Aerotecnica Missili & Spazio最新文献_第2页

Concept and Feasibility Analysis of the Alba Cubesat Mission 阿尔巴立方体卫星飞行任务的概念和可行性分析

Aerotecnica Missili & Spazio Pub Date : 2024-03-22 DOI: 10.1007/s42496-024-00205-9

M. Mozzato, G. Bemporad, S. Enzo, F. Filippini, R. Lazzaro, M. Minato, D. Visentin, A. Dalla Via, A. Farina, E. Pilone, F. Basana, L. Olivieri, G. Colombatti, A. Francesconi

{"title":"Concept and Feasibility Analysis of the Alba Cubesat Mission","authors":"M. Mozzato, G. Bemporad, S. Enzo, F. Filippini, R. Lazzaro, M. Minato, D. Visentin, A. Dalla Via, A. Farina, E. Pilone, F. Basana, L. Olivieri, G. Colombatti, A. Francesconi","doi":"10.1007/s42496-024-00205-9","DOIUrl":"10.1007/s42496-024-00205-9","url":null,"abstract":"<div><p>AlbaSat is a 2-Unit CubeSat which is being developed by a student team at the University of Padova. The Alba project aims to design, build, test, launch, and operate the first student CubeSat of the University of Padova, featuring four different payloads. The first goal is to collect data regarding the debris environment in Low Earth Orbit, the second goal is the study of the satellite vibrations, the third one is about CubeSat attitude determination through laser ranging technology, and the fourth goal concerns satellite laser and quantum communication. The Alba CubeSat mission has been selected by the European Space Agency to join the Fly Your Satellite! Design Booster program in December 2022. This paper presents the feasibility study of the Alba CubeSat mission reproduced in the framework of the “Space Systems Laboratory” class of Master of Science in Aerospace Engineering at the University of Padova. In the beginning, a mission requirements definition was conducted. After that, the mission feasibility was considered, with preliminary requirements verification to assess the ability of the spacecraft to survive the space environment, including compliance with Debris Mitigation Guidelines, ground station visibility and minimum operative lifetime evaluation. The Alba mission sets a base for a better understanding of the space environment and its interaction with nanosatellites, and an improvement of the accuracy of debris models. Furthermore, this paper, describing the educational experience and the results achieved, will provide a useful example for future students’ studies on CubeSat mission design.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 4","pages":"377 - 389"},"PeriodicalIF":0.0,"publicationDate":"2024-03-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-024-00205-9.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140212929","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

A Methodology for the Preliminary Design of a High-Efficiency Multistage Plasma Thruster 高效多级等离子推进器初步设计方法学

Aerotecnica Missili & Spazio Pub Date : 2024-03-20 DOI: 10.1007/s42496-024-00203-x

Nicola Puca, Mario Panelli, Francesco Battista

{"title":"A Methodology for the Preliminary Design of a High-Efficiency Multistage Plasma Thruster","authors":"Nicola Puca, Mario Panelli, Francesco Battista","doi":"10.1007/s42496-024-00203-x","DOIUrl":"10.1007/s42496-024-00203-x","url":null,"abstract":"<div><p>Space electric propulsion represents a class of power-limited systems that utilize the interaction of electromagnetic fields with ionized inert gas propellants to generate thrust. This technology has emerged as a highly fuel-efficient and sustainable alternative to chemical propulsion systems, particularly for satellite constellations. However, the miniaturization potential of EP systems is impeded by certain limitations, necessitating the exploration of novel architectures. The high-efficiency multistage plasma thruster (HEMP-T) stands as a promising contender for stand-alone missions due to its employment of a cusped magnetic-field topology, which effectively mitigates plasma-wall interactions and enhances overall efficiency even at low thrust levels. Despite the growing interest in HEMP-Ts, there is a dearth of comprehensive and streamlined preliminary design procedures for these systems. Prior research has predominantly focused on extensive numerical analyses, neglecting the development of efficient and accessible design tools. To bridge this gap, this paper presents a novel preliminary design tool derived from integrating established analytical models available in the literature. The proposed design tool also incorporates an iterative procedure that refines geometric properties using a 2D magnetostatic solver. Through the application of this tool, a 4 mN HEMP thruster was analyzed. This finally exhibited a specific impulse of approximately 2000s and a good efficiency level of 23%. Also, the results obtained for a 10 mN application align closely with those achieved by other types of EP thrusters.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 4","pages":"321 - 338"},"PeriodicalIF":0.0,"publicationDate":"2024-03-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-024-00203-x.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140225940","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Fast Reconfiguration Maneuvers of a Micro-satellite Constellation Based on a Hybrid Rocket Engine 基于混合火箭发动机的微型卫星星座的快速重组操纵

