Wyniki wyszukiwania - BazTech

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Model dynamiki zrzutu bomby w warunkach turbulencji

Kowaleczko G., Pietraszek M., Grajewski K.

Problemy Techniki Uzbrojenia

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2018

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R. 47, z. 146

119--143

PL

Celem niniejszego artykułu jest przedstawienie częściowych wyników badań symulacyjnych prowadzonych aktualnie w Instytucie Technicznym Wojsk Lotniczych. Badania te dotyczą dynamiki lotu ćwiczebnej bomby lotniczej LBĆw-10, która została opracowana w ITWL, a obecnie podlega modernizacji. Symulacje wykonano wykorzystując autorskie oprogramowanie opracowane na potrzeby tych badań. W artykule przedstawiono klasyczny model ruchu przestrzennego bomby oraz podano podstawowe dane tego obiektu. Dokładnie opisano sposób obliczania oddziaływań aerodynamicznych uzupełniając ten opis o przykładowe charakterystyki aerodynamiczne, które otrzymano wykorzystując komercyjne oprogramowanie PRODAS. Dodatkowo przedstawiono sposób uwzględnienia zmienności pola wiatru, a w szczególności turbulencji atmosfery. Zastosowano stochastyczny model pola wiatru. Pokazano przykładowe wyniki obliczeń, które zostaną wykorzystane w procesie modernizacji bomby polegającym na wprowadzeniu aktywnego sterowania torem lotu.

EN

The purpose of this article is to present partial results of simulation tests currently conducted at the Air Force Institute of Technology. These tests concern the flight dynamics of the LBCw-10 flight bomb, which was developed at ITWL and is currently undergoing modernization. Simulations were carried out using proprietary software developed for the needs of these studies. The article presents a classic model of spatial motion of a bomb and basic data of this object. The method of calculating aerodynamic forces is described in detail, complementing this description with exemplary aerodynamic characteristics, which were obtained using commercial PRODAS software. Additionally, the method of taking into account the variability of the wind field, and in particular the turbulence of the atmosphere is presented. A stochastic wind field model was used. Illustrative results of calculations are shown, which will be used in the process of bomb modernization involving the use of active flight path control.

2

Modelowanie i symulacja numeryczna dynamiki zrzutu bomby korygowanej

Kowaleczko G., Pietraszek M., Grajewski K.

Modelowanie Inżynierskie

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2018

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T. 35, nr 66

31--40

PL

W pracy przedstawiono proces modelowania dynamiki oraz wyniki symulacji lotu bomby lotniczej zrzucanej w warunkach spokojnej atmosfery. Opracowano model matematyczny ruchu przestrzennego bomby traktowanej jako bryła sztywna. W obliczeniach wykorzystano charakterystyki masowe i geometryczne opracowanej w Instytucie Technicznym Wojsk Lotniczych bomby ćwiczebnej LBĆw-10, którą poddano modernizacji w celu umożliwienia aktywnego sterowania jej lotem. Charakterystyki aerodynamiczne tej bomby określono, wykorzystując oprogramowanie PRODAS oraz na podstawie wyniku badań przeprowadzonych w tunelu aerodynamicznym. Pokazane przykładowe wyniki obliczeń numerycznych otrzymano z wykorzystaniem autorskiego oprogramowania.

EN

The paper presents a model of the bomb dynamics, which is dropped in calm weather conditions. The description of motion dynamics was based on the model of the rigid body and is dedicated to spatial motion simulation. The mass and geometric characteristics were referred to the LBC-10 training bomb, which had been developed at the Air Force Institute of Technology. Nowadays this bomb is modernized in order to enable the active control of the flight path. The aerodynamic characteristics of this bomb were determined using the PRODAS software and they were also based on the results of the wind tunnel tests. In the paper exemplary results of numerical calculations performed with the author's software are also shown.

3

The evaluation of the efficiency of active control system for aerial bomb

Kowaleczko G., Żyluk A., Pietraszek M., Wijaszka M.

Journal of KONES

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2018

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Vol. 25, No. 4

165--174

EN

The article presents the results of numerical simulation of a laser-guided bomb, which is dropped in calm weather conditions. The prototype of such a bomb was developed at the Air Force Institute of Technology. It was a result of the modification process of the classical training bomb. The modification consisted of building on the bomb's board a detection system to track targets that are designated by laser and a control system to adjust bomb’s glide path to precisely strike the target. In the simulation research, geometric and mass characteristics of the classical training bomb were used. Aerodynamic characteristics of the bomb have been determined using commercial software PRODAS. Using the mathematical model of the bomb spatial motion and model of the laser detection system series of simulations were performed. The main goal was to determine the effectiveness of the adopted construction solution. Therefore, simulations were performed for various initial positions of the bomb and fixed position of the target. It allowed finding the set of control laws coefficients giving the most accuracy of the bomb. The influence of structural modifications of the detection system on the possibility of effective detection and location of the target was also investigated. In the article, exemplary results of numerical calculations performed with the author's software are also shown.

