Aerotecnica Missili & Spazio最新文献_第5页

Hygrothermal Effects in Aeronautical Composite Materials Subjected to Freeze–Thaw Cycling 航空复合材料在冻融循环下的湿热效应

Aerotecnica Missili & Spazio Pub Date : 2023-12-14 DOI: 10.1007/s42496-023-00190-5

Pietro Aceti, Christian Bianchi, Giuseppe Sala

{"title":"Hygrothermal Effects in Aeronautical Composite Materials Subjected to Freeze–Thaw Cycling","authors":"Pietro Aceti, Christian Bianchi, Giuseppe Sala","doi":"10.1007/s42496-023-00190-5","DOIUrl":"10.1007/s42496-023-00190-5","url":null,"abstract":"<div><p>Fiber-reinforced composites (FRC) have gained widespread recognition in the aerospace, automotive, and energy industries due to their exceptional strength to-weight ratio. However, comprehending their performance within varying environmental contexts poses a multifaceted challenge. Specifically, the influence of humidity, temperature fluctuations, and freeze–thaw cycles on the structural integrity of FRC components requires careful examination. This research work seeks to provide insights into the effects of humidity, temperature, and freeze thaw cycles on FRC inter-laminar regions and the critical matrix/fiber interface. The experimental methodology employed includes a comprehensive array of techniques, such as thermal analysis, X-Ray tomography, and ILSS mechanical testing. Through these methods, an effort is made to discern the material’s response to the environmental variables. Carbon-reinforced composites exhibited a shear strength reduction of 16.9% at 80 °C, and glass-reinforced composites displayed a reduction of 18.4%. Further increasing the temperature to 125 °C resulted in a reduction of 32.5% for carbon-reinforced composites and 38.8% for glass-reinforced composites. In hot-wet conditions, which combine humidity saturation and a testing temperature of 80 °C, the shear strength reductions were the most pronounced, with a reduction of 48.7% for carbon-reinforced composites and 60.2% for glass-reinforced composites. Moreover, freeze–thaw cycle has been performed. The findings of this research endeavor hold profound implications for both the design and maintenance of FRC components. As FRCs continue to gain prominence in critical applications, an enhanced understanding of their behavior in diverse environmental conditions becomes increasingly imperative.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 3","pages":"255 - 267"},"PeriodicalIF":0.0,"publicationDate":"2023-12-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138974797","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

Orbit/Attitude Control for Rendezvous and Docking at the Herschel Space Observatory 赫歇尔空间天文台交会对接的轨道/高度控制

Aerotecnica Missili & Spazio Pub Date : 2023-12-13 DOI: 10.1007/s42496-023-00188-z

Andrea Siena

{"title":"Orbit/Attitude Control for Rendezvous and Docking at the Herschel Space Observatory","authors":"Andrea Siena","doi":"10.1007/s42496-023-00188-z","DOIUrl":"10.1007/s42496-023-00188-z","url":null,"abstract":"<div><p>In situ resource utilization (ISRU) will be the key for the success of many future space missions which are especially time or cost demanding. This is particularly true for the next Moon settlement mankind has decided to establish, and even further, for Mars colonization. Focusing on Moon operations, this paper presents a study carried out to assess the benefits of on-orbit servicing (OOS) exploiting lunar resources for the resupply of the Herschel Space Observatory (HSO). Herschel ended its operations in 2013 as a consequence of the depletion of its coolant, therefore an experimental mission has been envisaged to refill it. An adapted cargo spacecraft (s/c), employed in lunar gateway operations, will be supposed to depart from the Moon and reach Herschel for the resupply. Trajectory design and optimization for rendezvous, as well as attitude control and a methodology to simplify the dynamics equations through linearization, are the topics addressed in this study in order to obtain some preliminary data on the feasibility of these kind of missions. The results found list different trajectories that could be taken on for the mission, their <span>(Delta)</span>V cost and time of flight (ToF) and show the advantage of relying on simplified dynamics for the calculations. Moreover, it is presented the methodology used to approach the observatory during rendezvous (RdV) while ensuring minimum thrusting errors of the cargo spacecraft and a continuous visibility of the space observatory. The conclusion displays some ideas on how the next studies for the mission could be carried on.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 1","pages":"39 - 49"},"PeriodicalIF":0.0,"publicationDate":"2023-12-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139006309","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

