Pub Date : 2021-06-23DOI: 10.1109/MetroAeroSpace51421.2021.9511754
A. Spiridonov, V. Saetchnikov, Dmitrii Ushakov, V. Cherny, A. Kezik
The Doppler measurements of the telemetry radio signals nanosatellite CubeBel-l for a single pass over the Belarusian State University ground station were carried out. Two methods for orbit determination of a small satellite are considered. The first method is based on the SGP4 model and requires additional information from the NORAD TLE catalog of the satellite orbital parameters. An unknown small satellite is identified using the NORAD TLE catalog based on a probabilistic estimation of the elevation angle and the Doppler frequency shift of receiving telemetry signals. The second method is based on processing experimental measurements of the Doppler frequency of the telemetry radio signals and Keplerian circular motion model for the small satellite. It does not require additional information from the NORAD database of satellite orbital parameters.
{"title":"Orbit Determination Methods For LEO Satellites From Probabilistic Analysis, Circular Motion Model And Single Pass Doppler Measurements","authors":"A. Spiridonov, V. Saetchnikov, Dmitrii Ushakov, V. Cherny, A. Kezik","doi":"10.1109/MetroAeroSpace51421.2021.9511754","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511754","url":null,"abstract":"The Doppler measurements of the telemetry radio signals nanosatellite CubeBel-l for a single pass over the Belarusian State University ground station were carried out. Two methods for orbit determination of a small satellite are considered. The first method is based on the SGP4 model and requires additional information from the NORAD TLE catalog of the satellite orbital parameters. An unknown small satellite is identified using the NORAD TLE catalog based on a probabilistic estimation of the elevation angle and the Doppler frequency shift of receiving telemetry signals. The second method is based on processing experimental measurements of the Doppler frequency of the telemetry radio signals and Keplerian circular motion model for the small satellite. It does not require additional information from the NORAD database of satellite orbital parameters.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"2015 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":"127265180","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/MetroAeroSpace51421.2021.9511673
Mastan Raja Papanaboina, E. Jasiūnienė
The assessment of damages in the aircraft components is a key aspect to avoid structural failure. In general, damages may occur due to flight load, accidents during the maintenance and environmental conditions. Primary airframes such as aircraft wings and fuselages are covered with thin aluminum alloys. The damages in the aircraft wing skins are posing a serious threat. The traditional non-destructive testing (NDT) often requires dismantling the component for inspection, consuming more time. Guided wave structural health monitoring (GWSHM) is an alternative to inspect the large structures, it is a time saving and cost-effective. However, the defect identification and localization using multi-mode and highly dispersive guided waves requires significant knowledge. In this research, multiple defects are examined by performing numerical simulation. The defect can be identified and located by measuring the Time of Flight (ToF) and delay time of a signal. The Hilbert Transform (HT) and Zero-crossing techniques are used to measure the ToF of the signal to enable defect presence and the delay time between two signals are analyzed to enable defect location.
{"title":"The Defect Identification and Localization using Ultrasonic Guided Waves in Aluminum Alloy","authors":"Mastan Raja Papanaboina, E. Jasiūnienė","doi":"10.1109/MetroAeroSpace51421.2021.9511673","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511673","url":null,"abstract":"The assessment of damages in the aircraft components is a key aspect to avoid structural failure. In general, damages may occur due to flight load, accidents during the maintenance and environmental conditions. Primary airframes such as aircraft wings and fuselages are covered with thin aluminum alloys. The damages in the aircraft wing skins are posing a serious threat. The traditional non-destructive testing (NDT) often requires dismantling the component for inspection, consuming more time. Guided wave structural health monitoring (GWSHM) is an alternative to inspect the large structures, it is a time saving and cost-effective. However, the defect identification and localization using multi-mode and highly dispersive guided waves requires significant knowledge. In this research, multiple defects are examined by performing numerical simulation. The defect can be identified and located by measuring the Time of Flight (ToF) and delay time of a signal. The Hilbert Transform (HT) and Zero-crossing techniques are used to measure the ToF of the signal to enable defect presence and the delay time between two signals are analyzed to enable defect location.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"84 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":"126207996","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/MetroAeroSpace51421.2021.9511767
J. Pytka, P. Budzyński, Pawel Tomilo, Jan Laskowski, Joanna Michałowska, E. Gnapowski, D. Blazejczak, A. Łukaszewicz
The IMUMETER is a name an innovative sensor for measuring motion of any object, originally proposed by the authors. The IMUMETER was developed specifically for the purpose of monitoring airplane's motion in flight, especially during takeoff and landing. Separate phases of flight can be recognized by this sensor and this enables to analyze The paper includes the description of the development process as well as the tests of the IMUMETER prototype. Results obtained during a flight test campaign, performed with the PZL 104 Wilga 35A have also been included in the paper. One conclusion is that the IMUMETER sensor enables to determine touchdown point and, consequently to calculate landing ground roll distance.
