Journal of KONES. Powertrain and Transport最新文献

{"title":"DIAGNOSTIC TELEMETRY SYSTEM","authors":"R. Wróbel, M. Andrych-Zalewska, R. Dimitrov","doi":"10.5604/12314005.1217306","DOIUrl":"https://doi.org/10.5604/12314005.1217306","url":null,"abstract":"The theoretical aspects of diagnostics and diagnostic methodology are an important issue. Apart from theoretical aspects, this paper presents experiment results and a practical implementation example. Telemetry has a numbe of different definitions, depending on the area of application. It is generally defined as data acquisition at a remote, inconvenient and/or dangerous location and subsequent transmission of the data to another location for analysis. Telemetry systems are increasingly popular. The most widely used systems include the equipment for monitoring truck scales. The data obtained with this method allow estimating vehicle weight with accuracy between 90% and 98%. Currently a large number of ready-made, professional telemetry systems are commercially available. The LabView programming language used in this example allows for data visualization and acquisition. It also allows saving the executed program as an individual application. The measurements additionally included temperature, throttle position and battery voltage. Experiments proved that for stable communication an 80 kbps band is required. The commonly used telemetry systems, and even their custom-made original versions (as the one here presented), allow for remote diagnostics of an object using widely available communication technologies. The problem seems to be very development and requires further studies, which are scheduled in the near future.","PeriodicalId":165563,"journal":{"name":"Journal of KONES. Powertrain and Transport","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117033825","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"COMPOSITE ROTOR BLADES TESTS ESSENTIAL BEFORE MOUNTING ON GYROPLANE","authors":"A. Sobieszek, M. Wojtas","doi":"10.5604/12314005.1217289","DOIUrl":"https://doi.org/10.5604/12314005.1217289","url":null,"abstract":"The article presents the course of the composite rotor blades tests. Object of study was designed in Institute of Aviation, new airfoil for gyroplane rotors and technology of manufacturing carbon rotor blades were made. When the test program was developed, we focused for special test to check not only typical rotor blades properties but also composite structures thereby technology of manufacturing. One of the basic rotor blades test is to determine the breaking force, which, taking into account the safety factor, cannot exceed the maximum centrifugal force occurring on the rotor blades during flight. The first step of rotor blades tests was static test, which gave us answer about stiffness in plane of low stiffness and torsional stiffness, it’s very important properties related to vibrations. Another mechanical properties measured during tests were centre of gravity and mass moment of inertia in rotor blade. Next step was dynamic test – tracking and balancing verification. After static and dynamics, which has proper results – good balance and no vibration on the entire range of rotational speed – rotor blades can be use on fly object. After getting proper results of static and dynamic test next step was a specially prepared test, which defined the time needed for delamination to take place. During the delamination tests, the rotor blade was subjected to adequate loads that occur in horizontal flight. That kind of test is basis to determine service life of rotor blades.","PeriodicalId":165563,"journal":{"name":"Journal of KONES. Powertrain and Transport","volume":"75 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126192596","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Low speed wind tunnel test of the jet trainer model at high angles of attack","authors":"Kamil Smędra, Rafał Świerkot, K. Kubryński","doi":"10.5604/12314005.1217285","DOIUrl":"https://doi.org/10.5604/12314005.1217285","url":null,"abstract":"The article discusses the results of the wind tunnel test of the model of the highly manoeuvrable jet trainer, in the wide range of angles of attack. The main objective of this work was to modify the geometry in order to achieve the assumed properties (stability, control and dynamic behaviour in terms of high angles of attack), and possibly reliable verification of characteristics. In order to control the geometry of subsequent variants of aerodynamic models during the test, the full parametric representation of the CAD geometry was used (applying Siemens NX system) and the modular construction of the models. This enables to change the various components (e.g. the front part of the fuselage, the air inlets, wings, tail, strakes etc.). The wind tunnel models were produced using 3D printers, based