Pub Date : 2021-06-23DOI: 10.1109/MetroAeroSpace51421.2021.9511760
G. Cataldi, M. Gemignani, S. Marcuccio
Sounding balloons have proven to be a very effective low-cost method to bring scientific and commercial payloads to the near-space environment. In the frame of our ongoing effort towards the development of a small stratospheric platform with autonomous flying capabilities, we have undertaken the design and manufacture of a flight experiment to verify the possibility to perform onboard attitude determination using the solar cell power output measurements to complement the inertial sensor. The system is based on six low-cost terrestrial solar cells placed on the sides of a box-shaped gondola, lifted to about 34 km altitude by a weather balloon. We describe the system architecture, the results of the first experimental flight and the post-landing attitude reconstruction.
{"title":"Validation Flight Experiment for a Sounding Balloon Photovoltaic-based Attitude Determination System","authors":"G. Cataldi, M. Gemignani, S. Marcuccio","doi":"10.1109/MetroAeroSpace51421.2021.9511760","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511760","url":null,"abstract":"Sounding balloons have proven to be a very effective low-cost method to bring scientific and commercial payloads to the near-space environment. In the frame of our ongoing effort towards the development of a small stratospheric platform with autonomous flying capabilities, we have undertaken the design and manufacture of a flight experiment to verify the possibility to perform onboard attitude determination using the solar cell power output measurements to complement the inertial sensor. The system is based on six low-cost terrestrial solar cells placed on the sides of a box-shaped gondola, lifted to about 34 km altitude by a weather balloon. We describe the system architecture, the results of the first experimental flight and the post-landing attitude reconstruction.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"371 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131645613","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 : 2021-06-23DOI: 10.1109/MetroAeroSpace51421.2021.9511664
Francesco De Giudici, Federico Toson, A. Piva, Pietro Artusi, L. Olivieri, C. Bettanini
Avalanche rescue operations require quick localization of buried people. Organized rescue intervention is often not fast enough, since professional rescuers are not directly present in the avalanche area. Therefore, companion rescue remains the most effective option for rapid response, especially in case of employment of avalanche transceivers. In this context, the AVERLA project is developing avalanche localization instrumentation for small drones, to provide winter mountain recreationists, athletes and rescue teams with a fast and accurate system to improve the buried search. In this paper, a custom radiofrequency localization system, tuned on the avalanche transceivers transmission frequency, is described and its performance is assessed. Last, the integration of the instrument on an off-the-shelf drone, as baseline for further miniaturization, is presented.
{"title":"Design and testing of an autonomous ARTVA detector for small drones","authors":"Francesco De Giudici, Federico Toson, A. Piva, Pietro Artusi, L. Olivieri, C. Bettanini","doi":"10.1109/MetroAeroSpace51421.2021.9511664","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511664","url":null,"abstract":"Avalanche rescue operations require quick localization of buried people. Organized rescue intervention is often not fast enough, since professional rescuers are not directly present in the avalanche area. Therefore, companion rescue remains the most effective option for rapid response, especially in case of employment of avalanche transceivers. In this context, the AVERLA project is developing avalanche localization instrumentation for small drones, to provide winter mountain recreationists, athletes and rescue teams with a fast and accurate system to improve the buried search. In this paper, a custom radiofrequency localization system, tuned on the avalanche transceivers transmission frequency, is described and its performance is assessed. Last, the integration of the instrument on an off-the-shelf drone, as baseline for further miniaturization, is presented.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134178207","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 : 2021-06-23DOI: 10.1109/MetroAeroSpace51421.2021.9511711
J. Pieniążek, Piotr Cieciński
The propeller propulsion is mainly used kind of propulsion in small unmanned flying vehicles. In this propulsion an engine, in the most cases electric motor, powers the propeller which produces thrust. The efficiency of the use of engine energy by propeller depends on the proper propeller design or selection taking into account operating conditions. The whole propulsion characteristics are important for the numerical model development and advanced control systems. The optimized propeller increases the flight time of the particular vehicle. The test stand and testing method are main subjects of the paper. The tests of the motor with propeller or propeller only using some motor needs measurement devices of important variables, which are specified by theoretical analysis. Besides the measured system structure, main parts and user interface the sample results of raw data, computed propeller parameters, and pressure distribution along propeller blade are presented. The last data gives possibility for further analysis of the influence of a propeller geometry on propulsion parameters.