{"title":"IMUMETER - AI-Based Sensor for Airplane Motion Measurements","authors":"J. Pytka, P. Budzyński, Pawel Tomilo, Jan Laskowski, Joanna Michałowska, E. Gnapowski, D. Blazejczak, A. Łukaszewicz","doi":"10.1109/MetroAeroSpace51421.2021.9511767","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511767","url":null,"abstract":"The IMUMETER is a name an innovative sensor for measuring motion of any object, originally proposed by the authors. The IMUMETER was developed specifically for the purpose of monitoring airplane's motion in flight, especially during takeoff and landing. Separate phases of flight can be recognized by this sensor and this enables to analyze The paper includes the description of the development process as well as the tests of the IMUMETER prototype. Results obtained during a flight test campaign, performed with the PZL 104 Wilga 35A have also been included in the paper. One conclusion is that the IMUMETER sensor enables to determine touchdown point and, consequently to calculate landing ground roll distance.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"16 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":"121315448","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/MetroAeroSpace51421.2021.9511679
G. de Alteriis, V. Bottino, C. Conte, G. Rufino, R. S. Lo Moriello
The paper presents an innovative strategy to measure the initial heading of a vehicle in the local reference frame by means of a tactical-grade MEMS-based inertial measurement unit and a low-cost MEMS magnetometer. The developed system allows not only to pointing the North direction but also to assure the stability of the attitude estimates overcoming bias and drift errors affecting the measures of this type of sensors and keeping the advantages of the MEMS sensors technology such as small volume, lightweight and flexibility. The proposed integrated solution exploits an indirect gyrocompassing strategy through an error-state Kalman Filter algorithm for the coarse alignment aided by the magnetic Earth field measurements. The system performance is preliminarily assessed in static conditions and compared with a certified reference system in order to verify its compliance with the requirement for Small Unmanned Aerial System.
{"title":"Accurate Attitude Inizialization Procedure based on MEMS IMU and Magnetometer Integration","authors":"G. de Alteriis, V. Bottino, C. Conte, G. Rufino, R. S. Lo Moriello","doi":"10.1109/MetroAeroSpace51421.2021.9511679","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511679","url":null,"abstract":"The paper presents an innovative strategy to measure the initial heading of a vehicle in the local reference frame by means of a tactical-grade MEMS-based inertial measurement unit and a low-cost MEMS magnetometer. The developed system allows not only to pointing the North direction but also to assure the stability of the attitude estimates overcoming bias and drift errors affecting the measures of this type of sensors and keeping the advantages of the MEMS sensors technology such as small volume, lightweight and flexibility. The proposed integrated solution exploits an indirect gyrocompassing strategy through an error-state Kalman Filter algorithm for the coarse alignment aided by the magnetic Earth field measurements. The system performance is preliminarily assessed in static conditions and compared with a certified reference system in order to verify its compliance with the requirement for Small Unmanned Aerial System.","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":"125915260","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/MetroAeroSpace51421.2021.9511701
D. Scaccabarozzi, B. Saggin, M. Corti, Pietro Valnegri, C. Pernechele, L. Lessio, L. Paoletti, Luca Consolaro
High-performance imaging systems play a fundamental role in space and planetary observation. Traditional cameras require actuators coupled with movable elements to scan large scenarios and overcome their limited field of view. Extra equipment increases the mass budget and the instrument complexity, as well as the risk of failure. Panoramic optics constitute a valid solution to enhance the imaging systems robustness while enlarging the camera field of view, all with a single compact device. In this paper, the feasibility of employing an off-the-shelf optical system based on a hyper-hemispheric panoramic lens for planetary observation has been assessed. In particular, the supporting frame of the aforementioned optical system has been designed to withstand a general space environment, i.e. temperature variation between −120°C and + 120°C, and considering loading during launch. A design solution is proposed, resulting from a kinematic-like mounting system to safely endure the thermal environment. In order to validate the obtained design, a mockup has been manufactured, assembled, and tested in a representative mechanical environment, exhibiting good agreement with the dynamic behaviour predicted by the developed numerical models.