Optimal pure-pursuit missile guidance 最佳纯导弹制导

Aerotecnica Missili & Spazio Pub Date : 2023-11-30 DOI: 10.1007/s42496-023-00185-2

Ilan Rusnak

{"title":"Optimal pure-pursuit missile guidance","authors":"Ilan Rusnak","doi":"10.1007/s42496-023-00185-2","DOIUrl":"10.1007/s42496-023-00185-2","url":null,"abstract":"<div><p>The endeavor of the pure-pursuit guidance is aligning the missile velocity vector with the line-of-sight to the target. The classical pure-pursuit guidance is not the preferred choice for a guidance law as it does not perform well against moving targets. Albeit this, its appealing feature and the main advantage are that it needs measurement of angle only for implementation, thus reducing the cost at the price of the performance. To this day, the implemented guidance law for classical pure-pursuit is mostly a constant proportional control law, and acceptable miss distance is achieved for stationary and very slow targets, thus the use for engagement of moving targets is limited. This paper's objective is to use the optimal control theory in the design of the guidance law for pure-pursuit guidance and to assess the performance against non-stationary/moving targets and deterministic disturbances. The main conclusion is that applying the optimal control theory to design optimal guidance laws for pure pursuit improves performance and reduces the miss distance below a meter for a moderate target’s velocity. The Optimal Pure-Pursuit Guidance Law for stationary targets is shown to realize the Proportional Navigation guidance law.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 1","pages":"51 - 60"},"PeriodicalIF":0.0,"publicationDate":"2023-11-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139198070","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

Estimation of the Thermophysical Properties of C/C Plates with Ceramic Nanocoating at Different SiO2 Filling for Aerospace Applications 不同二氧化硅填充量下带有陶瓷纳米涂层的 C/C 板在航空航天应用中的热物理性能估算

Aerotecnica Missili & Spazio Pub Date : 2023-11-27 DOI: 10.1007/s42496-023-00187-0

A. V. Morzhukhina, O. M. Alifanov, S. A. Budnik, A. V. Nenarokomov, D. M. Titov, A. Delfini, R. Pastore, F. Santoni, M. Albano, M. Marchetti

{"title":"Estimation of the Thermophysical Properties of C/C Plates with Ceramic Nanocoating at Different SiO2 Filling for Aerospace Applications","authors":"A. V. Morzhukhina, O. M. Alifanov, S. A. Budnik, A. V. Nenarokomov, D. M. Titov, A. Delfini, R. Pastore, F. Santoni, M. Albano, M. Marchetti","doi":"10.1007/s42496-023-00187-0","DOIUrl":"10.1007/s42496-023-00187-0","url":null,"abstract":"<div><p>In aerospace industrial and commercial scenario, the reusable launch vehicles (RLV) evolution works constantly toward the lowering of payload conveyance expenses. The thermal protection system (TPS) preserves the integrity of the space vehicle surfaces exposed to huge thermal shock during the re-entry phase: its advanced design and manufacturing, aimed at both reusing and withstanding harsh space environment, result in increasing the production and maintenance charges. The present study introduces a cost-saving concept of TPS component made of carbon/carbon (C/C) tiles coated by a commercial refractory varnish reinforced with ceramic nanoparticles. Using a reliable computing method, known as inverse method, the thermophysical properties such as heat capacity and thermal conductivity of the manufactured materials are assessed in a broad range of temperatures, with the input aid of an in-house developed experimental setup. The described technique is especially suited for approaching such kind of issues, thanks to the capability of taking into account several physical variables simultaneously, with the aim of gaining a robust knowledge of materials’ thermal behavior for potential use in spacecraft TPS.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 1","pages":"3 - 15"},"PeriodicalIF":0.0,"publicationDate":"2023-11-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-023-00187-0.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139228289","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

Preliminary Study of the Effects of Different Drag Laws on Ice Crystal Impingement on Probes Mounted on a Fuselage 不同阻力定律对安装在机身上的探头上冰晶撞击效果的初步研究

Aerotecnica Missili & Spazio Pub Date : 2023-11-20 DOI: 10.1007/s42496-023-00184-3