on the FDM (Fused Deposition Modelling) method. This allows for relatively fast model prototyping while maintaining full control of geometry and very low cost. Studies were conducted using several models differing in geometry as well (in order to determine the effect of blockage) model scale implementation. Studies carried out in a low speed wind tunnel using an internal balance mounted on bent sting (to enable measurement at high angles of attack). The measurements were carried out in the range of angles of attack -2° to 56° and slip angles +/20°, with different deflections of leading edge flaps, trailing edge flaps, elevator, rudder and ailerons. The static aerodynamic characteristics of final version of the model indicates the correct properties in the entire range of flight conditions: the ability to ensure a longitudinal balance with appropriate longitudinal moments necessary to control (reduce the angle of attack), the correct dynamic characteristics at high angles of attack (no pro-spin trend) and the ability to lateral and directional control. Some interesting novelty that will be presented in the paper is a preliminary evaluation of the dynamic properties of the aircraft at high angles of attack, carried out on the model in the tunnel, providing three degrees of freedom (rotation about all three axes).","PeriodicalId":165563,"journal":{"name":"Journal of KONES. Powertrain and Transport","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125906445","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Numerical and experimental investigation of methane-oxygen detonation in a 9 m long tube","authors":"Konrad Malik, M. Żbikowski, A. Teodorczyk, P. Lesiak","doi":"10.5604/12314005.1217241","DOIUrl":"https://doi.org/10.5604/12314005.1217241","url":null,"abstract":"Numerical investigation of methane-oxygen detonation parameters was conducted with an OpenFoam code. Custom solver ddtFoam made especially for detonation problems was made use of. It uses the HLLC scheme to resolve the discontinuities and the subgridscale model to improve results on coarse meshes. Combustion model is based on progress variable equation, which contains two source terms. The first is the deflagrative source term and is modelled using the Weller correlation. The second is the detonative source term and it accounts for autoignition effects. Range of analysed gaseous mixture compositions was 20, 33 and 40% of methane in oxygen. The 2D calculation geometry was a 9 m long pipe with diameter 0.17 m. The mesh consisted of 382 500 hexahedral cells with the dimensions of 2x2 mm. Experimental results such as pressure profiles and detonation velocities are presented. Simulations were performed using LES turbulence model (k-equation-eddy-viscosity model) and compared with experimental data. Various dynamic parameters, like for example reaction lengths for methane-oxygen detonations, are estimated from the steady ZND analyses conducted in Cantera and SDToolbox libraries and based on GRI 3.0 kinetic mechanism of methane combustion. These lengths were then used in empirical formulas to obtain the characteristic cell sizes and assessed against experimental data.","PeriodicalId":165563,"journal":{"name":"Journal of KONES. Powertrain and Transport","volume":"39 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124660321","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"RESULTS OF LAPPING PROCESS EXECUTED IN ELEVATED TEMPERATURE","authors":"J. Molenda, A. Charchalis","doi":"10.5604/12314005.1217446","DOIUrl":"https://doi.org/10.5604/12314005.1217446","url":null,"abstract":"Lapping is used in the production of components of the highest quality in terms of form finish accuracy and surface integrity. A number of precision manufacturing applications use lapping process as a critical technology to achieve thickness tolerance and surface quality specification. Because of required parts accuracy tool flatness is the key to the successful machining. To avoid its excessive thermal expansion, plate temperature research was taken. This paper goal was to check the influence of temperature of executory system elements on lapping process results. In earlier work, authors investigated the dependence between time and the temperature of executory system elements. Tests showed that after five hours of machine working temperature stabilizes and slightly fluctuated around a certain value. Thus, this work concerns lapping results in this elevated temperature. Research was proceed during Al2O3 elements lapping. It was realised with use of ABRALAP 380 lapping machine. The lapping machine executory system consisted of three working conditioning rings. Executory system elements temperature was measured remotely by infrared camera Thermo Gear G100. Elements machining was started after 10, 140, and 270 minutes of machine