Aerotecnica Missili & Spazio Pub Date : 2024-03-13 DOI: 10.1007/s42496-024-00202-y

Antonio Sannino, Stefano Mungiguerra, Sergio Cassese, Raffaele Savino, Alberto Fedele, Silvia Natalucci

{"title":"Fast Reconfiguration Maneuvers of a Micro-satellite Constellation Based on a Hybrid Rocket Engine","authors":"Antonio Sannino, Stefano Mungiguerra, Sergio Cassese, Raffaele Savino, Alberto Fedele, Silvia Natalucci","doi":"10.1007/s42496-024-00202-y","DOIUrl":"10.1007/s42496-024-00202-y","url":null,"abstract":"<div><p>In this work, the formation flight of the CubeSat cluster RODiO (Radar for Earth Observation by synthetic aperture DIstributed on a cluster of CubeSats equipped with high-technology micro-propellers for new Operative services) with respect to a small satellite in LEO (Low Earth Orbit) has been analyzed. RODiO is an innovative mission concept funded by the Italian Space Agency (ASI) in the context of the Alcor program. The small satellite is equipped with an antenna that allows it to function as a transmitter, whereas RODiO functions as a receiver. The extension of the virtual SAR (Synthetic Aperture Radar) antenna can be achieved by establishing an along-track baseline performing an orbital coplanar maneuver. Another interesting scenario is the possibility to create a cross-track baseline performing an inclination change maneuver. Such formation reconfiguration maneuvers can be achieved in relatively short times only by use of a high-thrust propulsion system, i.e., based on conventional chemical technologies. From the study of maneuvers, it is possible to identify the required ∆<i>V</i> (order of magnitude of 10 m/s), which represents an input parameter for the design of propulsion system. Among the different kinds of propulsion systems, a Hybrid Rocket Engine was chosen. Based on the previous experience acquired by Department of Industrial Engineering (University of Naples Federico II), the preliminary design of the thrust chamber for a Hybrid Rocket Engine based on Hydrogen Peroxide (91 wt%) of the 10 N-class could be carried out, whose dimensions meet the compactness requirements of the CubeSat (1.5 U, 2 kg).</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 4","pages":"401 - 412"},"PeriodicalIF":0.0,"publicationDate":"2024-03-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-024-00202-y.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140394740","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

FLEW: A DNS Solver for Compressible Flows in Generalized Curvilinear Coordinates FLEW：广义曲线坐标下可压缩流动的 DNS 求解器

Aerotecnica Missili & Spazio Pub Date : 2024-03-04 DOI: 10.1007/s42496-024-00199-4

Giulio Soldati, Alessandro Ceci, Sergio Pirozzoli

{"title":"FLEW: A DNS Solver for Compressible Flows in Generalized Curvilinear Coordinates","authors":"Giulio Soldati, Alessandro Ceci, Sergio Pirozzoli","doi":"10.1007/s42496-024-00199-4","DOIUrl":"10.1007/s42496-024-00199-4","url":null,"abstract":"<div><p>We present FLEW, an in-house high-fidelity solver for direct numerical simulation (DNS) of turbulent compressible flows over arbitrary shaped geometries. FLEW solves the Navier–Stokes equations written in a generalized curvilinear coordinate system, in which the surface coordinates are non-orthogonal, whereas the third axis is normal to the surface. Spatial discretization relies on high-order finite-difference schemes. The convective terms are discretized using an hybrid approach, combining the near-zero numerical dissipation provided by central approximations with the robustness of weighted essentially non-oscillatory (WENO) schemes, required to capture shock waves. Central schemes are stabilized using a skew-symmetric-like splitting of convective derivatives, endowing the solver with the energy-preserving property in the inviscid limit. The maximum order of accuracy is eighth for central schemes (also used for viscous terms discretization) and seventh for WENO. The code is oriented to modern high-performance computing (HPC) platforms thanks to message passing interface (MPI) parallelization and the ability to run on graphics processing unit (GPU) architectures. Reliability, accuracy and robustness of the code are assessed in the low-subsonic, transonic and supersonic regimes. We present the results of several benchmarks, namely the inviscid Taylor–Green vortex, turbulent curved channel flow, transonic laminar flow over a NACA 0012 airfoil and turbulent supersonic ramp flow. The results for all configurations proved to be in excellent agreement with previous studies.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 4","pages":"413 - 425"},"PeriodicalIF":0.0,"publicationDate":"2024-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-024-00199-4.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140266406","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Implementation and Validation of a Numerical Method for Concentrated Suspensions in Large Flows Based on the Particle Diffusion Equation 基于粒子扩散方程的大流量集中悬浮物数值方法的实施与验证

