Autor: Jastrzebski, G. - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Description of the pneumatic work cycle of the starting unit of the UAV launcher
Autorzy:: Jastrzębski, G.
Powiązania:: https://bibliotekanauki.pl/articles/247898.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: launcher
pneumatic trigger
pneumatic system
Opis:: The publication presents a UAV pneumatic launcher designed and built in ITWL. The basic element of the pneumatic launcher is the launch mechanism. The starting mechanism determines the energy parameters that will be reached on the launch pad. The work of the launch engines used in propulsion systems has been reviewed and their advantages and disadvantages are discussed when used in pneumatic launchers. A detailed description of the author’s solution of the pneumatic launching mechanism from the launcher is presented. In order to determine guidelines for the design of pneumatic starter systems, a description of the cycle of operation of the complex pneumatic system was analysed. The description of the pneumatic system’s work cycle was based on the parameters of the flow of the compressed air C and b (C – the sound conductivity of the pneumatic element, b – the critical pressure of the pneumatic element). A set of equations describing the pressure change in the filled and emptied valve compartment and the equation of motion are presented. The equations of a mathematical model describing the pneumatic component and the replacement value of flow parameters for the pneumatic system of series pneumatic components are presented. For the mathematical model, a calculation algorithm is presented which takes into account the initial conditions and the boundary conditions of the various periods of the pneumatic system cycle. Examples of calculation results for a specific pneumatic trigger mechanism are shown. The results obtained were compared with the results of the pneumatic starter station tests and the mathematical model of the pneumatic starter was evaluated.
Źródło:: Journal of KONES; 2017, 24, 4; 61-70
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Impact of opening time of the take-off pneumatic launcher main valve on take-off pressure losses
Autorzy:: Jastrzębski, G.
Powiązania:: https://bibliotekanauki.pl/articles/243547.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: take-off launcher
pneumatic take-off systems
pressure losses
Opis:: This publication presents UAV rope and pneumatic launchers constructed and operated in the Air Force Institute of Technology. The construction and operating principle were presented, and functional properties of the UAV take-off pneumatic launcher were characterised. Furthermore, a detailed diagram of the take-off pneumatic launcher was shown, and an operating principle of the launcher take-off system and pneumatic control of the take-off procedure were discussed. The operation parameters of the most important operational elements (main ball valve, semi-rotary actuator, pneumatic valves controlling the flow) from the launcher pneumatic system were specified. On the basis of data sheets of pneumatic elements, a calculation model of the mass flow (volumetric flow rate) of compressed air flowing through the main valve (ball valve in the take-off cylinder supply line) of the take-off pneumatic launcher was designed. The possible cracks, through which compressed air leaks and the take-off cylinder dead sections during the main valve opening and shot, were characterised and discussed. The calculation model designed for individual leaks and total compressed air leaks in the take-off line of the pneumatic launcher was presented. Based on the mass flow model (volumetric flow rate) of compressed air flowing through the main valve, and total compressed air leaks, the relationship of compressed air energy losses depending on opening time of the main valve of the take-off pneumatic launcher was determined. In the paper, the results of simulation studies for the times shorter than data sheets of the main valve opening were presented. In addition, the change of the compressed air disposable energy losses was defined. Based on the results of simulation studies, the opening time of the take-off launcher main valve for the acceptable disposable energy loss level of the take-off pneumatic launcher was specified.
Źródło:: Journal of KONES; 2016, 23, 4; 175-182
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Experimental method of determining characteristics of power and torque engine for low-power unmanned aerial vehicles
Autorzy:: Jastrzębski, G.
Ułanowicz, L.
Powiązania:: https://bibliotekanauki.pl/articles/245545.pdf
Data publikacji:: 2011
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
internal combustion engines
motor test
motor braking
Opis:: The article presents an analytical determination of power and torque of internal combustion engines of small power. It measured actual power and torque characteristics of internal combustion engines of small power. Three types (methods), braking (receiving power via a hydraulic pump, generator and a package of propellers with variable angle of attack. For each method of receiving power (braking) determined the characteristics of torque and power. There is the summary of results for one engine with different ways of braking. There have been evaluation of the presented methods inhibit combustion piston engines of small power as methods for determining power internal combustion engines. The analysis methods presented in the perspective of the braking engine selection for light unmanned aircraft, and the use of parameters derived from research into engine control. Subject to the evaluation method of adjustment (increase) charged, increasing the load on a liquid or ankle. The criterion for comparing methods for inhibition of internal combustion engines of small power load assumed dependence on the rotational speed n, and obtain maximum power on the motor shaft when the throttle, a reflection of the actual engine operating parameters in its target applications.
Źródło:: Journal of KONES; 2011, 18, 3; 135-142
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Methods for determining the take-off speed of launchers for unmanned aerial vehicles
Autorzy:: Jastrzębski, G.
Ułanowicz, L.