4

Influence of geometric characteristics of the bomb-fluger system on its dynamics

Kowaleczko G., Pietraszek M., Klemba T.

Journal of KONES

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2018

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Vol. 25, No. 4

155--163

EN

The article presents the results of numerical simulations of the bomb-fluger system drop. This system consists of two rigid bodies – a bomb and a fluger, which are connected by a biaxial joint. For the analysis, an author's program was used to simulate the bomb-fluger system drop. Influence of the characteristic points of the system on its stability and dynamics was investigated. Particularly, locations of a bomb mass centre, a fluger mounting point, a fluger aerodynamic focus were tested. The article presents a model of the examined bomb in the wind tunnel, characteristic points of a bomb-fluger system, waveforms of values rate of change angles and the values of angles for different distances, waveforms of values of the angle of nutation and the pitch angle of the fluger relative to the bomb, diagrams of examined points of the location of the centre of the mass and pressure of the fluger, waveforms of values rate of change angles and the values of these angles for different locations of the centre of the mass of the fluger, waveforms of values of the angle of nutation and the pitch angle of the fluger relative to the bomb for different locations.

5

Estimation of the accuracy of laser guided bomb

Kowaleczko G., Pietraszek M.

Journal of KONES

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2016

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Vol. 23, No. 3

271--279

EN

The main goal of the bomb release is to hit the target with a maximum accuracy. Therefore, special active control systems are utilized to improve this accuracy. Some of the most popular are semi-active laser systems of guidance. Selected target is pointed with high-intensity laser by an airborne or ground laser designator. The laser-guided bomb (LGB) tracks this target using on-board laser seeker and adjusts its trajectory. The main task of the control system is to steer the bomb in the way allowing fixing the reflected laser beam in the centre of photo sensor array. This keeps the bomb axis straight toward the target. The aim of this study is to identify factors influencing on the accuracy of the LGB. It was performed for the prototype of LGB, which was designed in the Air Force Institute of Technology. This is the modernized version of the classical LB-10M bomb. Originally, this bomb has only four rear stabilizers and it has been equipped with four additional fins (Fig. 1). These fins allow controlling the bomb's path in active way. Earlier studies have shown that this is the useful method of bomb control both in longitudinal and lateral motions. Analysis proved that range of the bomb can be effectively changed. This paper presents method of flight simulations for released LGB. Calculations were performed using sixdegrees- of-freedom mathematical model of the LB-10M bomb motion. Aerodynamics was calculated using commercial software. Control laws were determined based on signals detected by two pairs of laser sensors. Exemplary results of simulations are submitted and conclusions focused on the main factors influencing on bombing accuracy are shown.

6

Comparative study of an additional oxidizer charge effect on selected operational characteristics of a solid-fuel rocket engine

Pietraszek M., Klemba T., Lubieniecka J., Łukasiewicz J., Pietraszek J.

Czasopismo Techniczne. Mechanika

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2016

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Y. 113, iss. 4-M

65--72

EN

This paper describes a part of research related to the elimination of adverse phenomenon involving the occurrence of a negative oxygen balance of combustion products of missile engines during their firing from aircrafts. It also presents the results of comparative tests of rocket engines equipped with an additional oxidizer charge.

PL

Artykuł opisuje fragment badań związanych z eliminowaniem niekorzystnego zjawiska polegającego na występowaniu ujemnego bilansu tlenowego produktów spalania silników pocisków rakietowych podczas ich odpalania ze statków powietrznych. Przedstawiono również wyniki porównawcze badań silników rakietowych wyposażonych w dodatkowy ładunek utleniacza.

7

Evaluation of the possibility of bomb flight control

Kowaleczko G., Olejniczak E., Pietraszek M., Żyluk A.

