Pub Date : 2003-12-01DOI: 10.1109/ICIASF.2003.1274853
P. Bueno, Y. Hou, N. Clemens, D. Dolling
A wide-field PIV system was used to study the effects of upstream pulsed mass injection on a turbulent boundary layer/shock wave interaction generated by a 20/spl deg/ compression ramp in a Mach 2 flow. The mass injection was provided by three discrete pulsed underexpanded jets, which were located 60 mm upstream of the compression ramp and had a pulse-duration of 5 ms. The wide-field PIV was achieved by using four megapixel cameras to enable a field of view that spanned the upstream unperturbed boundary layer, injection jets, intermittent and separation regions, and compression ramp face. Phase-locked PIV measurements were taken with no injection and with a 4 ms delay with respect to the injection trigger signal. The phase-average PIV measurements show that the pulsed jets have a substantial impact on the upstream boundary layer and the structure of the interaction. For example, the PIV shows the bow shock upstream of the injectors and the expansion region downstream of them. Pulsed injection was found to move the interaction downstream about one quarter of a boundary layer thickness. This result implies the injectors act like vortex generators that introduce high momentum fluid into the upstream boundary layer and thus make it more resistant to separation.
{"title":"A PIV study on the effect of pulsed-jet injection upstream of a Mach 2 shock wave/turbulent boundary layer interaction","authors":"P. Bueno, Y. Hou, N. Clemens, D. Dolling","doi":"10.1109/ICIASF.2003.1274853","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274853","url":null,"abstract":"A wide-field PIV system was used to study the effects of upstream pulsed mass injection on a turbulent boundary layer/shock wave interaction generated by a 20/spl deg/ compression ramp in a Mach 2 flow. The mass injection was provided by three discrete pulsed underexpanded jets, which were located 60 mm upstream of the compression ramp and had a pulse-duration of 5 ms. The wide-field PIV was achieved by using four megapixel cameras to enable a field of view that spanned the upstream unperturbed boundary layer, injection jets, intermittent and separation regions, and compression ramp face. Phase-locked PIV measurements were taken with no injection and with a 4 ms delay with respect to the injection trigger signal. The phase-average PIV measurements show that the pulsed jets have a substantial impact on the upstream boundary layer and the structure of the interaction. For example, the PIV shows the bow shock upstream of the injectors and the expansion region downstream of them. Pulsed injection was found to move the interaction downstream about one quarter of a boundary layer thickness. This result implies the injectors act like vortex generators that introduce high momentum fluid into the upstream boundary layer and thus make it more resistant to separation.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"197 10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124717176","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}
Pub Date : 2003-12-01DOI: 10.1109/ICIASF.2003.1274847
T. Niimi, H. Mori, K. Okabe, Y. Masai, M. Taniguchi
Aerospike nozzles have been expected as a candidate for an engine of reusable Space Shuttles to respond to growing demand for rocket-launching at the lower cost. In this study, the flow field structures in any cross sections around the linear-type aerospike nozzle are visualized and analyzed, using laser induced fluorescence (LIF) of NO seeded in the carrier gas N/sub 2/. Since the flow field structure is affected mainly by the pressure ratio (P/sub s//P/sub a/), the linear-type aerospike nozzle is set inside the vacuum chamber to carry out the experiments in the wide range of pressure ratios from 75 to 250. Flow fields are visualized in several cross-sections, demonstrating the complicated three-dimensional flow field structures. Pressure sensitive paint (PSP) of PtTFPP bound by poly(TMSP) is also applied successfully to measurement of the complicated pressure distribution on the spike surface.
