Krzysztof Kaźmierczak, Ph.D., Eng.

Department of Intelligent Technologies (ZTI)
Division of Safety Engineering (PIB)
position: senior specialist
telephone: (+48) 22 826 12 81 ext.: 168
room: 411
e-mail: kkazmier

Doctoral thesis
2015-11-25Modelowanie i symulacja dynamiki lotu na potrzeby syntezy systemów sterowania bezpilotowych statków powietrznych  (WAT)
supervisor -- Prof. Wiesław Sobieraj, Ph.D., Dr. Habil., Eng., WAT
1239 
Recent publications
1.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
Abstract:

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.

Keywords:

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

Affiliations:
Kaźmierczak K.-other affiliation
Przysowa R.-Air Force Institute of Technology (PL)
2.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
Abstract:

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.

Keywords:

dynamika lotu, statek powietrzny, symulator kabiny statku pasażerskiego

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

List of chapters in recent monographs
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

Conference papers
1.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
Abstract:

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.

Keywords:

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

Affiliations:
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.-IPPT PAN
2.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
Abstract:

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.

Keywords:

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

Affiliations:
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)
3.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
Abstract:

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.

Affiliations:
Przysowa R.-Air Force Institute of Technology (PL)
Kaźmierczak K.-IPPT PAN

Patents
Numer/data zgłoszenia patentowego
Ogłoszenie o zgłoszeniu patentowym
Twórca / twórcy
Tytuł
Kraj i Nazwa uprawnionego z patentu
Numer patentu
Ogłoszenie o udzieleniu patentu
pdf
419786
2016-12-13
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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.
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403707
2013-04-29
BUP 23/14
2014-11-10
Błachnio J., Kaźmierczak K., Przysowa R., Rokicki E., Spychała J., Szczepanik R., Żakowski M.
Układ do optycznego wykrywania wad powierzchniowych, zwłaszcza szyny kolejowej
PL, Instytut Techniczny Wojsk Lotniczych
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389600
2009-11-17
BUP 11/11
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 06/14
2014-06-30