Aerotecnica Missili & Spazio最新文献_第2页

Overview of Spacecraft-Fragmentation Testing 航天器碎片测试概述

Aerotecnica Missili & Spazio Pub Date : 2024-04-18 DOI: 10.1007/s42496-024-00209-5

Stefano Lopresti, Federico Basana, Lorenzo Olivieri, Cinzia Giacomuzzo, Alessandro Francesconi

引用次数: 0

A Combustion-Driven Facility for Hypersonic Sustained Flight Simulation 用于高超音速持续飞行模拟的燃烧驱动设施

Aerotecnica Missili & Spazio Pub Date : 2024-04-17 DOI: 10.1007/s42496-024-00213-9

Antonio Esposito, Marcello Lappa, Christophe Allouis

引用次数: 0

AIDAA News #22 AIDAA 新闻 #22

Aerotecnica Missili & Spazio Pub Date : 2024-04-13 DOI: 10.1007/s42496-024-00217-5

Michele Guida

引用次数: 0

Analysis of Subsonic/Hypersonic Aerodynamics of a High-Speed Aircraft 高速飞机的亚音速/超音速空气动力学分析

Aerotecnica Missili & Spazio Pub Date : 2024-04-05 DOI: 10.1007/s42496-024-00211-x

Giuseppe Pezzella, Antonio Viviani

引用次数: 0

SHM Implementation on a RPV Airplane Model Based on Machine Learning for Impact Detection 基于机器学习的 RPV 飞机模型 SHM 实现，用于撞击检测

Aerotecnica Missili & Spazio Pub Date : 2024-04-02 DOI: 10.1007/s42496-024-00206-8

Flavio Dipietrangelo, Francesco Nicassio, Gennaro Scarselli

{"title":"SHM Implementation on a RPV Airplane Model Based on Machine Learning for Impact Detection","authors":"Flavio Dipietrangelo, Francesco Nicassio, Gennaro Scarselli","doi":"10.1007/s42496-024-00206-8","DOIUrl":"10.1007/s42496-024-00206-8","url":null,"abstract":"<div><p>In this study, an on-working structural health monitoring system for impact detection on remote piloted vehicle (RPV) airplane is proposed. The approach is based on the propagation of Lamb waves in metallic structures on which Pb[Zr<sub><i>x</i></sub>Ti<sub>1−<i>x</i></sub>]O<sub>3</sub> (PZT) sensors are bonded for receiving vibrational signals due to impact events. The proposed method can be used to detect impacts in aerospace structures, i.e. skin fuselage and/or wing panels. After the detection, machine learning (ML) algorithms (polynomial regression and neural networks) are applied for processing the acquired ultrasounds waves in order to characterise the impacts, in terms of time of flight (ToF) and relative location. Several test cases are studied: the ML models are tested both without external noise (in laboratory) and introducing external RC engine vibration (on-working conditions). Furthermore, this work presents the implementation of a mini-equipment for acquisition and data processing based on Raspberry Pi. A good agreement between laboratory and in-flight results is achieved, in terms of distance between the actual and calculated impact location.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 4","pages":"363 - 375"},"PeriodicalIF":0.0,"publicationDate":"2024-04-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-024-00206-8.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140750964","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

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

Paving the Way for the Electrified Future of Flight: Safety Criteria Development for Integrating Structural Batteries in Aircraft 为未来的电气化飞行铺平道路：飞机结构电池集成安全标准的制定

Aerotecnica Missili & Spazio Pub Date : 2024-03-18 DOI: 10.1007/s42496-024-00207-7

G. Di Mauro, M. Guida, G. Olivares, L. M. Gomez

{"title":"Paving the Way for the Electrified Future of Flight: Safety Criteria Development for Integrating Structural Batteries in Aircraft","authors":"G. Di Mauro, M. Guida, G. Olivares, L. M. Gomez","doi":"10.1007/s42496-024-00207-7","DOIUrl":"10.1007/s42496-024-00207-7","url":null,"abstract":"<div><p>Within the global push towards environmental sustainability, the aviation industry is increasingly investigating electrification as a potential solution to reduce emissions and combat climate change. However, traditional battery integration faces significant drawbacks due to their limited energy and power densities, which negatively impact aircraft weight and performance. In this scenario, structural batteries are gaining interest, since they combine energy storage and load-bearing capabilities in multifunctional material structures, thus potentially eliminating barriers to the electrification of the air transport sector. While this novel technology holds immense potential, its integration raises new and unique airworthiness concerns. The present activity aims to support the development of aircraft certification requirements for structural batteries. Recognizing the dual nature of this technology, the proposed approach seeks to maintain or even enhance the current level of safety in both normal and emergency flight conditions.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"104 1","pages":"59 - 65"},"PeriodicalIF":0.0,"publicationDate":"2024-03-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-024-00207-7.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140232916","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

Rans Transition Model Predictions on Hypersonic Three-Dimensional Forebody Configuration

Aerotecnica Missili & Spazio Pub Date : 2024-03-05 DOI: 10.1007/s42496-024-00201-z

Luigi Cutrone, Antonio Schettino

引用次数: 0