2023 IEEE 10th International Workshop on Metrology for AeroSpace (MetroAeroSpace)最新文献

{"title":"Survey of GNC sensors suitable for hybrid stratospheric platform applications","authors":"Luca de Pasquale, P. Gili","doi":"10.1109/MetroAeroSpace57412.2023.10190015","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace57412.2023.10190015","url":null,"abstract":"The stratosphere has been receiving increasing interest by the aerospace industry due to its characteristics which make it a particularly suitable environment for performing missions that require proximity to and persistence over a specific area. Among the various available autonomous platforms, airships have proven to be the most effective in terms of cost, reliability, payload mass capacity and endurance. In order to overcome the limitations of typical airships, a novel configuration has been proposed: hybrid airships. By generating the lifting force through both aerostatics and aerodynamics, it is possible to carry even larger payloads without having to significantly increase the hull size. The purpose of this work is to provide a survey on the state of the art of GNC sensors, specifically for hybrid stratospheric platforms. The paper will provide a selection of suitable sensor technologies among those available, including air data sensors which are a fundamental source of information for the safe and effective operation of a hybrid platform.","PeriodicalId":153093,"journal":{"name":"2023 IEEE 10th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124742912","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":"Analysis of the thermal environment in the LuNaDrone exploration mission of lunar lava tubes","authors":"Stefano Pescaglia, R. Barbieri, Giuseppe Bortolato, P. Maggiore, P. Messidoro, R. Vittori","doi":"10.1109/MetroAeroSpace57412.2023.10189980","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace57412.2023.10189980","url":null,"abstract":"Lunar Nano Drone (LuNaDrone) is a small spacecraft capable of performing autonomous flight in the lunar near-surface environment, whose primary application is a mission of exploration of lunar pits to detect potential openings to lunar lava tubes. Throughout the phases of this mission, the spacecraft has to deal with several thermal environments and among these, the lunar surface operations can be critical for the thermal control design. A meaningful thermal analysis requires correct modelling of both the thermal environment and the spacecraft, on the ground and in flight. The proposed modelling approach, implemented in Thermal Desktop, aims to provide a preliminary evaluation of the radiative thermal fluxes incident on the spacecraft faces throughout the surface operations and flight segments, in order to qualitatively validate the flight manoeuvres model implementation and to identify the most critical thermal scenario. Starting from temperature data of Apollo 17 and Lunar Reconnaissance Orbiter, a thermal model was designed for the lunar surface and for a lunar pit, characterizing them for the Mare Tranquillitatis Pit case. A 12U test box has been modelled in order to evaluate heat fluxes on the spacecraft, exploiting Thermal Desktop's Assembly and Symbols features to implement the flight manoeuvres in the thermal model. The analyses were performed for three different local times and four cardinal directions approaches to the pit. The results showed how the modelling approach correctly allows the implementation of flight manoeuvres in the thermal model. Regardless of local time or spacecraft orientation, the results show that the most critical radiative scenario is not one of the flight segments, but the transmission phase, after the propellant has been almost completely depleted and the spacecraft finds itself in a highly radiative environment on the lunar surface.","PeriodicalId":153093,"journal":{"name":"2023 IEEE 10th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"52 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125371505","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 Non-Autonomous Doppler Navigation Method With Navigation Beacon","authors":"Tao Yu","doi":"10.1109/MetroAeroSpace57412.2023.10190010","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace57412.2023.10190010","url":null,"abstract":"A moving platform equipped with a Doppler receiver detects and receives signals from navigation beacon stations at a fixed speed and time interval. After obtaining three Doppler frequency shifts in succession, on the one hand, the moving speed of the moving platform itself is calculated by comprehensively using the velocity vector equation and the velocity analytical formula given by the Doppler frequency shift and the rate of change relationship. On the other hand, the virtual path difference is calculated by the path difference-frequency shift equation, and the virtual double-base array is constructed by using the motion trajectory of the single detection station. Thus, the distance and orientation of the moving platform relative to the beacon station can be directly obtained by using the double-base path difference positioning theory.","PeriodicalId":153093,"journal":{"name":"2023 IEEE 10th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"67 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127690099","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":"Optical multi-camera UAV positioning system via ArUco fiducial markers","authors":"Tony De Corso, L. De Vito, F. Picariello, K. Wojtowicz, Adam Marut, Przemysław Wojciechowski","doi":"10.1109/MetroAeroSpace57412.2023.10190004","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace57412.2023.10190004","url":null,"abstract":"In this paper, a multi-camera positioning system for Unmanned Aerial Vehicles (UAVs) via ArUco fiducial markers is proposed. Alternatively to the commonly used Global Navigation Satellite System (GNSS) technology, or to the positioning services provided by the mobile networks, the proposed system makes use of a set of optical cameras and a set of ArUco fiducial markers embedded