2017 IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace)最新文献

{"title":"Calibration of extrinsic parameters of a hybrid vision system for navigation comprising a very low resolution Time-of-Flight camera","authors":"M. Pertile, S. Chiodini, Riccardo Giubilato, S. Debei","doi":"10.1109/METROAEROSPACE.2017.7999604","DOIUrl":"https://doi.org/10.1109/METROAEROSPACE.2017.7999604","url":null,"abstract":"A procedure to calibrate the relative position and orientation (extrinsic parameters) between a Time of Flight (ToF) camera and an RGB camera is presented. The proposed approach is particularly suited for ToF cameras characterized by very low resolution and a limited field of view. The presented experimental set-up is conceived to facilitate feature detection using both the ToF and RGB cameras. Three different methods for feature detection using the ToF camera, are described and their behaviors are evaluated and compared through experimental tests.","PeriodicalId":229414,"journal":{"name":"2017 IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"95 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124629011","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":"Environmental impacts on antennas for wireless sensors on outer aircraft surfaces","authors":"W. Stocksreiter, H. Zangl, M. Moser","doi":"10.1109/METROAEROSPACE.2017.7999625","DOIUrl":"https://doi.org/10.1109/METROAEROSPACE.2017.7999625","url":null,"abstract":"Wireless sensors on the outer surface of aircrafts are of interest for both research and control of modern aircrafts. However, the constraints are quite challenging for the antenna design: Since the surface may be conductive and the constructive height of the sensor must remain low, e.g. below one millimeter, the antenna gain and directivity can be quite unfavorable. Moreover, the reliability of the wireless link in particular under varying environmental conditions, e.g. due to rain or icing conditions, is also a critical aspect. In this paper we report simulations and experimental results obtained in an icing wind tunnel. We show that the additional path loss for flat antennas mounted on a wing model remains below 25dB due to icing and rain conditions.","PeriodicalId":229414,"journal":{"name":"2017 IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122103422","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":"A measurement system for testing light remotely piloted aircraft","authors":"P. Daponte, F. Lamonaca, F. Picariello, M. Riccio, Luca Pompetti, Mauro Pompetti","doi":"10.1109/METROAEROSPACE.2017.7999605","DOIUrl":"https://doi.org/10.1109/METROAEROSPACE.2017.7999605","url":null,"abstract":"In this paper, a system for testing light Vertical Take Off and Landing (VTOL) — Remotely Piloted Aircraft System (RPAS), called “DronesBench”, is proposed. This system aims to detect fault related to the RPAS components by measuring the thrust force module, the power consumption and the attitude stability of RPAS under test. In this paper, the system is described and preliminary results are reported by testing a quad-rotor VTOL-RPAS. Furthermore, according to the systems already available in literature, the novelty and the advantages of “DronesBench” are highlighted.","PeriodicalId":229414,"journal":{"name":"2017 IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"55 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116730846","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":"Laboratory test of pose determination algorithms for uncooperative spacecraft","authors":"R. Opromolla, Marco Z. Di Fraia, G. Fasano, G. Rufino, M. Grassi","doi":"10.1109/METROAEROSPACE.2017.7999558","DOIUrl":"https://doi.org/10.1109/METROAEROSPACE.2017.7999558","url":null,"abstract":"This paper presents an experimental activity carried out to evaluate the performance of LIDAR-based algorithms for pose determination of uncooperative space targets. The test setup includes a scanning LIDAR and a monocular camera mounted with a fixed relative geometry, providing 3D (point cloud) and 2D (image) representations of the same scene within the shared portion of their respective Field-of-Views. A scaled satellite mock-up is used as target. The target pose with respect to the camera, computed implementing a standard solution to the Perspective-n-Points problem, is exploited as a reference to verify the performance of the LIDAR-based pose estimation process. To this end, an original semi-analytical approach is developed to determine the relative extrinsic calibration between camera and LIDAR.","PeriodicalId":229414,"journal":{"name":"2017 IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116905922","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":"Design and testing of a low-cost extended-range pressure measurement system for aerospace applications","authors":"Arthur Provost, Guillaume Bonneric, M. Ferlauto, G. D. Di Cicca","doi":"10.1109/METROAEROSPACE.2017.7999531","DOIUrl":"https://doi.org/10.1109/METROAEROSPACE.2017.7999531","url":null,"abstract":"The paper describes the design, development and testing of an automated, programmable pressure measurement system based on