{"title":"Analyses of flow field structures around linear-type aerospike nozzles using LIF and PSP","authors":"T. Niimi, H. Mori, K. Okabe, Y. Masai, M. Taniguchi","doi":"10.1109/ICIASF.2003.1274847","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274847","url":null,"abstract":"Aerospike nozzles have been expected as a candidate for an engine of reusable Space Shuttles to respond to growing demand for rocket-launching at the lower cost. In this study, the flow field structures in any cross sections around the linear-type aerospike nozzle are visualized and analyzed, using laser induced fluorescence (LIF) of NO seeded in the carrier gas N/sub 2/. Since the flow field structure is affected mainly by the pressure ratio (P/sub s//P/sub a/), the linear-type aerospike nozzle is set inside the vacuum chamber to carry out the experiments in the wide range of pressure ratios from 75 to 250. Flow fields are visualized in several cross-sections, demonstrating the complicated three-dimensional flow field structures. Pressure sensitive paint (PSP) of PtTFPP bound by poly(TMSP) is also applied successfully to measurement of the complicated pressure distribution on the spike surface.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132256571","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}
Pub Date : 2003-12-01DOI: 10.1109/ICIASF.2003.1274881
C. Dankert, H. Mori
In the DLR-high vacuum plume test facility STG, experiments have been performed to study the expansion of supersonic plumes into vacuum with N/sub 2/ as a test gas. The measured values were the Pitot pressure, the molecular number flux, the rotational temperature and the density. The last two quantities were measured by the 2+2 REMPI-technique with a stimulation wavelength of 283-284 nm (REMPI = resonance enhanced multi photon ionization). This method is also suitable to measure the absolute flow velocity by the ion time-of-flight (TOF) method. The apparatus for the combination of the REMPI and TOF technique is similar to that for the TOF experiments using electron beam bombardment, but a focused laser beam is used instead of an electron beam. The results of such laser measurements in highly rarefied plumes for several stagnation temperatures are presented with nitrogen as test gas. On-axis results fit well with the theoretical limiting velocity for perfect expansion; angular velocity profiles off-axis are discussed and compared to theory. This study is focused on the experimental procedure to measure the flow velocity of N/sub 2/ in rarefied plumes expanding from supersonic nozzles into vacuum.
{"title":"Flow velocity measurements in nitrogen plumes stimulated by REMPI","authors":"C. Dankert, H. Mori","doi":"10.1109/ICIASF.2003.1274881","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274881","url":null,"abstract":"In the DLR-high vacuum plume test facility STG, experiments have been performed to study the expansion of supersonic plumes into vacuum with N/sub 2/ as a test gas. The measured values were the Pitot pressure, the molecular number flux, the rotational temperature and the density. The last two quantities were measured by the 2+2 REMPI-technique with a stimulation wavelength of 283-284 nm (REMPI = resonance enhanced multi photon ionization). This method is also suitable to measure the absolute flow velocity by the ion time-of-flight (TOF) method. The apparatus for the combination of the REMPI and TOF technique is similar to that for the TOF experiments using electron beam bombardment, but a focused laser beam is used instead of an electron beam. The results of such laser measurements in highly rarefied plumes for several stagnation temperatures are presented with nitrogen as test gas. On-axis results fit well with the theoretical limiting velocity for perfect expansion; angular velocity profiles off-axis are discussed and compared to theory. This study is focused on the experimental procedure to measure the flow velocity of N/sub 2/ in rarefied plumes expanding from supersonic nozzles into vacuum.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"68 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114504917","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}
Pub Date : 2003-12-01DOI: 10.1109/ICIASF.2003.1274885
K. Shirai
A new optical measurement method for local wall shear stress is proposed. The method is an extension of laser Doppler technique. It has a possibility of detecting the both magnitude and angle of local wall shear stress. The principle was investigated for Doppler frequency and measurement volume. The Doppler frequency changes in a Doppler burst signal. The frequency variation depends on the magnitude and angle of local wall shear stress and the spanwise offset of scattering particle path. A signal processing technique is proposed to detect the magnitude and the angle of local wall shear stress. The technique consists of detecting Doppler frequency variation by time-frequency analysis and nonlinear least squares fit. A simulation was conducted to investigate the performance of the method. Simulated Doppler signals were generated by using the instantaneous velocity data of a fluid-flow simulation result. The generated signals with different noise levels were processed and the effect of the noise level was investigated. The local wall shear stress was estimated with moderate accuracy but its angle was not estimated with good accuracy. A further investigation is required to improve the accuracy of measurement for the method.