{"title":"Preliminary structural design of PANCAM, a bifocal panoramic camera for planetary observation","authors":"D. Scaccabarozzi, B. Saggin, M. Corti, Pietro Valnegri, C. Pernechele, L. Lessio, L. Paoletti, Luca Consolaro","doi":"10.1109/MetroAeroSpace51421.2021.9511701","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511701","url":null,"abstract":"High-performance imaging systems play a fundamental role in space and planetary observation. Traditional cameras require actuators coupled with movable elements to scan large scenarios and overcome their limited field of view. Extra equipment increases the mass budget and the instrument complexity, as well as the risk of failure. Panoramic optics constitute a valid solution to enhance the imaging systems robustness while enlarging the camera field of view, all with a single compact device. In this paper, the feasibility of employing an off-the-shelf optical system based on a hyper-hemispheric panoramic lens for planetary observation has been assessed. In particular, the supporting frame of the aforementioned optical system has been designed to withstand a general space environment, i.e. temperature variation between −120°C and + 120°C, and considering loading during launch. A design solution is proposed, resulting from a kinematic-like mounting system to safely endure the thermal environment. In order to validate the obtained design, a mockup has been manufactured, assembled, and tested in a representative mechanical environment, exhibiting good agreement with the dynamic behaviour predicted by the developed numerical models.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"187 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":"121727315","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/MetroAeroSpace51421.2021.9511719
G. Bazzano, A. Ampollini, E. Cisbani, C. De Angelis, S. Della Monaca, P. Nenzi, E. Nichelatti, G. Palmerini, L. Picardi, M. Piccinini, C. Ronsivalle, M. Sabatini
This contribution describes the methods developed for the characterization in air of the proton beam at the TOP-IMPLART linear accelerator of ENEA Frascati Research Centre. Beam energy and spectrum, transverse homogeneity, fluence and flux are assessed both experimentally and by numerical calculations. Here we present an application of these methods for the characterization of set-ups relevant for electronic and space components testing.
{"title":"Beam characterization methods at the TOP-IMPLART proton linear accelerator: an application to space components qualification","authors":"G. Bazzano, A. Ampollini, E. Cisbani, C. De Angelis, S. Della Monaca, P. Nenzi, E. Nichelatti, G. Palmerini, L. Picardi, M. Piccinini, C. Ronsivalle, M. Sabatini","doi":"10.1109/MetroAeroSpace51421.2021.9511719","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511719","url":null,"abstract":"This contribution describes the methods developed for the characterization in air of the proton beam at the TOP-IMPLART linear accelerator of ENEA Frascati Research Centre. Beam energy and spectrum, transverse homogeneity, fluence and flux are assessed both experimentally and by numerical calculations. Here we present an application of these methods for the characterization of set-ups relevant for electronic and space components testing.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"47 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":"121350160","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/MetroAeroSpace51421.2021.9511756
A. Nebylov, A. Panferov, S. Brodsky
The features of the mathematical description of the dynamics of models are considered, the problems of the theory of designing control systems for ekranoplane (or Wing-in-Ground effect vehicle or WIG-craft), taking into account aerodynamics and local loads and flexible dynamics. Flying at low altitude over an uneven surface is accompanied by powerful periodic and impulsive loads caused by unevenness of the underlying surface. In addition, with small changes in height, the controllability and stability of the ekranoplane significantly changes up to loss of stability. For the synthesis of the ekrano-plane control system, a new method for calculating the nonlinear mathematical model of the ekranoplane is proposed based on the CFD Comsol Multiphysics and Matlab programs. The simulation results are presented.
{"title":"Mathematical Model and Control System of an Ekranoplan under the Action of Large Aerodynamic Loads","authors":"A. Nebylov, A. Panferov, S. Brodsky","doi":"10.1109/MetroAeroSpace51421.2021.9511756","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511756","url":null,"abstract":"The features of the mathematical description of the dynamics of models are considered, the problems of the theory of designing control systems for ekranoplane (or Wing-in-Ground effect vehicle or WIG-craft), taking into account aerodynamics and local loads and flexible dynamics. Flying at low altitude over an uneven surface is accompanied by powerful periodic and impulsive loads caused by unevenness of the underlying surface. In addition, with small changes in height, the controllability and stability of the ekranoplane significantly changes up to loss of stability. For the synthesis of the ekrano-plane control system, a new method for calculating the nonlinear mathematical model of the ekranoplane is proposed based on the CFD Comsol Multiphysics and Matlab programs. The simulation results are presented.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"107 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":"122896820","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/MetroAeroSpace51421.2021.9511668
L. Bonino, S. Cesare, B. Leone, L. Massotti, M. Pisani, Jessica Girella
The measurement of static and temporal variation of Earth's gravity field provides an insight on water storage, seasonal and sub-seasonal water cycles, their impact on water levels, and delivers key data to Earth's climate models. After missions like GOCE (ESA), GRACE and GRACE Follow-On (US-DE), ESA is studying a new mission provisionally named “Next Generation Gravity Mission” (NGGM) consisting of two pairs of satellites and a heterodyne laser interferometer for intersatellite ranging. Currently, two laser ranging interferometer concepts are under evaluation: the transponder and the retroreflector concept. Both concepts require to perform the laser link acquisition via an auxiliary optical metrology, named Acquisition and Pointing Metrology System (APMS). It is composed by a light source (mounted on one out of the two satellites) and an acquisition detector (mounted on the counterpart satellite). This paper describes the recently performed activity related to breadboarding and testing of the APMS optical head.