low-cost sensors. To improve the accuracy of the measure, multiple sensors with different pressure range are used. A micro-controller drives the automatic switching logic and activates the suitable sensor for the measured pressure range. A practical application is described, where the device measures the velocity profile at the inlet of a micro-jetengine and computes the instantaneous inlet mass-flow rate.","PeriodicalId":229414,"journal":{"name":"2017 IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"67 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117094987","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":"A survey of calibration algorithms for small satellite magnetometers","authors":"H. Soken","doi":"10.1109/METROAEROSPACE.2017.7999539","DOIUrl":"https://doi.org/10.1109/METROAEROSPACE.2017.7999539","url":null,"abstract":"Magnetometers are an integral part of attitude determination system for the low-Earth orbiting small satellites as they are lightweight, inexpensive and reliable. Yet using magnetometers for attitude determination is not straightforward because of the sensor errors. These errors limit the overall achievable attitude determination accuracy. Thus far different methods to cope with magnetometer errors and calibrate the magnetometers have been proposed. A new research field is the specific errors for magnetometers onboard the small satellites and their time-variation characteristics. In accordance, algorithms which consider also the time-varying error terms are proposed. This paper reviews the recent calibration algorithms for small satellite magnetometers. The survey mainly covers batch and recursive estimation algorithms which are capable of estimating the time-varying magnetometer error terms. It presents the foundation of each algorithm and covers issues about the algorithm design, application and performance. In the end possible directions in this research field are briefly discussed.","PeriodicalId":229414,"journal":{"name":"2017 IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"5 3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120903679","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":"Inter-network bias: Impact on multi-network TDOA","authors":"C. Gioia, Francesco Sermi, D. Tarchi, M. Vespe, V. Kyovtorov","doi":"10.1109/METROAEROSPACE.2017.7999609","DOIUrl":"https://doi.org/10.1109/METROAEROSPACE.2017.7999609","url":null,"abstract":"The growth of applications relying on the Automatic Identification System (AIS) brings to light the need of verification and trustworthiness of AIS data. AIS data are vulnerable to false or missing declarations requiring the implementation of measures increasing the trustworthiness of AIS messages. One of the possible solution is the comparison between the reported vessel position and the position estimated using for example radiolocalization techniques. The usage of AIS signals for radi-olocalization has been already demonstrated, however the main limitation of this technique is the limited coverage. In order to extend the coverage area, data from different networks should be used. In this case an inter-network time bias has to be considered. This offset is due to the lack of standardization about the specific synchronization technique, hence each AIS receiver manufacturer can implement time extraction using different algorithms. If devices from the same manufacturer are employed, the offset between the receivers is negligible, whereas if dissimilar receivers are used, the offsets could prevent the correct outcome of the classical radiolocalization techniques. In order to fill in this gap, a “Multi-Network (MN) Time Difference Of Arrival (TDOA)” algorithm has been designed. The approach extends the traditional TDOA technique, by working out any synchronization problem. The algorithm has been tested in simulated scenarios. From the results, the effects of the inter-network bias have been investigated and the benefits of the inclusion of heterogeneous stations, either non-synchronized or with different accuracies, have been shown. Moreover, the maximum tolerable anachronism between the receivers included in the network has been evaluated.","PeriodicalId":229414,"journal":{"name":"2017 IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116758527","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":"Development of a counterbalanced pendulum thrust stand for electric propulsion","authors":"F. Trezzolani, M. Magarotto, M. Manente, D. Moretto, F. Bosi, G. Gallina, P. de Carlo, D. Melazzi, D. Pavarin, M. Pessana","doi":"10.1109/METROAEROSPACE.2017.7999554","DOIUrl":"https://doi.org/10.1109/METROAEROSPACE.2017.7999554","url":null,"abstract":"We have designed and tested a thrust stand conceived for the characterization of RF plasma thrusters. The balance has been employed in the development of small-medium size HPT prototypes, therefore it allows for an high number of tests per day with an accuracy within the 10%. The balance relies on the counterbalanced-type pendulum concept, which allows to achieve high sensitivity while maintaining a low overall size of the system; the displacement is measured