{"title":"Measurement system for small propeller propulsion","authors":"J. Pieniążek, Piotr Cieciński","doi":"10.1109/MetroAeroSpace51421.2021.9511711","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511711","url":null,"abstract":"The propeller propulsion is mainly used kind of propulsion in small unmanned flying vehicles. In this propulsion an engine, in the most cases electric motor, powers the propeller which produces thrust. The efficiency of the use of engine energy by propeller depends on the proper propeller design or selection taking into account operating conditions. The whole propulsion characteristics are important for the numerical model development and advanced control systems. The optimized propeller increases the flight time of the particular vehicle. The test stand and testing method are main subjects of the paper. The tests of the motor with propeller or propeller only using some motor needs measurement devices of important variables, which are specified by theoretical analysis. Besides the measured system structure, main parts and user interface the sample results of raw data, computed propeller parameters, and pressure distribution along propeller blade are presented. The last data gives possibility for further analysis of the influence of a propeller geometry on propulsion parameters.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"14 3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132123537","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 : 2021-06-23DOI: 10.1109/MetroAeroSpace51421.2021.9511733
M. Cagnetti, M. Leccisi, F. Leccese
WSNs (Wireless sensor Networks) are a very robust and flexible structure which can be adapted to each scenario. The choice of the correct routing algorithm is a central point of a WSN, so a comparison between two routing algorithms, for an optical sensor network based on Lidar sensors, has been studied to propose a low consumption structure to improve security in aerospace scenario.
{"title":"MPRR and Pegasis Routing Protocol comparison for Aerospace application","authors":"M. Cagnetti, M. Leccisi, F. Leccese","doi":"10.1109/MetroAeroSpace51421.2021.9511733","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511733","url":null,"abstract":"WSNs (Wireless sensor Networks) are a very robust and flexible structure which can be adapted to each scenario. The choice of the correct routing algorithm is a central point of a WSN, so a comparison between two routing algorithms, for an optical sensor network based on Lidar sensors, has been studied to propose a low consumption structure to improve security in aerospace scenario.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"20 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133691393","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 : 2021-06-23DOI: 10.1109/MetroAeroSpace51421.2021.9511725
R. Kliza, M. Wendeker, Jan Pytka, P. Kasprzak
The PROPWING denotes a novel propulsion concept for light airplanes, sailplanes and motorgliders, originally proposed by the authors. A number of small electric motors are installed in the wings and the propellers rotate throughout openings in the wing skin. The concept has been examined in a flight test campaign with the use of a scale model airplane and the system showed its functionality, what was reported in past works. This paper includes results of numerical simulations of the PROPWING system performed with the use of CFD-software.
{"title":"Simulation Researches of the PROPWING Airplane Propulsion System","authors":"R. Kliza, M. Wendeker, Jan Pytka, P. Kasprzak","doi":"10.1109/MetroAeroSpace51421.2021.9511725","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511725","url":null,"abstract":"The PROPWING denotes a novel propulsion concept for light airplanes, sailplanes and motorgliders, originally proposed by the authors. A number of small electric motors are installed in the wings and the propellers rotate throughout openings in the wing skin. The concept has been examined in a flight test campaign with the use of a scale model airplane and the system showed its functionality, what was reported in past works. This paper includes results of numerical simulations of the PROPWING system performed with the use of CFD-software.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"49 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126819085","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 : 2021-06-23DOI: 10.1109/MetroAeroSpace51421.2021.9511666
Emanuele Bedetti, Niccolò Picci, Andrea Gianfermo, Lorenzo Frezza, Diego Amadio, F. Curianò, Paolo Marzioli, A. Delfini
This paper reports the results from the thermal analysis, the steady state analysis and the thermal vacuum testing from the LEDSAT 1U CubeSat environmental qualification. While the thermal analysis has been computed to state the compliance of the CubeSat to the orbital environment, the steady state analysis has been performed to confirm the suitability of the selected thermal vacuum test levels for the survivability and operational ranges of the satellite components. The spacecraft system-level thermal vacuum testing has given satisfying results, with perfect functionalities of the spacecraft and with a successful qualification of the PFM for spaceflight.
