The occurrence and characteristics of reservoir waters from the Silesian segment of the Rotliegend Basin (SW Poland)

The paper considers the potential for new discoveries of gas accumulations in the Rotliegend Basin on the basis of the analysis of reservoir and hydrochemical tests and the results of reservoir simulations. Several reservoir simulations carried out in the study area (history of production and history matching) demonstrate the regional migration of reservoir waters. The integration of the simulations with mathematical calculations (in consistency with Hubbert’s theory) and with hydrochemical results permits recognition of the regional hydrody- namics and the potential localization of gas fields. In an analysis of the current hydrodynamic and hydrochemical conditions of reservoir waters in the Rotliegend (Lower Permian) strata, attention was focused on part of the sedi- mentary Rotliegend Basin, located south of the Wolsztyn-Pogorzela High, utilizing materials available from drilling and noting the differences between this area and the northern sub-basin. The current hydrogeological conditions and the dynamics of fluid transfer in the Rotliegend Basin are an effect of structural rearrangement during the Laramide orogeny. The basin hypsometry, resulting from the Laramide movements, became the decisive factor that controlled the filtration of groundwater. The recent hydrodynamic characteristics of migrating reservoir waters are reflected in the P-T (fluid pressure and temperature gradient) distribution pattern. Hence, the analysis of this distribution may reveal reactions that have taken place over time. It must be emphasized that clusters of gas fields are located in the zones occupied by stagnant groundwater (rNa/rCl<0.75) under hydrostatic (or slightly higher) pressure

The Analysis of Efficiency of Proportional Navigation Method in Gas-Dynamic Control of Spinning Objects in Flight

W pracy przedstawiono model matematyczny procesu samonaprowadzania wirującego obiektu latającego sterowanego gazodynamicznie. Przeprowadzono badania symulacyjne efektywności takiego sterowania według metody proporcjonalnej nawigacji na przykładzie sterowania w końcowej fazie lotu 120 mm przeciwpancernego pocisku moździerzowego. Wyniki przykładowych obliczeń dynamiki lotu pocisku, zwłaszcza w fazie sterowanej, zobrazowano na wykresach.In the paper the simulation research of target-homing accuracy of a spinning object in flight is presented. Numerical calculation was based on the mathematical model of three-dimension flight of jets control projectile according to the proportional navigation method. Control jets are small orifices in center of gravity and sides of the object to be controlled, through which gas can be ejected. This gas may be generated from compressed gas in bottles or by burning fuel. The influence of the guidance method on the mortar missile flight trajectory, and thus affects such guidance criteria as duration of flight to target, normal accelerations of the missile, guidance error and the possibility of attacks zone was analysed. Achievements of example calculations were presented in the tables and on the graphs

Experimental studies of pulsed rocket engine for gas-dynamic steering of flying objects

Idea gazodynamicznego sterowania lub korygowania trajektorii lotu obiektów kosmicznych znalazła zastosowanie również w pociskach rakietowych [1]. Zasada gazodynamicznej korekcji toru lotu polega na krótkotrwałym przyłożeniu siły określonej wartości, wywołanej ukierunkowanym strumieniem gazów, w odpowiedni punkt na powierzchni korygowanego obiektu. Do wytworzenia takiej siły może być użyty małogabarytowy silnik rakietowy na paliwo stałe. W artykule przedstawiono wyniki wyznaczonych doświadczalnie charakterystyk balistycznych rakietowego silnika korekcyjnego. Przedstawiono także wyniki badań wpływu oddziaływania takiego silnika na dynamikę makiety pocisku, uzyskane na stanowisku badawczym opracowanym i wykonanym specjalnie do realizacji tego zagadnienia.Gas-dynamic steering or correcting of flight trajectory of cosmic objects founds application in the rocket missiles as well. The principle of gas-dynamic correction of flight path consists on a short duration application of a defined force, created by a gas stream of an appropriate directed on a defined point of the corrected object. The force can be produced by a rocket engine of small overall dimension operating on a solid fuel. The results of the experimentally determined ballistic characteristics of the rocket correcting engine are presented. The results of studies on the impact of the interaction of this kind of engine on the dynamics of the missile dummy are also presented. The stand has been elaborated and realized in order to perform the mentioned studies

The Analysis of Trajectory of 122 mm Rotary Missile under the Influence of Interferences

W artykule przedstawiono analizę wpływu zakłóceń na tor lotu 122 mm niekierowanego wirującego pocisku rakietowego. Efektem działania zakłóceń na torze lotu niekierowanego pocisku rakietowego jest jego rozrzut w postaci uchylenia w donośności i uchylenia bocznego. Wpływ gazodynamicznego mimośrodu ciągu i wiatru na tor lotu wirującego pocisku rakietowego przeanalizowano przy wykorzystaniu symulacji komputerowej. Wyniki analiz i badań przedstawiono w postaci wykresów i tabel.In this paper the analysis of influence on trajectory of 122 mm unguided rotary missile has been presented. Results of interferences that act during the flight of unguided missile are his dispersion in the form of range and lateral deflections. The influence of deviation of thrust has been researched by means of computer simulation. Results of analysis and research work have been presented in the form of graphs and charts

Experimental research works on the gas-dynamical control of an object

W referacie przedstawiono wyniki badań doświadczalnych wpływu oddziaływania pojedynczego rakietowego silniczka korekcyjnego na dynamikę pocisku rakietowego. Wyznaczenie charakterystyk balistycznych rakietowego silniczka korekcyjnego oraz zbadanie ich wpływu na dynamikę makiety pocisku, przeprowadzono na stanowisku badawczym, opracowanym specjalnie do realizacji tego zagadnienia.Some results of experimental research works on the impact of a single correcting rocket motor on the missile trajectory are presented in the paper. The measurement of ballistic characteristics of this corrective motor and its influence onto the missile mock-up dynamics was carried out on the test bed specially developed for this reason

