databases hosted on a central database server. This solution ensures concurrent availability of the data to a large group of authorized users. The key components of the system include the database server and client applications, which ensure access to centralized information resources, according to assigned user rights. The project involves development of client applications using three technologies: web, desktop and mobile one. Developed client applications have successfully passed integration tests performed using sample maintenance data. Currently works on user authorization security and wireless data security are under way.

Słowa kluczowe:

maintenance system, mobile application, aircraft

Afiliacje autorów:

Brzozowski B.-Military University of Technology (PL)
Kawka K.-Military University of Technology (PL)
Kaźmierczak K.-other affiliation
Rochala Z.-Military University of Technology (PL)
Wojtowicz K.-Military University of Technology (PL)
9p.
3.Kaźmierczak K., Przysowa R., Standard sine fitting algorithms applied to blade tip timing data, Journal of KONBiN, ISSN: 1895-8281, DOI: 10.2478/jok-2014-0012, Vol.30, No.2, pp.21-30, 2014

Streszczenie:

Blade Tip Timing (BTT) is a non-intrusive method to measure blade vibration in turbomachinery. Time of Arrival (TOA) is recorded when a blade is passing a stationary sensor. The measurement data, in form of undersampled (aliased) tip-deflection signal, are difficult to analyze with standard signal processing methods like digital filters or Fourier Transform. Several indirect methods are applied to process TOA sequences, such as reconstruction of aliased spectrum and Least-Squares Fitting to harmonic oscillator model. We used standard sine fitting algorithms provided by IEEE-STD-1057 to estimate blade vibration parameters. Blade-tip displacement was simulated in time domain using SDOF model, sampled by stationary sensors and then processed by the sinefit.m toolkit. We evaluated several configurations of different sensor placement, noise level and number of data. Results of the linear sine fitting, performed with the frequency known a priori, were compared with the non-linear ones. Some of non-linear iterations were not convergent. The algorithms and testing results are aimed to be used in analysis of asynchronous blade vibration.

Słowa kluczowe:

turbomachinery, blade vibration, tip-timing, sine fitting, least squares, harmonic oscillator

Afiliacje autorów:

Kaźmierczak K.-other affiliation
Przysowa R.-Air Force Institute of Technology (PL)
4p.
4.Kaźmierczak K., Rochala Z., Wojtowicz K., Metoda generowania dynamiki lotu statku powietrznego zastosowana w symulatorze kabiny samolotu pasażerskiego, Zeszyty Naukowe Politechniki Rzeszowskiej. Mechanika, ISSN: 0209-2689, DOI: 10.7862/rm.2013.40, Vol.XXX, No.85 (4/13), pp.445-453, 2013

Streszczenie:

Modelowanie dynamiki lotu statku powietrznego jest procesem, w wyniku którego można uzyskać odpowiedź na pytania: jak zachowuje się badany statek powietrzny oraz jak należy nim sterować, aby wykonał przewidziane zadanie. W ramach prac prowadzonych w Zakładzie Awioniki i Uzbrojenia Lotniczego Wojskowej Akademii Technicznej zbudowano dydaktyczny symulator kabiny współczesnego samolotu pasażerskiego z zaimplementowanym modelem ruchu statku powietrznego. Oprócz symulacji pracy przyrządów pokładowych stanowisko może służyć do analizy wpływu poszczególnych parametrów geometrycznych, masowych i innych charakterystyk statku powietrznego na jego zachowanie. Dzięki temu możliwe jest podczas zajęć dydaktycznych przebadanie wielu konfiguracji samolotu bez rozwiązywania trudnych zagadnień matematycznych. Studenci mogą więc więcej czasu poświęcić na rozpatrywanie różnych przypadków i analizę jakościową na podstawie przeprowadzonego wirtualnego lotu.

Słowa kluczowe:

dynamika lotu, statek powietrzny, symulator kabiny statku pasażerskiego

Afiliacje autorów:

Kaźmierczak K.-other affiliation
Rochala Z.-Military University of Technology (PL)
Wojtowicz K.-Military University of Technology (PL)
4p.

Lista rozdziałów w ostatnich monografiach
1.
420
Kaźmierczak K., Sobieraj W., Mechanika w Lotnictwie, rozdział: Uproszczony sposób tworzenia wirtualnego modelu dynamiki lotu bezpilotowego statku powietrznego, Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej, I, pp.189-198, 2014
2.
421
Szczepanik R., Przysowa R., Spychała J., Rokicki E., Kaźmierczak K., Majewski P., Thermal Power Plants, rozdział: Application of blade – tip sensors to blade – vibration monitoring in gas turbines, InTech, pp.157-188, 2012

Prace konferencyjne
1.Wołejsza Z., Holnicki-Szulc J., Graczykowski C., Hinc K., Faraj R., Kowalski T., Mikułowski G., Kaźmierczak K., Wiszowaty R., Pawłowski P., Dynamics and control of adaptive airbags for UAV impact protection, ISMA 2018 / USD 2018, International Conference on Noise and Vibration Engineering / International Conference on Uncertainty in Structural Dynamics, 2018-09-17/09-19, Leuven (BE), pp.3661-3670, 2018