Journal of KONES

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2015

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Vol. 22, No. 3

105--115

EN

This paper presents theoretical model dedicated to a guided bomb. A mathematical description of the six-degrees-of-freedom motion of the bomb is shown. Particular attention was paid on aerodynamic forces and moments generated by additional control fins mounted on the front part of the bomb. Exemplary results of a numerical simulation of bombing are submitted and conclusions focused on the possibility of flightpath control are formulated. The paper concerns on the equations of bomb spatial motion and kinematic relations expressed making use of moving coordinate systems, the common origin of which is located at the centre of mass of the bomb. The set of equations of the rotating motion about the centre of mass in the body-fixed reference frame is presented. Aerodynamic forces and moments acting on the bomb are described. Coefficients are determined using the PRODAS software with detailed geometry of the LB-10M bomb. The coefficients were determined for different Mach numbers from 0.4 to 0.8. The important task was research investigations of aerodynamic characteristics with a wind tunnel and a set of experiments in real bombing conditions.

8

Modelowanie dynamiki lotu pocisku rakietowego z wykorzystaniem programu PRODAS

Olejniczak E., Pietraszek M., Ziółkowski Z.

Problemy Mechatroniki : uzbrojenie, lotnictwo, inżynieria bezpieczeństwa

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2014

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Vol. 5, Nr 3 (17)

83-94

PL

W artykule przedstawiono zagadnienia związane z badaniem własności dynamicznych pocisku rakietowego. Przedstawiono realizację badań zgodnie z następującą kolejnością: badania teoretyczne, eksperymentalne oraz weryfikacja. Stosując zasady modelowania, opisano budowę i dane techniczne pocisku rakietowego oraz wykorzystując program PRODAS, opracowano model fizyczny pocisku, w oparciu o który przeprowadzono badania symulacyjne. Wyznaczono charakterystyki masowe, aerodynamiczne oraz podstawowe parametry toru lotu. Następnie omówiono badania doświadczalne podstawowych charakterystyk dynamicznych. Porównanie wyników uzyskanych z badań eksperymentalnych i teoretycznych świadczy o poprawności opracowanego modelu.

EN

The paper has been intended to present the issues of studying dynamic properties of a rocket projectile. The study has been carried out and presented as the following sequence: theoretical analyses, experimental testing works, and their verification. With the theory of modelling applied, a physical model of a rocket projectile has been generated. A mathematical model has been formulated using the PRODAS software. With the latter one as the basis, simulation-based analyses have been made. Mass and aerodynamic characteristics and the most essential parameters of the flight path/trajectory have been found. What follows is the discussion of the experimental study of fundamental dynamic characteristics. Comparison of theoretically found results and those gained experimentally proves the generated model to be correct.

9

Investigation of an additional oxidizer charge effect on selected operational characteristics of a solid-fuel rocket engine

Żyluk A., Pietraszek M.

Journal of Theoretical and Applied Mechanics

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2014

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Vol. 52 nr 1

139--149

EN

The paper has been intended to discuss some issues closely related to the elimination of an extremely disadvantageous phenomenon, i.e. the occurrence of a negative oxygen balance in products of combustion emitted by a solid-fuel rocket engine while launching a missile from the aircraft. Findings of experimental examination of such engines furnished with an additional oxidizer charge have also been presented.

10

Investigation of the Oxidizer Charge Impact Onto Energetic Characteristics Demonstrated by the Stream of Gunpowder Gas Ejected by Solid-Propellant Missile Engines

Pietraszek M., Klemba T.

Prace Naukowe Instytutu Technicznego Wojsk Lotniczych

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2013

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nr 33

203–219

EN

The study discloses outputs from examinations devoted to charges of oxidizers and their impact on behaviour of missile engine operation with particular attention to measures that are undertaken to counteract stall of a helicopter engine. Homogenous solid propellant for missile engines exhibits a negative oxygen balance. When a series of rocket missiles driven by means of such fuel is launched from the helicopter board there is a hazard of the engine stall effect that may lead to killing its engines. Admixture of potassium (II) sulphate (VI) that is added into the combustion chamber of a missile engine as an inhibitor of the combustion reaction favourably alters characteristics of the engine output power and, at the same time, is irrelevant to the available thrust of the engine. Application of the oxidizer as an insert into the engine substantially improves flight safety when rocket missiles are launched from an aircraft and makes it possible to avoid significant changes in the engine design. The paper outlines the results from investigations when a charge of K2SO4 was introduced into the Mk66 missile engine as a compressed bar and the working parameters of the engine were measured. The investigations on a vertical workbench comprised measurements of the engine thrust and temperature in the stream of exhaust gases. The measurement results were compared against figures sourced from the original data sheets of engines.

11

Badanie wpływu ładunku utleniacza na charakterystyki energetyczne strumienia gazów prochowych silnika rakietowego na paliwo stałe

Pietraszek M., Klemba T.