The role of structural and parametricmodelling in the process of selecting Enhanced Geothermal System location in sedimentary rocks

In the years 2010–2013, analysis of rocks that build the sedimentary covers in Poland was carried out from the point of view of utilization of energy accumulated in closed geothermal systems – so-called Enhanced Geothermal Systems (EGS). Preliminary assessment of available digital cartographic data in terms of variability in the structural setting, thickness, and geothermal and reservoir parameters allowed selecting, for detailed studies, an area situated in central Poland in the Kujawy segment of the Mid-Polish Anticlinorium, in the Mogilno-£ódŸ Trough and in the northern margin of the Fore-Sudetic Monocline. A complex structural- parametric model was constructed for this area, which comprised the interval from the base of the Carboniferous up to the base of the Cenozoic. The model was a basis for further modelling (e.g. others, modelling of the electric and thermal energy production potential). The study results indicate that the most favourable conditions for the development of EGS occur in the Lower and Middle Buntsandstein deposits to the NE of the K³odawa salt diapir (in the Krooeniewice–Kutno vicinity). They are buried to depths greater than 5000 m b.s.l., their thicknesses exceed 1000 m and they are characterised by porosity about 2.5%, permeability about 0.1 mD and mean density approximately 2.7 g/cm3

Measuring temperature distribution on the surface of flying missiles

There are problems associated with flight of objects such as rockets after exceeding sound barrier. One of them is heating up their body during the flight, especially at low altitudes. Overheated surface of rocket leads to serious consequences, such as rapid destruction of material components of missile. It could cause an interference with target tracking signal if it is on the spectral range of missile optoelectronic detecting head. It can cause destruction of flying missile in extreme cases. In addition, temperature increase causes an increase of drag force of object what directly influences its ballistic parameters. The subject of the paper is to present a concept of experimental set-up to test the heating of missile body at flight. The set-up is based on a wind tunnel. Four missiles were selected for initial analysis in order to test some typical designs for significantly different flight velocities and aerodynamics. Boundary layer at flow around the surface, determining temperature field of missile, the local distribution of heat transfer coefficients on the sphere and exemplary distribution of temperature and pressure on the sphere during flow around, distribution of Nusselt numbers for different velocities of flow around roll, numerical model of rockets, distribution of Mach number, temperature field and velocity vectors are presented

An Inverse Approach to Estimate Heat Transfer Coefficients of 122 mm Medium-Range Missile During Correction Engine Operation

This paper presents an inverse approach to estimate the heat transfer coefficients on the inner and the outer sides of a cylindrical shield made of R35 steel containing a gas-dynamic control block of a 122 mm medium-range missile during the combustion of propulsion charge in a correction engine. The specific heat and the thermal diffusivity of R35 steel was experimentally determined using both Netzsch DSC 404F1 Pegasus and LFA 427 measuring devices, respectively. The obtained temperature characteristics of the thermo-physical parameters of cylindrical shield materials were then used to calculate the temperature field concerning the main problem. The inverse problem based on the parameter estimation method using Levenberg–Marquardt optimization procedure was applied to find the unknown heat transfer coefficients. To solve the inverse problem the temperature histories at some locations of the cylindrical shield were known from the experiment. For this purpose a test measuring stand was built and during the combustion process of the propulsion charge inside the cylindrical shield containing the correction engine the temperature distribution on the outer surface of the cylindrical shield was recorded by means of a high-speed infrared camera (PhantomV210). A two-dimensional axial-symmetric nonlinear heat conduction model which takes into account the heat loss due to convection and radiation was solved using the Finite Volume Method (FVM). It was found that the assumption of fixed heat transfer coefficients on both sides of the cylindrical shield was sufficient enough to achieve a satisfactory compliance between the measured and the calculated temperature histories at the same location

Ocena przydatności głowic obserwacyjno-śledzących dalekiego zasięgu dla systemu rozpoznania aerostatu stratosferycznego

The paper presents the problems of applications of stratospheric systems to increase the tactical and reconnaissance capabilities of the Polish Armed Forces. The paper contains the results from examples of simulations which were designed to determine the cost/performance ratio of the production and operation of aerostats with strictly identified technical parameters in the context of their operational capabilities. It also describes the principles of operation of aerostats for the support of intelligence collection and the limitations imposed on aerostats by the specificity of tropospheric and stratospheric regions. Finally, the article presents basic information about optoelectronic parameters of tracking and targeting units intended for operation in the stratosphere with a selection of optoelectronic tracking and targeting unit designs developed by Polish and leading global manufacturers.W artykule przedstawiono problematykę wykorzystania systemów stratosferycznych do zwiększenia możliwości taktycznych lub rozpoznawczych Sił Zbrojnych RP. Przedstawiono wyniki przykładowych symulacji, których celem jest określenie wskaźnika koszt/efekt wykonania i zastosowania aerostatów o ściśle określonych parametrach technicznych w kontekście ich możliwości operacyjnych. Opisano także zasady wykorzystywania aerostatów do wspierania sposobów pozyskiwania informacji wywiadowczych oraz ograniczenia aerostatów wynikające ze specyfiki obszarów troposfery i stratosfery. W artykule podano podstawowe informacje związane z parametrami optoelektronicznych głowic śledząco-celowniczych, przeznaczonych do pracy w stratosferze oraz przedstawiono wybrane konstrukcje optoelektronicznych głowic śledząco-celowniczych firm polskich i zagranicznych przodujących na rynku światowym