Streszczenie:

Small drones with total mass of a few kilograms are becoming more and more popular in many applications increasing the probability of occurrence of emergency situations caused by an equipment failure or a human error. In case of a fall from a high altitude very often it is possible to use parachute rescue systems, which however require relatively long time for deployment and development of braking forces. The touchdown velocity may be large enough to exceed limit accelerations for UAV equipment. The paper presents the concept of deployable airbag systems, in particular with adaptive flow control, which provides a possible solution to the above-mentioned problems. The paper discusses the overall control and adaptation strategy. Simplified methods for mathematical modeling are proposed and formulated for an example on a cylindrical airbag. The conceptual part is concluded with the presentation of the methodology of experimental verification and results of initial tests of the integrated airbag system.

Afiliacje autorów:

Wołejsza Z.-IPPT PAN
Holnicki-Szulc J.-IPPT PAN
Graczykowski C.-IPPT PAN
Hinc K.-other affiliation
Faraj R.-IPPT PAN
Kowalski T.-Adaptronica Sp. z o.o. (PL)
Mikułowski G.-IPPT PAN
Kaźmierczak K.-other affiliation
Wiszowaty R.-IPPT PAN
Pawłowski P.-IPPT PAN
20p.
2.Brzozowski B., Kaźmierczak K., Magnetic field mapping as a support for UAV indoor navigation system, 4th IEEE International Workshop on Metrology for Aerospace, 2017-06-21/06-23, Paduna (IT), DOI: 10.1109/MetroAeroSpace.2017.7999535, pp.583-588, 2017

Streszczenie:

Safe indoor flights of unmanned aerial vehicles (UAVs) requires an independent measurement systems, that will enable efficient navigation in the absence of GPS data. One of the many solutions currently being developed is the use of information about changes in the value of the local magnetic field. This paper presents ways of recording, visualizing and mapping local magnetic field changes that can be used as a support for indoor navigation systems. At the beginning we reviewed devices for acquisition of magnetic field strength and the type of data being recorded. In the next step we analyzed the possibilities of visualization of acquired data. Finally the methods used to generate magnetic field maps of enclosed areas have been presented. In each of the aspects covered in this paper, solutions developed by the authors will be described.

Słowa kluczowe:

Magnetic field, Position estimation, UAV, Indoor Navigation, Avionics.

Afiliacje autorów:

Brzozowski B.-Military University of Technology (PL)
Kaźmierczak K.-other affiliation
3.Brzozowski B., Rochala Z., Wojtowicz K., Gawełda B., Kaźmierczak K., Miniature Airflow Probe for an Unmanned Aerial Vehicle, 3rd IEEE International Workshop on Metrology for Aerospace, 2016-06-21/06-23, Florence (IT), DOI: 10.1109/MetroAeroSpace.2016.7573266, pp.500-505, 2016

Streszczenie:

This paper presents in details design and development of a probe for measuring airflow data for an unmanned aerial vehicle (UAV). The research regards the definition of the requirements and dimensions of the device and limits the measurements to selected aerodynamic parameters only. In the design concept the five parameters gauged in the two independent sections of the probe were envisaged. In the first section temperature, stagnation and static pressure and in the second section flow angles - sideslip and angle of attack (AoA) were determined. The development has been divided into three stages. The first stage included a formulation of the guidelines for the construction of the mechanical elements. The specified requirements included the maximum size of the probe and the resultant restriction on the size of the sensors and their electronics hardware circuits. The next stage was focused on sensors selection and electronics hardware development. Additionally, an appropriate microcontroller system for sensors control and data acquisition was developed. The final stage included formulation of a software algorithm and its implementation. Eventually, the probe was installed on a mini UAV for inflight tests which verified the correctness of the design.

Słowa kluczowe:

Probes, Electron tubes, Temperature measurement, Aerodynamics, Sensors, Blades, Unmanned aerial vehicles

Afiliacje autorów:

Brzozowski B.-Military University of Technology (PL)
Rochala Z.-Military University of Technology (PL)
Wojtowicz K.-Military University of Technology (PL)
Gawełda B.-other affiliation
Kaźmierczak K.-other affiliation
4.Brzozowski B., Kaźmierczak K., Rochala Z., Wojda M., Wojtowicz K., A concept of UAV indor navigation system based on magnetic field measuements, 3rd IEEE International Workshop on Metrology for Aerospace, 2016-06-21/06-23, Florence (IT), DOI: 10.1109/MetroAeroSpace.2016.7573291, pp.636-640, 2016

Streszczenie:

This paper presents a conception of an indoor positioning system for an unmanned aerial vehicle (UAV). The measurement of magnetic field is a main source of information required to estimate a position of the platform. It is a parameter which can be measured with affordable sensors and is easy to obtain. In order to use acquired data, a magnetic field map of the specified environment should be previously determined. Thus, a few ideas of using this information were elaborated. First of all, dedicated hardware had to be designed to implement the method. In this process, a multipurpose measurement system was developed. The measurement system consists of three axis digital magnetometers and battery powered microprocessor system with SD memory card and LCD display. The module was installed on the specially designed chassis that enable testing on 3 different heights. The verification tests were performed in designated room, where permanent magnets were used to modify local magnetic field that could work as beacons.