{"title":"LEDSAT 1U CubeSat thermal analysis and steady state calibration for thermal-vacuum testing","authors":"Emanuele Bedetti, Niccolò Picci, Andrea Gianfermo, Lorenzo Frezza, Diego Amadio, F. Curianò, Paolo Marzioli, A. Delfini","doi":"10.1109/MetroAeroSpace51421.2021.9511666","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511666","url":null,"abstract":"This paper reports the results from the thermal analysis, the steady state analysis and the thermal vacuum testing from the LEDSAT 1U CubeSat environmental qualification. While the thermal analysis has been computed to state the compliance of the CubeSat to the orbital environment, the steady state analysis has been performed to confirm the suitability of the selected thermal vacuum test levels for the survivability and operational ranges of the satellite components. The spacecraft system-level thermal vacuum testing has given satisfying results, with perfect functionalities of the spacecraft and with a successful qualification of the PFM for spaceflight.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126949420","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 : 2021-06-23DOI: 10.1109/MetroAeroSpace51421.2021.9511698
Lei Peng, C. Ye, Yu Tao, Cai Long, Ming Li
Blade is a crucial part in steam turbine that chronically exposes to an atmosphere of high temperature, humidity, and pressure, which prone to cause fatigues in the structure. The root of a turbine blade is in undulation shape giving rise to the difficulties for inspection with conventional probes. This work proposes a novel flexible array eddy current testing (ECT) probe for the turbine blade root inspection. The proposed probe employs an in-plane differential scheme to reduce the common mode noise and increase the sensitivity to small defects. It works with three modes to improve the reliability of detecting defects in different orientations. It keeps the lift-off almost constant when scans the undulation shape structure, as the shape of the sensor array is flexible and is bended according to the sample surface. A prototype probe has been developed and tested by inspecting of a blade sample with artificial and nature defects. The probe can identify defect with dimensions length×wldth×depth=z.u mmxu.z mm×0.2 mm with various orientations and locations. The experiment results demonstrate that the probe has high sensitivity for defects at the root of turbine.
{"title":"Inspection of the undulation structure with an in-plane differential flexible array probe","authors":"Lei Peng, C. Ye, Yu Tao, Cai Long, Ming Li","doi":"10.1109/MetroAeroSpace51421.2021.9511698","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511698","url":null,"abstract":"Blade is a crucial part in steam turbine that chronically exposes to an atmosphere of high temperature, humidity, and pressure, which prone to cause fatigues in the structure. The root of a turbine blade is in undulation shape giving rise to the difficulties for inspection with conventional probes. This work proposes a novel flexible array eddy current testing (ECT) probe for the turbine blade root inspection. The proposed probe employs an in-plane differential scheme to reduce the common mode noise and increase the sensitivity to small defects. It works with three modes to improve the reliability of detecting defects in different orientations. It keeps the lift-off almost constant when scans the undulation shape structure, as the shape of the sensor array is flexible and is bended according to the sample surface. A prototype probe has been developed and tested by inspecting of a blade sample with artificial and nature defects. The probe can identify defect with dimensions length×wldth×depth=z.u mmxu.z mm×0.2 mm with various orientations and locations. The experiment results demonstrate that the probe has high sensitivity for defects at the root of turbine.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129639859","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 : 2021-06-23DOI: 10.1109/MetroAeroSpace51421.2021.9511692
I. Catapano, G. Ludeno, F. Soldovieri, T. Toullier, J. Dumoulin
Aerospace industry needs accurate coating thickness measurement as well as adhesion testing for preventing the corrosion of wear of metal substrates. In this frame, a constant attention is towards the potentialities offered by non-invasive sensing techniques and their technological advancements. This communication deals with THz surveys of painted steel samples. Specifically, we account for time of flight THz imaging, enhanced by a noise filtering procedure based on the Singular Value Decomposition of the data matrix. This analysis allowed for detecting paint coating layers and providing images of them and of the probed face of the steel substrate.
{"title":"TeraHertz inspections of painted steel samples","authors":"I. Catapano, G. Ludeno, F. Soldovieri, T. Toullier, J. Dumoulin","doi":"10.1109/MetroAeroSpace51421.2021.9511692","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511692","url":null,"abstract":"Aerospace industry needs accurate coating thickness measurement as well as adhesion testing for preventing the corrosion of wear of metal substrates. In this frame, a constant attention is towards the potentialities offered by non-invasive sensing techniques and their technological advancements. This communication deals with THz surveys of painted steel samples. Specifically, we account for time of flight THz imaging, enhanced by a noise filtering procedure based on the Singular Value Decomposition of the data matrix. This analysis allowed for detecting paint coating layers and providing images of them and of the probed face of the steel substrate.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"45 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122143705","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 : 2021-06-23DOI: 10.1109/MetroAeroSpace51421.2021.9511704
Alex Caon, Francesco Branz, A. Francesconi
Space missions that focus on On-Orbit-Servicing often involve the capture of a target satellite or space debris as a key event in the operational sequence. Space robots are among the most promising technologies to perform this task and mission architectures involving manipulators proved successful in orbit. Such mission scenarios are complex and imply a considerable risk of collision between the chaser and the target vehicles. For the sake of safety, it is of key importance to accurately position the capture interface w.r.t. the gripping point on the target, especially when relative distance is very low. During these phases, the guidance and control algorithms rely on pose measurements provided by navigation sensors that are generally able to reconstruct the target position and orientation only up to a certain distance between the camera and the target. To the purpose of having a complete control of the capture interface until contact, a new sensor based on a LED and a matrix of phototransistors has been developed. This paper describes the sensor and provides its preliminary characterization. A simple theoretical description of the sensor behavior is obtained from geometrical considerations, while experiments have been performed to measure the performances of the actual hardware implementation of the system.