in the UAV's frame. This offers a simple and scalable system in which a variable amount of cameras can detect any number of UAVs. A static analysis of the system has been carried out, in which a set of cameras mounted on the ground look at the target from different distances. The collected results exhibit a promising performance in terms of the precision of the system. Moreover, the effect of a weighted average between different camera estimates has been investigated, showing that it effectively compensates for the effect of the increasing distance between cameras and a target.","PeriodicalId":153093,"journal":{"name":"2023 IEEE 10th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"496 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130001179","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":"Optimized Design and Experimental Analysis of Mechanical Structure of Torsional Pendulum Thrust Frame","authors":"Qing-Qing Wang, Junwei Jia, Xue-Chao Liu, Yu-Jing Wu, Meng Chang, Tie-Li Li, Hao Lang, Xue-Jiang Dong, Ren Zhang","doi":"10.1109/MetroAeroSpace57412.2023.10190001","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace57412.2023.10190001","url":null,"abstract":"China enters the era of large-scale application of plasma propulsion in 2020, and there is an urgent demand for electric propulsion technology in the fields of human spaceflight, communication constellation, deep space exploration, and space science. Thrust is one of the key performance indicators of electric propulsion systems. Accurate and reliable measurement of thrust is the basis for performance testing and optimization of electric propulsion systems. Currently, 10∼100-mN electric propulsion systems are the most widely used. In this paper, a mechanical structure model of a 10∼100-mN torsional pendulum thrust frame is proven using the lever principle, the deflection performance under different thrusts is studied, and the linear relationship between deflection displacement and thrust is derived. The ANSYS simulation software was used to perfect the simulation analysis of each design variable. The influence of each parameter is investigated by experiment. The results show that the optimized torsional pendulum thrust frame structure has good linearity, and the relative error is better than 0.33%.","PeriodicalId":153093,"journal":{"name":"2023 IEEE 10th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"os-44 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127782485","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":"Evaluation of Potential Flow Capabilities for Ground Effect Predictions of a Single Propeller","authors":"A. Lerro","doi":"10.1109/MetroAeroSpace57412.2023.10189926","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace57412.2023.10189926","url":null,"abstract":"The present work aims to investigate the capabilities of a potential flow approach to predict the ground effect of a single double-blade propeller. Proper models of propeller working close to solid surfaces, e.g, multi-rotor drones or helicopter tail rotors, can be useful for control end manoeuvrability studies. A low-fidelity approach can be suitable for preliminary design stages where the responsiveness is more important than very accurate estimations. The panel code VSPAERO is developed by NASA and implemented in the desktop application Open VSP where it is possible to model several geometries. Firstly, using the propeller outside the ground effect, a mesh sensitivity is documented comparing results with respect to wind tunnel tests. Secondly, the ground is modelled in Open VSP using geometries available in the software. The numerical results are compared to theoretical ones in order to highlight the prediction capability of the proposed approach when the propeller works in ground effect. Moreover, a flow analysis is performed in order to highlight the limitations of the proposed approach to simulate a propeller in ground effect.","PeriodicalId":153093,"journal":{"name":"2023 IEEE 10th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"6 42","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120929880","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":"Atmospheric effects on testing and calibrating star tracking algorithms","authors":"Louis Jannin, L. Felicetti","doi":"10.1109/MetroAeroSpace57412.2023.10190028","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace57412.2023.10190028","url":null,"abstract":"Star trackers are usually considered to be the most accurate sensors, able to achieve a sub-arcminute precision. Star tracker algorithms are often tested and validated with simulated space views. Testing the algorithms with real space images is expensive as it requires implementing them on existing in-space star trackers, or launching new satellites. This study shows that those algorithms are usually performing poorly with ground-based sky pictures and that some adaptations are necessary to take into account the atmospheric effects. In order to tackle this issue, this study will start by implementing and testing two published Lost-In-Space algorithms with a simulated sensor to compare their performance against various noise sources. After comparing the space-based generated views with ground-based images, an adaptation for the aforementioned algorithms is proposed. In order to counter the effect of atmospheric extinction, the number of stars visible in the image is increased by modifying the field-of-view of the camera, the exposure time and estimating the experimental inter-star angular distance error. The idea is to match the star density used in the state-of-the-art algorithms in the experimental pictures. The modified algorithms are tested with the experimental images, and the adaptation process is validated with a good success rate.","PeriodicalId":153093,"journal":{"name":"2023 IEEE 10th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"70 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115982375","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":"CFD prediction of bioaerosol dynamics in a