by means of an high-accuracy laser interferometer put outside the vacuum chamber. The system can be calibrated with both a calibration mass, before the test, and an electro-magnetic device, during the test session. We have verified the linear behavior of the instrument and we have developed a dedicated algorithm in order to correct the thermal drifts of the balance. We have compared the stand measurements with the thrust estimations derived from Faraday probe measurements within the plasma plume, verifying that the two estimates are in agreement within 20%.","PeriodicalId":229414,"journal":{"name":"2017 IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126104521","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 unused power of SW safety&dependability analyses","authors":"P. Rodríguez-Dapena","doi":"10.1109/METROAEROSPACE.2017.7999546","DOIUrl":"https://doi.org/10.1109/METROAEROSPACE.2017.7999546","url":null,"abstract":"In many domains, when software controls or implements safety critical functionalities, software safety and dependability analyses are needed in order to understand how it may fail, the consequences of these failures and how to avoid or mitigate these failures. But from experience in different projects, when these analyses are performed at the software level, they are not used to their maximum extent: they are always late and their content is often incomplete (just to justify the already assigned criticality level). They are not always considered as bringing safety and dependability requirements into the project. Existing techniques may be used along all software development and used for many different purposes to support the definition, verification and demonstration of software related safety and dependability characteristics. Therefore the questions are: When are these analyses required? Why are they so difficult to be performed? How are they finally used and why in such a limited way so far? This paper will analyze when these analyses are required, what for, which ones are required by ECSS and evaluate how to better use them in Space projects.","PeriodicalId":229414,"journal":{"name":"2017 IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"101 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124806181","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":"Study on calibration technology of port quick leak detector for spacecraft","authors":"Lan Zhao, Yong-jun Cheng, Wen-jun Sun, Yongjun Wang, Yanwu Li","doi":"10.1109/METROAEROSPACE.2017.7999633","DOIUrl":"https://doi.org/10.1109/METROAEROSPACE.2017.7999633","url":null,"abstract":"In order to reduce measure standard uncertainty and achieve precise calibration of Port Quick Leak Detector in different temperatures under full range, the special calibration apparatus was designed on basis of theoretical studies. This apparatus consists of pressure standard leak system, calibration system, temperature control system, gas supply and pump system. Pressure standard leak system is made up of a series of standard leaks, it provides standard leak by adjusting the inlet gas and outlet gas pressures of standard leak. Calibration system includes measure instrument, calibration chamber, reference chamber, which used for measure the pressure leakage of leak. Temperature control system consists of constant temperature box, temperature control unit, temperature sensor etc. it can change the environment temperature of calibration system from −50°C to 20°C. Gas supply and pumping system comprised of high pressure gas cylinder, vacuum pump. It provides known pressure gas to pressure standard leak system and calibration system, and pumps all the apparatus. This apparatus is based on direct comparison calibration method of constants volume pressure reduction method, the apparatus and Port Quick Leak Detector are measured under same flow leak, which is provided by pressure standard flow system, and its correction factor in full range is gained by comparing both measure values. This apparatus is used symmetry structure for calibration chamber and reference chamber, and hence which can reduce the influence of calibration environment temperature on calibration results, calibration lower limit is extended to 2×10−6Pa·m3/s. By using cycle water system, the influence of initiative constant temperature and passivity constant temperature techniques on the calibration of detector was studied systematically, and the accurate calibration of Port Quick Leak Detector under different temperature was achieved. The effect of inlet and outlet pressures of leak on leakage was investigated, and a corrected formula about the change of leakage with pressure was derived successfully, and a series of standard leaks were provided and the full range calibration of detector is achieved. The calibration range of the resultant apparatus is 2×10−6∼1×10−3Pam3/s with a combined standard uncertainty about 4.7 %, and its calibration temperature is in the range from −50°C to 20°C.","PeriodicalId":229414,"journal":{"name":"2017 IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128388601","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}