Aerotecnica Missili & Spazio Pub Date : 2024-02-28 DOI: 10.1007/s42496-024-00197-6

Raoul Andriulli, Luca Fadigati, Mattia Magnani, Nabil Souhair, Fabrizio Ponti

{"title":"Implementation and Validation of a Numerical Method for Concentrated Suspensions in Large Flows Based on the Particle Diffusion Equation","authors":"Raoul Andriulli, Luca Fadigati, Mattia Magnani, Nabil Souhair, Fabrizio Ponti","doi":"10.1007/s42496-024-00197-6","DOIUrl":"10.1007/s42496-024-00197-6","url":null,"abstract":"<div><p>This work presents the development of an OpenFOAM solver aimed at correctly predicting dynamics of concentrated suspensions when subjected to non-uniform shear flows. The newly implemented solver is able to predict the behavior of a heterogeneous mixture whose characteristics depend on the solid particle local concentration. To simulate such behavior, the conservation equation expressing the time variation of the particle volume fraction has been implemented in OpenFOAM; this was achieved by modifying a pre-existing solver, <i>pimpleFoam</i>, which discretizes the Navier–Stokes system of equation through the PIMPLE algorithm. As a first step, the formulation of the momentum equation has been adapted to correctly solve cases with non-Newtonian fluids. Successively, the Krieger’s correlation has been used to model the viscosity variation in the domain to take in account heterogeneous particle distributions. Finally, the iterative cycle for the solution of the migration equation has been included within the time loop. The above-mentioned code has been successfully validated by comparing the numerical results with the measured data provided by experiments reported in literature.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 2","pages":"165 - 178"},"PeriodicalIF":0.0,"publicationDate":"2024-02-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-024-00197-6.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140418848","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Innovative Multi-Unmanned Vehicle System for Enhancing Diver Safety: BEA 增强潜水员安全的创新型多无人驾驶飞行器系统：东亚银行

Aerotecnica Missili & Spazio Pub Date : 2024-02-21 DOI: 10.1007/s42496-024-00198-5

Leonardo Barilaro, Jason Gauci, Marlon Galea, Andrea Filippozzi, David Vella, Robert Camilleri

{"title":"Innovative Multi-Unmanned Vehicle System for Enhancing Diver Safety: BEA","authors":"Leonardo Barilaro, Jason Gauci, Marlon Galea, Andrea Filippozzi, David Vella, Robert Camilleri","doi":"10.1007/s42496-024-00198-5","DOIUrl":"10.1007/s42496-024-00198-5","url":null,"abstract":"<div><p>This paper presents BEA (Buoy Eau Air), an innovative multi-unmanned vehicle system to address the issue of marine traffic endangering scuba diving and free diving. Scuba diving is a popular recreational activity with over 6 million active participants worldwide. Boat drivers may fail to recognize universal markers due to a variety of factors, such as inattention, unfamiliarity with dive zones, or poor visibility. In addition, some boat drivers may deliberately speed too close to dive zones, unaware of the dangers they pose to divers. This risk is particularly pronounced in popular dive destinations like Malta, where boat traffic can be heavy. Divers in these areas are often more vulnerable to collisions. To mitigate these risks, the proposed system consists of an Unmanned Aerial Vehicle (UAV), an Unmanned Surface Vehicle (USV), and an Unmanned Underwater Vehicle (UUV), which work in synergy to monitor and protect divers. The UAV monitors the surface of the sea near the dive zone for any traffic, while the USV tracks the UUV, communicates with the other unmanned vehicles, and provides a takeoff/landing surface for the UAV. The USV can also be used to tow divers and equipment to and from the shore. Finally, the UUV tracks the diver and warns them if it is unsafe to surface. The paper provides an overview of the system’s design and architecture, as well as algorithms for boat detection, precision landing, and UUV tracking. Preliminary tests on a prototype have shown that the system is suitable for the intended application. The BEA system is the first in the world to use a multi-drone system to create a geo-fence around the diver and monitor the area within it. This has the potential to significantly improve diver safety with real-time alerts, providing also assistance with navigation, towing of divers and emergency response.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 4","pages":"339 - 349"},"PeriodicalIF":0.0,"publicationDate":"2024-02-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140445405","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}

引用次数: 0

AIDAA News #21 AIDAA 新闻 #21

Aerotecnica Missili & Spazio Pub Date : 2024-02-03 DOI: 10.1007/s42496-024-00196-7