concept air sanitiser for space applications","authors":"G. Mongelluzzo, M. Lombini, L. Schreiber, G. Pareschi, A. Bianco, E. Diolaiti, F. Cortecchia, G. Malaguti, L. Lessio, M. Pelizzo, M. Fiorini, E. Cascone, V. de Caprio","doi":"10.1109/MetroAeroSpace57412.2023.10189974","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace57412.2023.10189974","url":null,"abstract":"SAILOR Moon is a concept air sanitiser for closed space environments. There is indeed an increasing interest in the development of potentially inhabited outposts in space, such as the forecasted NASA's Lunar Gateway, as well as on the Moon and Mars surfaces. The health monitoring of astronauts is paramount in the development of such missions. The idea is to collect pathogens emitted in the closed environment by astronauts, especially through bioaerosol, and use the well-known principle of Ultraviolet Germicidal Irradiation (UVGI) through UVC light for pathogen inactivation. This work focuses on the method for predicting the device's bioaerosol dynamics. The method mainly relies on Computational Fluid Dynamics (CFD) and optical simulations. In this paper, the CFD simulations performed are presented, along with some analysis results and their implications.","PeriodicalId":153093,"journal":{"name":"2023 IEEE 10th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"86 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126269481","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":"Striking a Balance: Performance and Cost Optimization of LEO-PNT Constellation for Hybrid Users Using a Meta-Heuristic Approach","authors":"Lorenzo Marchionne, Leandro Maria Gessato, Fabrizio Toni, S. L. Barbera","doi":"10.1109/MetroAeroSpace57412.2023.10189946","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace57412.2023.10189946","url":null,"abstract":"The design process of a novel LEO-PNT constellation that can provide continuous global coverage to hybrid users (e.g., those who require the use of both GNSS and LEO systems) is predominantly governed by two key factors, namely the system's performance and cost. They play a decisive role in determining the optimal configuration of the constellation. The performance factors entail a comprehensive evaluation of the constellation's ability to meet the desired mission objectives and requirements, including, but not limited, to services' availability and continuity, and position and timing accuracies. On the other hand, the cost drivers encompass the expenses associated with designing, launching, and maintaining the constellation over its expected lifespan. As such, a delicate balance between the two factors must be struck to ensure that the design outcome is not only efficient and effective but also economically viable. The present study sought to address the LEO-PNT constellation design problem through a meta-heuristic approach and by formulating it as a multi-objective optimization problem. To solve this problem, a nondominated sorting-based Multi-Objective Evolutionary Algorithm (MOEA), specifically a variant of N ondominated Sorting Genetic Algorithm II (NSGA-II) was employed because they have been shown to be effective optimization means to search the complex trade-off spaces of satellite constellation design [1]. Four Figures of Merit (FoMs) are used as objectives to strive for a fast trade-off between the navigation performance and the space segment cost and deployment efficiency, namely the minimization of Global Dilution Of Precision (GDOP) both at Average User Location (AUL) and Worst User Location (WUL), plus the minimization of the total number of satellites and orbital planes. A ranking-based approach is used to select the best solution candidates and fine-tuning of the best constellation patterns set is performed to enhance the efficiency of the optimization process. This paper first introduces a tailored optimization strategy and methodology for the design of a new LEO-PNT constellation with global coverage. The implementation of this methodology is presented, starting from the assumption of a plausible but simplified set of mission scenarios and requirements. The resultant optimal design is then validated for compliance by carrying out a detailed analysis of the selected constellation baselines in high resolution, in terms of user grid points uniformly distributed on the Earth's surface and simulation time window.","PeriodicalId":153093,"journal":{"name":"2023 IEEE 10th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"16 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128472481","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 heuristic algorithm for aircraft landing scheduling problem","authors":"V. Guliashki, G. Mušič, G. Marinova","doi":"10.1109/MetroAeroSpace57412.2023.10189951","DOIUrl":"https://doi.org/10.1109/MetroAeroSpace57412.2023.10189951","url":null,"abstract":"This paper considers Aircraft Landing Problem (ALP) in the context of optimal runway utilization. A heuristic algorithm is proposed to minimize a penalty cost function associated with the difference between the determined landing time and the target landing time. The objective is to obtain an optimal schedule for a sequence of a finite number of aircraft that can use 1, 2, or 3 runways. The constraints are defined in relation to the time window bounded by the earliest and latest landing times. Six single-objective simulation optimization tasks were solved, namely 2 tasks on 1 runway, one with sequences of 10 and the second with sequences of 20 aircraft, 2 tasks on 2 runways with sequences of 10 and 20 aircraft, respectively, and 2 tasks on 3 runways with sequences of 10 and 20 aircraft. The solutions found are optimal. The results show that the proposed algorithm has a good performance and can be used for solving real-life optimization problems of this type.","PeriodicalId":153093,"journal":{"name":"2023 IEEE 10th International Workshop on Metrology for AeroSpace (MetroAeroSpace)","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125143001","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}