{"title":"A new optical measurement method for local wall shear stress and its signal processing techniques","authors":"K. Shirai","doi":"10.1109/ICIASF.2003.1274885","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274885","url":null,"abstract":"A new optical measurement method for local wall shear stress is proposed. The method is an extension of laser Doppler technique. It has a possibility of detecting the both magnitude and angle of local wall shear stress. The principle was investigated for Doppler frequency and measurement volume. The Doppler frequency changes in a Doppler burst signal. The frequency variation depends on the magnitude and angle of local wall shear stress and the spanwise offset of scattering particle path. A signal processing technique is proposed to detect the magnitude and the angle of local wall shear stress. The technique consists of detecting Doppler frequency variation by time-frequency analysis and nonlinear least squares fit. A simulation was conducted to investigate the performance of the method. Simulated Doppler signals were generated by using the instantaneous velocity data of a fluid-flow simulation result. The generated signals with different noise levels were processed and the effect of the noise level was investigated. The local wall shear stress was estimated with moderate accuracy but its angle was not estimated with good accuracy. A further investigation is required to improve the accuracy of measurement for the method.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125167566","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}
Pub Date : 2003-08-25DOI: 10.1109/ICIASF.2003.1274858
V. Simonov, A. Kuzin
Described are results of creation and application of an optoelectronic system, which is based on a principle of oscillation measurements using optical image of the object. Presented are results of mathematical modeling of the system's main parts functioning. Also presented are results of application for vibration testing of aviation engine blades; for rotors' balancing; for vibration testing of aviation turbine coolers; for vibration measurements of elements of printed circuit boards in electronic devices; for various parts of constructions; for acoustic loudspeakers; for optically-active objects (which emit light themselves). Also discussed are results and possibilities of application in automotive industry; for distant measurements (hundreds of meters); and for some medical applications. Discussed are investigations of errors compensation. These errors take place because various objects have different size and shape, and they emit or reflect different amount of light. Without using of compensation the total error would be about hundreds of percent. So all errors were analyzed, classified, mathematically modeled and there were created special loops for errors compensation. As a result total error of measurement was less that 15% for all conditions of practical usage. During design and construction it was provided that the system can be applied for indoor and outdoor conditions. Special climatic testing has confirmed that. The system incorporates build-in block for self-testing.
{"title":"Optoelectronic vibration measurement system","authors":"V. Simonov, A. Kuzin","doi":"10.1109/ICIASF.2003.1274858","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274858","url":null,"abstract":"Described are results of creation and application of an optoelectronic system, which is based on a principle of oscillation measurements using optical image of the object. Presented are results of mathematical modeling of the system's main parts functioning. Also presented are results of application for vibration testing of aviation engine blades; for rotors' balancing; for vibration testing of aviation turbine coolers; for vibration measurements of elements of printed circuit boards in electronic devices; for various parts of constructions; for acoustic loudspeakers; for optically-active objects (which emit light themselves). Also discussed are results and possibilities of application in automotive industry; for distant measurements (hundreds of meters); and for some medical applications. Discussed are investigations of errors compensation. These errors take place because various objects have different size and shape, and they emit or reflect different amount of light. Without using of compensation the total error would be about hundreds of percent. So all errors were analyzed, classified, mathematically modeled and there were created special loops for errors compensation. As a result total error of measurement was less that 15% for all conditions of practical usage. During design and construction it was provided that the system can be applied for indoor and outdoor conditions. Special climatic testing has confirmed that. The system incorporates build-in block for self-testing.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"262 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116240761","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}
Pub Date : 2003-08-25DOI: 10.1109/ICIASF.2003.1274861
P. Reulet, D. Nortershauser, P. Millan
Temperature measurements, for the direct identification of the surface heat flux, are not always possible considering an aggressive environment or an inaccessible zone. That is why an inverse method has been developed: the direct problem with the unknown boundary condition (wall heat flux) is solved by adding an observation equation given by temperature measurements on the opposite face of the wall. In order to estimate spatiotemporal variations of the surface heat flux, an inverse non linear three-dimensional unsteady model has been developed. The resolution is based on the minimisation of a function representing the sum of the differences between the observations (measured surface temperatures) and the calculated temperature at the same position. A compression method using DCT is used to filter the temperature measurements and reduce the number of heat flux components to be estimated. First a numerical validation of the inverse model has been conducted: a flat plate submitted to a specified spatiotemporal heat flux evolution. Then two validation experiments have been developed: impact of a moving laser beam on a flat steel plate and flame-wall interaction. The estimation of high resolution unsteady heat flux cartographies have been demonstrated.