A. Carozza, P. L. Vitagliano, G. Mingione

引用次数: 0

Simulation of In-Space Fragmentation Events 模拟空间碎片事件

Aerotecnica Missili & Spazio Pub Date : 2023-11-15 DOI: 10.1007/s42496-023-00186-1

Lorenzo Olivieri, Cinzia Giacomuzzo, Stefano Lopresti, Alessandro Francesconi

{"title":"Simulation of In-Space Fragmentation Events","authors":"Lorenzo Olivieri, Cinzia Giacomuzzo, Stefano Lopresti, Alessandro Francesconi","doi":"10.1007/s42496-023-00186-1","DOIUrl":"10.1007/s42496-023-00186-1","url":null,"abstract":"<div><p>In the next years, the space debris population is expected to progressively grow due to in-space collisions and break-up events; in addition, anti-satellite tests can further affect the debris environment by generating large clouds of fragments. The simulation of these events allows identifying the main parameters affecting fragmentation and obtaining statistically accurate populations of generated debris, both above and below detection thresholds for ground-based observatories. Such information can be employed to improve current fragmentation models and to reproduce historical events to better understand their influence on the non-detectable space debris population. In addition, numerical simulation can also be used as input to identify the most critical objects to be removed to reduce the risk of irreversible orbit pollution. In this paper, the simulation of historical in-orbit fragmentation events is discussed and the generated debris populations are presented. The presented case-studies include the COSMOS-IRIDIUM collision, the COSMOS 1408 anti-satellite test, the 2022-151B CZ-6A in-orbit break-up, and a potential collision of ENVISAT with a spent rocket stage; for these events, results are presented in terms of cumulative fragments distributions and debris orbital distributions.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 3","pages":"225 - 232"},"PeriodicalIF":0.0,"publicationDate":"2023-11-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-023-00186-1.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142411984","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

Application of Optimal Control Techniques to the Parafoil Flight of Space Rider 将优化控制技术应用于太空骑手的伞翼飞行

Aerotecnica Missili & Spazio Pub Date : 2023-11-14 DOI: 10.1007/s42496-023-00176-3

Michele Lucrezia

{"title":"Application of Optimal Control Techniques to the Parafoil Flight of Space Rider","authors":"Michele Lucrezia","doi":"10.1007/s42496-023-00176-3","DOIUrl":"10.1007/s42496-023-00176-3","url":null,"abstract":"<div><p>The Space Rider program falls within the framework of ESA activities for the design of affordable and sustainable reusable aerospace vehicles. Among the greatest challenges for this mission is the design of the Guidance, Navigation and Control (GNC) subsystem for the re-entry phase. The final stage of the latter consists of an autonomous flight under parafoil that must guarantee a smooth and precise landing. To ensure compliance with the requirements in terms of landing accuracy and ground speed constraints at touchdown, the GNC subsystem must be able to counterbalance the effect of the wind during the flight and guarantee an upwind landing. A key role in this regard is played by what is commonly referred to as the Terminal Guidance phase i.e., the final part of the descent under parafoil where the vehicle performs the final approach to the designated landing point. The study presented in this work has been developed at the AOCS/GNC department of SENER Aeroespacial and the objective is to design a complete solution for managing the Terminal Guidance phase of a Space Rider-type case. This includes a guidance algorithm based on a direct method to generate an optimal solution for the trajectory, a path-tracking procedure, and a guidance logic that allows for a correct implementation within the whole GNC software. The optimal terminal guidance algorithm has then been implemented within the six-degrees-of-freedom simulator developed by SENER Aeroespacial demonstrating an excellent functioning for the proposed problem.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 2","pages":"117 - 128"},"PeriodicalIF":0.0,"publicationDate":"2023-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134991236","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

Analysis of Collision Avoidance Manoeuvres Using Aerodynamic Drag for the Flying Laptop Satellite 利用气动阻力分析飞行笔记本电脑卫星的防撞机动性能

Aerotecnica Missili & Spazio Pub Date : 2023-11-11 DOI: 10.1007/s42496-023-00183-4

Fabrizio Turco, Constantin Traub, Steffen Gaißer, Jonas Burgdorf, Sabine Klinkner, Stefanos Fasoulas