{"title":"The Innovative Acquisition and Pointing Metrology for Next Generation Gravity Mission","authors":"L. Bonino, S. Cesare, B. Leone, L. Massotti, M. Pisani, Jessica Girella","doi":"10.1109/MetroAeroSpace51421.2021.9511668","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511668","url":null,"abstract":"The measurement of static and temporal variation of Earth's gravity field provides an insight on water storage, seasonal and sub-seasonal water cycles, their impact on water levels, and delivers key data to Earth's climate models. After missions like GOCE (ESA), GRACE and GRACE Follow-On (US-DE), ESA is studying a new mission provisionally named “Next Generation Gravity Mission” (NGGM) consisting of two pairs of satellites and a heterodyne laser interferometer for intersatellite ranging. Currently, two laser ranging interferometer concepts are under evaluation: the transponder and the retroreflector concept. Both concepts require to perform the laser link acquisition via an auxiliary optical metrology, named Acquisition and Pointing Metrology System (APMS). It is composed by a light source (mounted on one out of the two satellites) and an acquisition detector (mounted on the counterpart satellite). This paper describes the recently performed activity related to breadboarding and testing of the APMS optical head.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"35 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":"132569488","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}
In order to study the terahertz continuous wave imaging technology for spacecraft porous ceramics prevent insulation adhesive quality, a terahertz continuous wave imaging system was built. The porous ceramic insulation cover proof imaging features of metal components has carried on through experimental study. Combined with two-dimensional scanning imaging obtained clear images, result of test proved practicability of scaffolding system, and methods to improve the quality of imaging system is discussed in detail.
{"title":"Research on Non-destructive test of porous ceramic insulation material for spacecraft based on Terahertz continuous wave imaging technology","authors":"Yonghong Wu, Yuekui Zhang, Zhu Jiang, Yongyao Xu, Lin Liu, Yinxiao Miao","doi":"10.1109/MetroAeroSpace51421.2021.9511681","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511681","url":null,"abstract":"In order to study the terahertz continuous wave imaging technology for spacecraft porous ceramics prevent insulation adhesive quality, a terahertz continuous wave imaging system was built. The porous ceramic insulation cover proof imaging features of metal components has carried on through experimental study. Combined with two-dimensional scanning imaging obtained clear images, result of test proved practicability of scaffolding system, and methods to improve the quality of imaging system is discussed in detail.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"33 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":"133897341","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/MetroAeroSpace51421.2021.9511770
A. Riccio, S. Saputo, M. Zarrelli, A. Sellitto, Carmine Napolitano, V. Acanfora
In this work, an experimental characterization of Shape Memory Alloy (SMA) springs was carried-out to assess the efficiency of simple analytical procedure for a preliminary design of Shape Memory Alloy-based spring actuators. Two static analytical models were considered recursively, respectively to determine SMA material properties by accurate tensile experimental test and to identify the optimized geometrical characteristic of SMA-bias spring-based unit for a specific feasible mini-actuator for vehicle moveable part. The final extra-force and displacement of the actuator was validated at different temperature above transformation temperature to assess the limitation of the implemented procedure.
{"title":"Shape Memory Alloy-based actuator: experimental and modelling","authors":"A. Riccio, S. Saputo, M. Zarrelli, A. Sellitto, Carmine Napolitano, V. Acanfora","doi":"10.1109/MetroAeroSpace51421.2021.9511770","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace51421.2021.9511770","url":null,"abstract":"In this work, an experimental characterization of Shape Memory Alloy (SMA) springs was carried-out to assess the efficiency of simple analytical procedure for a preliminary design of Shape Memory Alloy-based spring actuators. Two static analytical models were considered recursively, respectively to determine SMA material properties by accurate tensile experimental test and to identify the optimized geometrical characteristic of SMA-bias spring-based unit for a specific feasible mini-actuator for vehicle moveable part. The final extra-force and displacement of the actuator was validated at different temperature above transformation temperature to assess the limitation of the implemented procedure.","PeriodicalId":236783,"journal":{"name":"2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"17 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":"115560973","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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