{"title":"Inverse method using infrared thermography for surface temperature and heat flux measurements","authors":"P. Reulet, D. Nortershauser, P. Millan","doi":"10.1109/ICIASF.2003.1274861","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274861","url":null,"abstract":"Temperature measurements, for the direct identification of the surface heat flux, are not always possible considering an aggressive environment or an inaccessible zone. That is why an inverse method has been developed: the direct problem with the unknown boundary condition (wall heat flux) is solved by adding an observation equation given by temperature measurements on the opposite face of the wall. In order to estimate spatiotemporal variations of the surface heat flux, an inverse non linear three-dimensional unsteady model has been developed. The resolution is based on the minimisation of a function representing the sum of the differences between the observations (measured surface temperatures) and the calculated temperature at the same position. A compression method using DCT is used to filter the temperature measurements and reduce the number of heat flux components to be estimated. First a numerical validation of the inverse model has been conducted: a flat plate submitted to a specified spatiotemporal heat flux evolution. Then two validation experiments have been developed: impact of a moving laser beam on a flat steel plate and flame-wall interaction. The estimation of high resolution unsteady heat flux cartographies have been demonstrated.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129699172","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}
Pub Date : 2003-08-25DOI: 10.1109/ICIASF.2003.1274880
D. Klimenko, W. Clauss, W. Mayer, M. Oschwald, J.J. Smith
Quantitative and qualitative optical diagnostics have been successfully applied within a liquid propellant rocket engine with optical access at representative, supercritical operating conditions. A series of unique optical techniques have been implemented in an attempt to characterise the liquid oxygen (LOX) and hydrogen (H/sub 2/) spray flames prevalent in today's heavy launch vehicle engines. A windowed, high-pressure combustion chamber has been developed and constructed specifically for the purpose of the application of optical diagnostics. Precise control and regulation of operational and injection conditions is important to ensure consistent, stable operation of the combustor. A variety of parameters have been carefully monitored with the aid of an array of measurement instrumentation including, temperatures, pressures, vibrations and massflow rates.
{"title":"Optical diagnostics and instrumentation for supercritical combustion studies in a LOX/H/sub 2/ rocket engine combustion chamber","authors":"D. Klimenko, W. Clauss, W. Mayer, M. Oschwald, J.J. Smith","doi":"10.1109/ICIASF.2003.1274880","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274880","url":null,"abstract":"Quantitative and qualitative optical diagnostics have been successfully applied within a liquid propellant rocket engine with optical access at representative, supercritical operating conditions. A series of unique optical techniques have been implemented in an attempt to characterise the liquid oxygen (LOX) and hydrogen (H/sub 2/) spray flames prevalent in today's heavy launch vehicle engines. A windowed, high-pressure combustion chamber has been developed and constructed specifically for the purpose of the application of optical diagnostics. Precise control and regulation of operational and injection conditions is important to ensure consistent, stable operation of the combustor. A variety of parameters have been carefully monitored with the aid of an array of measurement instrumentation including, temperatures, pressures, vibrations and massflow rates.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"44 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130225762","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}
Pub Date : 2003-08-25DOI: 10.1109/ICIASF.2003.1274857
Y. Sant
A new method has been developed to correct the effects of model deformation on PSP images. This method is based upon grid tracking instead of marker tracking. The grid is stretched according to a deformation law and deformation parameters. The deformation law is designed by using mechanical and aerodynamic knowledge about the model behavior. The parameters are identified by using the same markers that are used for usual PSP applications. The identification algorithm is an extended version of the algorithm that identifies the relative position of the camera and the model. The method has been applied successfully on images obtained in a pressurized wind tunnel at Onera Modane. The achieved accuracy is 0.1 pixel, which is considered as a very good value. The method enables to identify not only deformation parameters but also motion parameters. As a result, the method can be used to measure model deformation and motion, which would be very useful for tests in research and industrial wind tunnels. The method can be extended to handle simultaneously several cameras, thus improving the accuracy.