working time. Studies showed that machine executory system elements temperature affected only the Ra parameter, which is higher for surfaces, which were processed starting from 270th minute of machine working time.","PeriodicalId":165563,"journal":{"name":"Journal of KONES. Powertrain and Transport","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129872575","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"The new data exchange facilities with CAN-FD","authors":"M. Śmieja, K. Duda, J. Mamala","doi":"10.5604/12314005.1217297","DOIUrl":"https://doi.org/10.5604/12314005.1217297","url":null,"abstract":"The modern vehicles demand more and more data exchange to coordinate, control and monitor functions of on board system. The variety of networks applied in these systems is featured mainly by the bandwidth and time determinism. The development electronic information and network sciences find its reflection in the new and new automotive implementations. The last significant step towards the increase the throughout put of the on board network channels are works on CAN-FD. CAN is now the most common network present on board. It helps to manage the maintenance with the numerous subassemblies of the modern car. Next to the many features making CAN so useful and popular, there is a bandwidth limitation, which slows down further implementation of it. The new CAN-FD specification adds new properties that extend the possibilities of CAN as automotive network protocol. These are: different speed transmission in the arbitration phase and in the data phase during the message transmission as well as the extending the maximum size of data filed of the frame from 8 (CAN) to 64 (CAN-FD). In the paper there have been presented the limitations of existing CAN protocol usage, the explanation of the basics of the arbitration mechanisms and the response of the scientist and engineers to cope with it, as well as the formal result outlined in the CAN-FD","PeriodicalId":165563,"journal":{"name":"Journal of KONES. Powertrain and Transport","volume":"69 ","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120887012","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"PREDICTION OF AIRCRAFT LOST OF CONTROL IN THE FLIGHT BY CONTINUATION, BIFURCATION, AND CATASTROPHE THEORY METHODS","authors":"K. Sibilski, M. Kowalski","doi":"10.5604/12314005.1217280","DOIUrl":"https://doi.org/10.5604/12314005.1217280","url":null,"abstract":"Lost of Control in Flight (LOC-I) is ordinarily associated with flight outside of the normal flight envelope, with nonlinear behaviours, and with an inability of the pilot to control the aircraft. These results provide a means for analysing accident data to establish whether or not the accident should be classified as LOC-I. Moreover, they help identify when the initial upset occurred, and when control was lost. The analysis also suggests which variables were involved, thereby providing clues as to the underlying mechanism of upset. However, it does not provide direct links to the flight mechanics of the aircraft, so it cannot be used proactively to identify weaknesses or limitations in the aircraft or its control systems. Moreover, it does not explain how departures from controlled flight occur. The complexity of the disaster aetiology stems from both the scale and coupling of the systems (not only the physical aircraft systems but also the organizational systems that support the operation). This complexity creates a pattern of disaster that evolves or it is precipitated through a series of several small failures. The cusp catastrophe model facilitates the mapping of Reason’s latent failure model, providing a descriptive and predictive illustration of the emergence of latent conditions under the trigger of situational factors. The risk of an accident increases as the situational and systematic factors combine to create an inherent instability resulting in the catastrophic event","PeriodicalId":165563,"journal":{"name":"Journal of KONES. Powertrain and Transport","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121840916","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"The rig stand for testing integrated rocket ramjet engine","authors":"Artur Rowiński","doi":"10.5604/12314005.1217261","DOIUrl":"https://doi.org/10.5604/12314005.1217261","url":null,"abstract":"Integrated rocket ramjet engine is adapted to aircraft propulsion and supersonic missiles moving at the speed of 8 Ma. The engine’s construction enables flexibly benefit from both types of drive depending on the conditions of the flight. The ejector mode of operation applicable to Mach numbers smaller than 2 cooperate with the rocket engine positioned in flow channel. Secondary air stream enters the engine through the convergent divergent nozzle and supplies the air to the ejector and booster. Rocket engine