Słowa kluczowe:

Magnetic field measurement, Magnetic fields, Magnetometers, Earth, Unmanned aerial vehicles, Sensors, Sea measurements

Afiliacje autorów:

Brzozowski B.-Military University of Technology (PL)
Kaźmierczak K.-other affiliation
Rochala Z.-Military University of Technology (PL)
Wojda M.-Military University of Technology (PL)
Wojtowicz K.-Military University of Technology (PL)
5.Przysowa R., Kaźmierczak K., Triggering Methods in Blade Tip-timing Systems, VETOMAC-XII, XII International Conference on Vibration Engineering and Technology of Machinery, 2016-09-07/09-09, Warszawa (PL), pp.129-138, 2016

Streszczenie:

The uncertainty of non-contact blade vibration measurements depends on the precision of time-of-arrival (TOA) or phase measurement. Various TOA estimation methods are used in the existing tip-timing measurement systems, which contribute to differences in vibration amplitude results. The known hardware triggering circuits have structure related to the sensor type and limitations specific to analogue circuits. The paper reviews the current hardware and software methods for conditioning of tip sensors and estimation of time of arrival, including customizable triggering circuits and processing of the sampled sensor output. It presents some measurement solutions developed at ITWL and example results. Selected algorithms of phase estimation, their possible implementation and performance issues are discussed. An exemplary software phase detector, implemented as a state machine, able to adapt to the mean pulse amplitude and ignore noise peaks is demonstrated. Numerical techniques, such as linear and polynomial interpolation and curve fitting, are proposed to process sampled sensor signal in order to increase resolution in time and measure characteristics of the blade-related pulse, including zero-crossing, maximum amplitude, rise time and pulse width. The selection of optimum clock or sampling rate in relation to the blade passing frequency and pulse rise time is discussed.

Afiliacje autorów:

Przysowa R.-Air Force Institute of Technology (PL)
Kaźmierczak K.-other affiliation

Abstrakty konferencyjne
1.Pawłowski P., Płatek P., Sarzyński M., Kaźmierczak K., Suwała G., Frąś T., Janiszewski J., Mechanical response of additively manufactured 2D regular cellular structures made of MS1 steel powder subjected to uniaxial loading tests, AMT 2018, IUTAM Symposium on Mechanical design and analysis for AM technologies, 2018-08-20/08-25, Moskwa (RU), pp.1-4, 2018

Patenty
Numer/data zgłoszenia patentowego
Ogłoszenie o zgłoszeniu patentowym
Twórca / twórcy
Tytuł
Kraj i Nazwa uprawnionego z patentu
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Ogłoszenie o udzieleniu patentu
pdf
419786
2016-12-13
BUP 13/2018
2018-06-18
Holnicki-Szulc J., Faraj R., Pawłowski P., Wołejsza Z., Kaźmierczak K., Hinc K.
Rozkładana konstrukcja sterowca stratosferycznego i sposób zmiany objętości, zwłaszcza rozkładanej konstrukcji sterowca stratosferycznego
PL, Instytut Podstawowych Problemów Techniki PAN, Adaptronica sp. z o.o.
233353
WUP 10/2019
2019-10-31



398776
2012-04-10
BUP 21/2013
2013-10-14
Rokicki E., Spychała J., Kaźmierczak K., Szczepanik R., Rządkowski R., Kowalski M.
Turbina wiatrowa o osi poziomej i łopatach wywołujących efekt Magnusa
PL, Instytut Techniczny Wojsk Lotniczych
223671
WUP 10/2016
2016-10-31
394709
2011-04-28
BUP 23/2012
2012-11-05
Rokicki E., Spychała J., Majewski P., Szczepanik R., Przysowa R., Kaźmierczak K., Dąbrowski W.
Sposób pomiaru prędkości obrotowej oraz drgań koszyczka łożyska
PL, Instytut Techniczny Wojsk Lotniczych
224361
WUP 12/2016
2016-12-30
390904
2010-01-04
BUP 15/2011
2011-07-18
Rokicki E., Spychała J., Szczepanik R., Kaźmierczak K.
Sposób pomiaru drgań łopatki turbiny wirnikowej maszyny przepływowej za pomocą czujnika indukcyjnego dla otoczenia powyżej temperatury Curie
PL, Instytut Techniczny Wojsk Lotniczych
219271
WUP 04/2015
2015-04-30
389600
2009-11-17
BUP 11/2011
2011-05-23
Rokicki E., Spychała J., Szczepanik R., Kaźmierczak K.
Sposób pomiaru drgań łopatki z półką wirnika i drgań tarczy wieńca łopatek z półkami turbinowej maszyny przepływowej za pomocą czujnika indukcyjnego
PL, Instytut Techniczny Wojsk Lotniczych
217099
WUP 06/2014
2014-06-30