{"title":"A model deformation method applied to PSP measurements","authors":"Y. Sant","doi":"10.1109/ICIASF.2003.1274857","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274857","url":null,"abstract":"A new method has been developed to correct the effects of model deformation on PSP images. This method is based upon grid tracking instead of marker tracking. The grid is stretched according to a deformation law and deformation parameters. The deformation law is designed by using mechanical and aerodynamic knowledge about the model behavior. The parameters are identified by using the same markers that are used for usual PSP applications. The identification algorithm is an extended version of the algorithm that identifies the relative position of the camera and the model. The method has been applied successfully on images obtained in a pressurized wind tunnel at Onera Modane. The achieved accuracy is 0.1 pixel, which is considered as a very good value. The method enables to identify not only deformation parameters but also motion parameters. As a result, the method can be used to measure model deformation and motion, which would be very useful for tests in research and industrial wind tunnels. The method can be extended to handle simultaneously several cameras, thus improving the accuracy.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"48 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132610835","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}
Pub Date : 2003-08-25DOI: 10.1109/ICIASF.2003.1274887
H. Mori, T. Niimi, M. Yoshida, M. Kondo, Y. Oshima, M. Hirako
The PSP technique has the capability to be applied to high Knudsen number flows, such as low density gas flows, micro-flows, and so on. In this study, fundamental properties of PSPs such as sensitivity to pressure are examined especially in the range of pressure below 150 Pa (about 1 Torr), to select the most suitable PSP for the low pressure range. One of the PSP is Bath-Ru adsorbed directly on anodized aluminum, and the other PSPs are composed of porphyrin complexes bound by glassy polymer poly(TMSP). As an application of PSP to low density gas flows, we measure a pressure distribution on a surface of an aluminum plate interacting with a low density supersonic free jet. The clear two-dimensional pressure distribution was obtained by using PtTFPP/poly(TMSP), showing the feasibility of quantitative pressure measurement using the PSP.
{"title":"Application of PSP in low pressure regime","authors":"H. Mori, T. Niimi, M. Yoshida, M. Kondo, Y. Oshima, M. Hirako","doi":"10.1109/ICIASF.2003.1274887","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274887","url":null,"abstract":"The PSP technique has the capability to be applied to high Knudsen number flows, such as low density gas flows, micro-flows, and so on. In this study, fundamental properties of PSPs such as sensitivity to pressure are examined especially in the range of pressure below 150 Pa (about 1 Torr), to select the most suitable PSP for the low pressure range. One of the PSP is Bath-Ru adsorbed directly on anodized aluminum, and the other PSPs are composed of porphyrin complexes bound by glassy polymer poly(TMSP). As an application of PSP to low density gas flows, we measure a pressure distribution on a surface of an aluminum plate interacting with a low density supersonic free jet. The clear two-dimensional pressure distribution was obtained by using PtTFPP/poly(TMSP), showing the feasibility of quantitative pressure measurement using the PSP.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"16 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124171938","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}
Pub Date : 2003-08-25DOI: 10.1109/ICIASF.2003.1274860
V. Simonov, A. Kuzin
Described are results of creation and application of an optoelectronic system, intended for measurements of field of vibrations of objects with complicated surface structure. Principle of vibration measurements is based on displacement measurements of an optical image of the object. Discussed are investigations of errors compensation, which take place because of variations of objects' size and shape, as objects usually emit or reflect different amount of light. Without using of compensation the total error would be about hundreds of percent. This is why all kinds of measurement errors were analyzed, classified, mathematically modeled and there were created special loops for errors compensation. As a result total error of measurement was less that 15% for all conditions of practical usage. In this paper presented also are results of implementation of half-automatical algorithm for adaptation to different kinds of objects during scanning of the object's surface. Discussed are principles of classification of various types of "light functions", specific for various types of objects.
{"title":"Intelligent system for optoelectronic surface vibration testing","authors":"V. Simonov, A. Kuzin","doi":"10.1109/ICIASF.2003.1274860","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274860","url":null,"abstract":"Described are results of creation and application of an optoelectronic system, intended for measurements of field of vibrations of objects with complicated surface structure. Principle of vibration measurements is based on displacement measurements of an optical image of the object. Discussed are investigations of errors compensation, which take place because of variations of objects' size and shape, as objects usually emit or reflect different amount of light. Without using of compensation the total error would be about hundreds of percent. This is why all kinds of measurement errors were analyzed, classified, mathematically modeled and there were created special loops for errors compensation. As a result total error of measurement was less that 15% for all conditions of practical usage. In this paper presented also are results of implementation of half-automatical algorithm for adaptation to different kinds of objects during scanning of the object's surface. Discussed are principles of classification of various types of \"light functions\", specific for various types of objects.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129464375","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}
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