Powiązania:: https://bibliotekanauki.pl/articles/243050.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aviation
unmanned aerial vehicle
take-off launcher
take-off speed
acceleration recorder
lotnictwo
bezzałogowy statek powietrzny
prędkość startu
rejestrator przyspieszenia
Opis:: Unmanned aerial vehicles (UAV) are currently a very rapidly developing type of aviation. The problem of support during the take-off with the use of, i.e. take-off launchers arose along with their development, especially for UAVs with weights and dimensions preventing manual take-off. One of the major issues associated with UAV take-off launchers is for its UAV accelerating element to obtain its initial speed. The article presents three methods of determining launcher take-off speeds for unmanned aerial vehicles, i.e. the concentrated very oblique projection method, the high-speed camera methods, and the acceleration recorder method. The take-off launcher carriage speed in the oblique projection method is determined from a formula. This method involves “ejections” of concentrated masses from the UAV mass range and measuring the component values resulting from the used formula, which contains the range of the oblique projection, the elevation of the projection and its angle. The method using the high-speed camera involves recording the course of ejections of the concentrated mass from the launcher. The average take-off speed is determined on the basis of a take-off run length (section of the launcher race, where the unit accelerates) and defining the start and end frame of the carriage movement. The third method for the determination of the take-off speed utilizes an acceleration recorder. The method with the recorder involves registering a change in the accelerations when the take-off carriage is being accelerated by a system fixed on the carriage or the accelerated object. The article presents the methodology of dynamic tests of object acceleration on a launcher, necessary for the determination of speed with the mentioned methods. Selected results from actual tests with the use of the 01/WS/2015 launcher, which is an element of the ZOCP JET2 set, were presented. The test results are presented in a tabular form. The methods for the determination of the take-off speed were compared on the basis of performed tests. Based on the obtained results, the factors impacting the accuracy of each of the methods were identified.
Źródło:: Journal of KONES; 2018, 25, 1; 170-176
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Examination of hydraulic amplifiers in the aspect of lifetime prediction
Autorzy:: Jastrzębski, G.
Ułanowicz, L.
Powiązania:: https://bibliotekanauki.pl/articles/244003.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: hydraulic amplifier
distributing slider
hydrodynamic radial force
insensitivity (dead) zone of a hydraulic amplifier
durability (lifetime)
Opis:: The paper presents the lifetime analysis for a hydraulic amplifier and considers two types of the flow distributing devices, i.e. a linear distributings lider and a rotarys lider. Description of essential properties associated with operation of distributing devices in hydraulic amplifiers is included with particular attention to analysis of processes that affect wear and tear of hydraulic amplifiers and influence quality of their operation. In that context a set of parameters that determine operation quality of hydraulic amplifiers was found out where mutual independence of the parameters, their unambiguousness and measurability served as the criteria for selection there of two methods of analysis were used that took account for the foregoing assumption, i.e. the method of maximum informative capacity of the parameter and the method that assumes maximum alteration of the technical condition due to execution of the test. The completed examinations made it possible to find out characteristic curves for hydraulic amplifiers with a linear distributing slider as well as with a rotary slider with regard to their accumulated operation time. Further predictions of the hydraulic amplifier lifetime take advantage of the assumption that the deterioration effect of functional parameters attributable to hydraulic amplifiers is represented by a series of time-related values (y1,y2.....yn)i.e. a set of discrete observations {y1=ksi(teta)} associated with an unsteady stochastic process ksi(teta). The relationships how functional parameters o f a hydraulic amplifier vary in pace with its operation time t are described by means of the Gaussian distribution with the assumption that the course of a functional parameter deterioration corresponds to its aggregated characteristic curve that represents resistance of a distributing device embedded into a hydraulic amplifier to wear and tear processes. Wear of crucial parts within a hydraulic amplifier is measured in terms how functional parameters of that part associated with its accuracy, sensitivity and switching speed are getting worse and worse as time goes by.
Źródło:: Journal of KONES; 2010, 17, 3; 165-172
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: A method of investigating internal leakages in aircraft hydraulic units
Autorzy:: Szczepaniak, P.
Jastrzębski, G.
Jóźko, M.
Powiązania:: https://bibliotekanauki.pl/articles/242288.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft hydraulic unit
internal leakage
precision hydraulic pair
Opis:: Methods of diagnosing technical condition of aircraft hydraulic systems have been analysed. Associated precision pairs of aircraft hydraulic systems have been presented. The most essential features of operating conditions and the loads that affect distributor components of sliding pairs have been identified. The structure of BU intensifier with a sliding distributor has been illustrated. Equation for internal leakages for a precision hydraulic pair with a concentric annular gap (clearance) has been presented. Illustrated and discussed are instances of examining internal leakages occurring in hydraulic systems (with direct methods applied). Findings of research into these issues have been presented as based on measurements taken on the hydraulic system of the Su-22 operated by the Air Force of the Republic of Poland. The technique of examining the problem consists in taking and recording measurements of the drop in pressure in the hydraulic system. The relationship between time of pressure-drop and total leakage for hydraulic systems of particular Su-22 aircraft has been illustrated. The results of research direct and indirect methods have been presented and analysed. Both methods have been compared from the aspect of assessing technical condition of the aircraft hydraulic system. Potential factors that could affect measurements with a given method have been identified.
Źródło:: Journal of KONES; 2014, 21, 4; 471-478
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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