Prace Naukowe Instytutu Technicznego Wojsk Lotniczych

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2013

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nr 33

187–201

PL

W pracy przedstawiono wyniki badań wpływu ładunku utleniacza na charakterystyki pracy silnika rakietowego, w kontekście przeciwdziałania pompażowi silnika śmigłowca. Homogeniczne paliwo stałe silnika rakietowego charakteryzuje się ujemnym bilansem tlenowym. W przypadku odpalania serią pocisków rakietowych napędzanych takim paliwem ze śmigłowca istnieje możliwość wystąpienia zjawiska pompażu, które może doprowadzić do zgaśnięcia jego silników. Wprowadzenie do komory spalania silnika rakietowego na paliwo stałe siarczanu (VI) potasu (II) jako inhibitora reakcji spalania paliwa rakietowego korzystnie zmienia charakterystyki energetyczne silnika rakietowego, jednocześnie nie wpływając na generowany ciąg. Zastosowanie utleniacza jako wkładu do silnika znacząco poprawia bezpieczeństwo odpalania rakiet ze statku powietrznego i nie wymusza zmian w konstrukcji silnika. Praca zawiera wyniki badań wpływu ładunku K2SO4, w postaci zaprasowanego pręta, na charakterystyki pracy silnika rakietowego Mk66. W trakcie badań na hamowni pionowej zmierzono ciąg oraz temperaturę gazów strumienia gazów wylotowych. Wyniki zestawiono z danymi dla oryginalnych silników.

12

Feasibility of measurements in examination of air weapons

Żyluk A., Pietraszek M.

Journal of KONES

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2013

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Vol. 20, No. 3

451--460

EN

Specific features of air weapons, dynamic examinations as an important component of the investigation process, examples of data recorders for parameters of the combat mean under test, telecommunication system for on-line data transmission with the assumption that the system should be composed of components and subassemblies that are commercially available from the market, system for RF transmission of flight parameters in the real time mode are presented in the paper. The system is made up of a transmitter and rpm sensors embedded into the head of the S-7 uncontrolled missile. Signals from the telecommunication module are received and decoded by means of a transducer with the sensitivity of about 2PV and stored in the memory of the TDS 3020 digital oscilloscope from Tektronix as well as in a four-channel digital recorder. The data acquisition system is triggered at the moment when the transmitter installed on the missile head was switched on. The missile was launched several seconds later. The paper includes among others workflow for examination of combat means, composition of measuring instruments for flight tests, data recorders for flight parameters installed on avionic bombs, signal waveforms recorded from rotation sensors and rotation speed variations for the S-7 missile during the flight

13

Removal of detergents from industrial wastewater in ultrafiltration process

Kowalska I., Kabsch-Korbutowicz M., Majewska-Nowak K., Pietraszek M.

Environment Protection Engineering

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2005

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Vol. 31, nr 3-4

207-220

EN

The aim of the study was to evaluate the suitability of UF membranes for purification and concentration of effluents from detergent production. During preliminary experiments flat-sheet Amicon (the cut-off of 100, 50, 1 and 0.5 kDa) and Intersep (the cut-off of 30, 10 and 4 kDa) membranes were used. Semi-pilot and full-scale cross-flow experiments were performed using Koch/Romicon capillary ultrafiltration mod-ules with polysulfone membranes of the cut-off of 2 and 5 kDa. The results obtained indicate that a decrease of membrane cut-off value improves the efficiency of effluent treatment. The membrane with a cut-off of 0.5 kDa yields the best separation efficiency: the decrease of COD-Cr value is over 85%, which corresponds to COD-Cr of permeate equal to 8800g O2/m3. It has been found that UF capillary modules made by Koch/Romicon are suitable for concentration of highly polluted effluents containing detergents. The modules applied are characterised by stable transport and separation properties. In the course of a long-term concentration of effluents, an essential drop in a permeability was not observed and the permeate quality remained almost constant, although a systematic increase in pollution load of the concentrate occurred.

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Nanofiltracja - nowoczesne technologie membranowe w uzdatnianiu wody i oczyszczaniu ścieków w przemyśle spożywczym

Pietraszek M.

Przemysł Spożywczy

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2001

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T. 55, nr 8

58-59

PL

Spośród wielu technik membranowych najbardziej popularne są techniki separacji, w których sita napędową jest różnica ciśnień po obu stronach przegrody filtracyjnej: mikrofiltracja, ultrafiltracja, nanofiltracja, odwrócona osmoza. Różnią się one wielkością zatrzymywanych cząstek i ciśnieniem pracy.