Michele Guida

引用次数: 0

AIDAA News #21 AIDAA 新闻 #21

Aerotecnica Missili & Spazio Pub Date : 2024-02-03 DOI: 10.1007/s42496-024-00196-7

Michele Guida

引用次数: 0

Near-Optimal Feedback Guidance for Low-Thrust Earth Orbit Transfers 低推力地球轨道转移的近优反馈制导

Aerotecnica Missili & Spazio Pub Date : 2024-02-01 DOI: 10.1007/s42496-023-00193-2

D. Atmaca, M. Pontani

{"title":"Near-Optimal Feedback Guidance for Low-Thrust Earth Orbit Transfers","authors":"D. Atmaca, M. Pontani","doi":"10.1007/s42496-023-00193-2","DOIUrl":"10.1007/s42496-023-00193-2","url":null,"abstract":"<div><p>This research describes a near-optimal feedback guidance, based on nonlinear orbit control, for low-thrust Earth orbit transfers. Lyapunov stability theory leads to proving that although several equilibria exist, only the desired operational conditions are associated with a stable equilibrium. This ensures quasi-global asymptotic convergence toward the desired final orbit. The dynamical model includes the effect of eclipsing on the available thrust, as well as all the relevant orbit perturbations, such as several harmonics of the geopotential, solar radiation pressure, aerodynamic drag, and gravitational attraction due to the Sun and the Moon. Near-optimality of the feedback guidance comes from careful selection of the control gains. They are identified in two steps. Step (a) is an extensive table search in which the gains are changed in a large interval. Step (b) uses a numerical optimization algorithm that refines the gains found in (a), while minimizing the time of flight. For the numerical simulations, two scenarios are defined: (i) nominal conditions and (ii) nonnominal conditions, which arise from orbit injection errors and stochastic failures of the propulsion system. For case (i), gain optimization leads to obtaining numerical results very close to those corresponding to a known optimal orbit transfer with eclipse arcs. Moreover, for case (ii), extensive Monte Carlo simulations demonstrate that the nonlinear feedback guidance at hand is effective in driving a spacecraft from a low Earth orbit to a geostationary orbit, also in the presence of nonnominal flight conditions.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 3","pages":"245 - 253"},"PeriodicalIF":0.0,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-023-00193-2.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139814354","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

EFESTO-2: European Flexible Heat Shields Advanced TPS Design and Tests for Future In-Orbit Demonstration-2 EFESTO-2：欧洲柔性热屏蔽先进 TPS 设计和未来在轨演示-2 测试

Aerotecnica Missili & Spazio Pub Date : 2024-01-19 DOI: 10.1007/s42496-023-00191-4

Giuseppe Guidotti, Alessandro Princi, Jaime Gutierrez-Briceno, Federico Trovarelli, Giuseppe Governale, Nicole Viola, Ingrid Dietlein, Steffen Callsen, Kevin Bergmann, Junnai Zhai, Thomas Gawehn, Roberto Gardi, Barbara Tiseo, Ysolde Prevereaud, Yann Dauvois, Giovanni Gambacciani, Giada Dammacco

{"title":"EFESTO-2: European Flexible Heat Shields Advanced TPS Design and Tests for Future In-Orbit Demonstration-2","authors":"Giuseppe Guidotti, Alessandro Princi, Jaime Gutierrez-Briceno, Federico Trovarelli, Giuseppe Governale, Nicole Viola, Ingrid Dietlein, Steffen Callsen, Kevin Bergmann, Junnai Zhai, Thomas Gawehn, Roberto Gardi, Barbara Tiseo, Ysolde Prevereaud, Yann Dauvois, Giovanni Gambacciani, Giada Dammacco","doi":"10.1007/s42496-023-00191-4","DOIUrl":"10.1007/s42496-023-00191-4","url":null,"abstract":"<div><p>EFESTO-2 is an EU-funded project under Horizon Europe that aims to enhance European expertise in Inflatable Heat Shields (IHS). Building on the achievements of the previous EFESTO project (H2020 funds No 821801), EFESTO-2 focuses on advancing key IHS technologies to increase their Technology Readiness Level (TRL). The project pillars include analysing the business case for IHS applications, exploring additional aspects of IHS, improving tools and models and establishing a development roadmap for IHS systems. This paper outlines the project objectives and plan, highlighting ongoing and future activities for the next 2 years, positioning it within the European re-entry technology roadmap. This project has received funding from the European Union's Horizon Europe program (grant agreement No 1010811041).</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 2","pages":"149 - 164"},"PeriodicalIF":0.0,"publicationDate":"2024-01-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-023-00191-4.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139525702","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0