{"title":"Characterization of a new positioning sensor for space capture","authors":"Alex Caon, Francesco Branz, A. Francesconi","doi":"10.1109/MetroAeroSpace51421.2021.9511704","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511704","url":null,"abstract":"Space missions that focus on On-Orbit-Servicing often involve the capture of a target satellite or space debris as a key event in the operational sequence. Space robots are among the most promising technologies to perform this task and mission architectures involving manipulators proved successful in orbit. Such mission scenarios are complex and imply a considerable risk of collision between the chaser and the target vehicles. For the sake of safety, it is of key importance to accurately position the capture interface w.r.t. the gripping point on the target, especially when relative distance is very low. During these phases, the guidance and control algorithms rely on pose measurements provided by navigation sensors that are generally able to reconstruct the target position and orientation only up to a certain distance between the camera and the target. To the purpose of having a complete control of the capture interface until contact, a new sensor based on a LED and a matrix of phototransistors has been developed. This paper describes the sensor and provides its preliminary characterization. A simple theoretical description of the sensor behavior is obtained from geometrical considerations, while experiments have been performed to measure the performances of the actual hardware implementation of the system.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"34 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121436431","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 : 2021-06-23DOI: 10.1109/MetroAeroSpace51421.2021.9511761
M. Witoś, A. Szelmanowski, A. Pazur, Jerzy Borowski
In the XXI century, magnetic measurements are widely used in diverse applications. This paper presents the practical application of magnetic measurements in the Magnetic Heading System (MHS) and the Helmet Mounted Cueing System (HMCS) on board of civilian and military aircrafts. The area of application of magnetic field sensors and the corresponding measuring ranges and errors are presented. The research problem and the method of its solution were defined in relation to the determination of spatial deviation occurring in aviation heading indicating systems for various angles of spatial orientation. The mathematical relationships describing the components of the Earth's magnetic field and disturbing fields originating from hard and soft magnetic iron, which are structural elements of the aircraft, were given. An innovative element is a simulation model, developed in the Matlab-Simulink package, enabling the determination of 2D horizontal deviation and 3D spatial deviation for the given spatial orientation angles. Selected results of research on the influence of inaccuracies in the positioning of magnetometers and the possibility to identify their errors using the spectral analysis applied to the course of magnetic deviation are presented.
{"title":"Research on errors of magnetic field sensors and algorithms for determining 3D spatial deviation in aeronautical heading reference systems","authors":"M. Witoś, A. Szelmanowski, A. Pazur, Jerzy Borowski","doi":"10.1109/MetroAeroSpace51421.2021.9511761","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511761","url":null,"abstract":"In the XXI century, magnetic measurements are widely used in diverse applications. This paper presents the practical application of magnetic measurements in the Magnetic Heading System (MHS) and the Helmet Mounted Cueing System (HMCS) on board of civilian and military aircrafts. The area of application of magnetic field sensors and the corresponding measuring ranges and errors are presented. The research problem and the method of its solution were defined in relation to the determination of spatial deviation occurring in aviation heading indicating systems for various angles of spatial orientation. The mathematical relationships describing the components of the Earth's magnetic field and disturbing fields originating from hard and soft magnetic iron, which are structural elements of the aircraft, were given. An innovative element is a simulation model, developed in the Matlab-Simulink package, enabling the determination of 2D horizontal deviation and 3D spatial deviation for the given spatial orientation angles. Selected results of research on the influence of inaccuracies in the positioning of magnetometers and the possibility to identify their errors using the spectral analysis applied to the course of magnetic deviation are presented.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"53 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121630945","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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