using the ejector effect would be used only in the phase of accelerating an object to the supersonic speed and then the drive would gradually shift to ramjet. The range of speed for the ramjet mode is 2-6 Mach. The prototype of the rocket ramjet engine of over 1300 N is equipped with annular combustion chamber in which phenomena of rotating detonation as well as the aero spike nozzle were used. Both the test stand as well as the engine is adapted to trials suitable to the conditions of a flight at the speed of 1.4 Ma. The test stand is powered by compress air coming from the instalment set up in the earth test bed and by oxygen and methane at a pressure of 10 bar. The rig is designed for functional tests of prototype, areas of the creation of mixture of firearms used to measuring and the range of stable functioning of the engine in the ramjet mode. Moreover, the measured parameters in gas supply installations as well as the temperature and pressure in the combustion chamber and thrust created by integrated rocket ramjet engine are measured.","PeriodicalId":165563,"journal":{"name":"Journal of KONES. Powertrain and Transport","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130427882","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Influence of dimensional proportions of cylindrical explosive on resulting blast wave","authors":"R. Panowicz, Michał Trypolin, M. Konarzewski","doi":"10.5604/12314005.1217252","DOIUrl":"https://doi.org/10.5604/12314005.1217252","url":null,"abstract":"Explosives are broadly used today in many applications, both civilian and military. Many experiments involving explosives use either ball or cylinder charges. However, there can be raised a question whether an exact shape influences the resulting blast wave, and, additionally, if the length to diameter ratio of the cylinder influences the wave. To answer the question, numerical analysis was conducted. A 3D model of the charge was constructed in LS-Prepost software and calculated with use of an explicit FEM method in LS-DYNA software. To determine the change of character of the blast wave, the dimensions of the charge change, whereas the mass and distance from the centre of the charge are constant. Several length to diameter ratios was tested, starting from 0.25, to 2, in 0.25 increments. Two explosives, HMX and TNT, were used. As expected, the resulting Blast wave was different in each case, with 100% difference in pressure values between 0.25 and 2 L to D ratios, especially along the length axis of the cylinder. The results show that the exact diameters of the charges need to be taken into consideration while determining a type of charge to be used as well as determining the goal to be achieved during a particular conducted experiment.","PeriodicalId":165563,"journal":{"name":"Journal of KONES. Powertrain and Transport","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127977925","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"ASSESSMENT OF THE DEGREE OF DETERIORATION OF TRUNK PISTON ENGINE OIL USED IN THE ENGINE 6AL20/24","authors":"M. Malinowska","doi":"10.5604/12314005.1217242","DOIUrl":"https://doi.org/10.5604/12314005.1217242","url":null,"abstract":"The problem of engine oils and lubrication systems of marine diesel engines is an important issue in operation of engines. When considering the problems of exploitation of machines and devices, the lubricating oils are treated as one of the part of engine design, which should perform the functions: control friction between load-bearing surfaces, limit the temperature by carrying away heat from fluid fraction and fuel combustion, reduce corrosion etc. – general protect engine parts. The knowledge of the properties lubricating oils allows for proper selection them for the engine and correct use. During operation, the oil subjects' irreversible process of oil deterioration and it cannot properly fulfil their functions. Therefore important are frequent periodic checks of oil, it means monitoring. The state of the lubricating oil can be characterized by parameters such as viscosity, total base number, acid value, lubricating ability, flash point etc. Changes on these parameters of engine oil during exploitation, cause problems in fulfilling the primary functions of the oil. The target of the paper was the analysis and estimate of properties of trunk piston engine oil – Marinol RG 1240 after various times overwork on the sailing vessel “Dar Młodzieży” on the engine CegielskiSulzer 6AL20/24. The results were compared with the values critical and preventive limits and proposed several corrective actions for users the engine 6AL20/24.","PeriodicalId":165563,"journal":{"name":"Journal of KONES. Powertrain and Transport","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115460966","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}