{"title":"Analysis of Collision Avoidance Manoeuvres Using Aerodynamic Drag for the Flying Laptop Satellite","authors":"Fabrizio Turco, Constantin Traub, Steffen Gaißer, Jonas Burgdorf, Sabine Klinkner, Stefanos Fasoulas","doi":"10.1007/s42496-023-00183-4","DOIUrl":"10.1007/s42496-023-00183-4","url":null,"abstract":"<div><p>Collision avoidance is a topic of growing importance for any satellite orbiting Earth. Especially those satellites without thrusting capabilities face the problem of not being able to perform impulsive collision avoidance manoeuvres. For satellites in low Earth orbits, though, perturbing accelerations due to aerodynamic drag may be used to influence their trajectories, thus offering a possibility to avoid collisions without consuming propellant. Here, this manoeuvring option is investigated for the satellite <i>Flying Laptop</i> of the University of Stuttgart, which orbits the Earth at approximately <span>({600},{textrm{km}})</span>. In a first step, the satellite is aerodynamically analysed making use of the tool ADBSat. By employing an analytic equation from the literature, in-track separation distances can then be derived following a variation of the ballistic coefficient through a change in attitude. A further examination of the achievable separation distances proves the feasibility of aerodynamic collision avoidance manoeuvres for the <i>Flying Laptop</i> for moderate and high solar and geomagnetic activity. The predicted separation distances are further compared to flight data, where the principle effect of the manoeuvre on the satellite trajectory becomes visible. The results suggest an applicability of collision avoidance manoeuvres for all satellites in comparable and especially in lower orbits than the <i>Flying Laptop</i>, which are able to vary their ballistic coefficient.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 1","pages":"61 - 71"},"PeriodicalIF":0.0,"publicationDate":"2023-11-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-023-00183-4.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135041984","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

AIDAA News #20 AIDAA 新闻 #20

Aerotecnica Missili & Spazio Pub Date : 2023-11-04 DOI: 10.1007/s42496-023-00179-0

Michele Guida

引用次数: 0

Modelling the Wall Pressure Fluctuations on the VEGA-C Launcher in Supersonic Conditions 超音速条件下 VEGA-C 发射器壁压波动建模

Aerotecnica Missili & Spazio Pub Date : 2023-10-25 DOI: 10.1007/s42496-023-00181-6

R. Camussi, Alessandro Di Marco, Elisa De Paola, Gerorgiana Luana Stoica, Cornelius Stoica, Fabio Paglia, Luca Romano, Daniele Barbagallo

{"title":"Modelling the Wall Pressure Fluctuations on the VEGA-C Launcher in Supersonic Conditions","authors":"R. Camussi, Alessandro Di Marco, Elisa De Paola, Gerorgiana Luana Stoica, Cornelius Stoica, Fabio Paglia, Luca Romano, Daniele Barbagallo","doi":"10.1007/s42496-023-00181-6","DOIUrl":"10.1007/s42496-023-00181-6","url":null,"abstract":"<div><p>The prediction of pressure fluctuations generated over the external surface of aerospace launchers during the atmospheric flight remains a challenging task due to the complexity of the geometry and the effects of compressibility at high supersonic Mach numbers. An experimental database is here analysed to the scope of providing a procedure to model and predict the relevant statistics of the wall pressure fluctuations generated by a supersonic flow overflowing the VEGA-C Launcher Vehicle. Data have been obtained in an extensive Wind Tunnel test campaign carried out in the trisonic wind tunnel of the National Institute for Aerospace Research (INCAS) in Bucharest. Wall-mounted pressure transducers allowed for the computation of the pressure Auto- and Cross-spectra over the fourth (the payload region) and third stages of the launcher model. Coherence functions are modelled through exponential-like analytical functions following the approaches usually adopted in canonical boundary layer flows, whereas the auto-spectra models are based on polynomial fits. The approach adopted for the achievement of proper non-dimensional quantities as well as the procedure implemented for the full-scale extrapolation is presented and discussed.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"103 1","pages":"73 - 81"},"PeriodicalIF":0.0,"publicationDate":"2023-10-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-023-00181-6.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134971804","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