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Re-entry predictions of space objects and impact on air traffic 空间物体再入预测及其对空中交通的影响
Materials Research Society symposia proceedings. Materials Research Society Pub Date : 2023-11-01 DOI: 10.21741/9781644902813-139
F. Bernelli-Zazzera
{"title":"Re-entry predictions of space objects and impact on air traffic","authors":"F. Bernelli-Zazzera","doi":"10.21741/9781644902813-139","DOIUrl":"https://doi.org/10.21741/9781644902813-139","url":null,"abstract":"Abstract. This work focuses on predicting the re-entry of an uncontrolled re-entry vehicle (RV) and how this affects air traffic. It includes the propagation of the nominal trajectory and that of the fragments resulting from the breakup of the object. The breakup does not occur at a fixed altitude but is a consequence of the thermal and dynamic loads acting on the RV as it re-enters the atmosphere. The purpose of the analysis is to identify a dangerous area at specific heights (flight levels) to be evacuated in time for air traffic. The hazard area is defined as that which includes all the impact points of the fragments at this altitude taking into account the additional safety margins. The study also considers the presence of uncertainties affecting the initial state of the vehicle. Accordingly, a Monte Carlo analysis is performed to predict the worst-case scenario and to better estimate the hazard area. Once the area has been defined, an evacuation algorithm calculates, for each aircraft, the trajectory changes necessary to clear or avoid the zone over time.","PeriodicalId":87445,"journal":{"name":"Materials Research Society symposia proceedings. Materials Research Society","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135116443","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
Dynamic buckling structural test of a CFRP passenger floor stanchion CFRP乘客地板支柱的动态屈曲结构试验
Materials Research Society symposia proceedings. Materials Research Society Pub Date : 2023-11-01 DOI: 10.21741/9781644902813-89
G. di Mauro
{"title":"Dynamic buckling structural test of a CFRP passenger floor stanchion","authors":"G. di Mauro","doi":"10.21741/9781644902813-89","DOIUrl":"https://doi.org/10.21741/9781644902813-89","url":null,"abstract":"Abstract. The work focuses on the study of the structural behavior of a composite floor beam in the cargo area of a commercial aircraft subjected to static and dynamic loads. Experimental tests have been performed in the laboratories of the Dept. of Industrial Engineering (UniNa) jointly with the development of numerical models suitable to correctly simulate the phenomenon through the LS-DYNA software. The definition of a robust numerical model allowed to evaluate the possibility of buckling triggering. The test article was equipped with potting supports on both ends of the tested beam, filling the pots with epoxy resin toughened with glass fiber nanoparticles. This allowed to uniformly load the beam ends in compression and to carry out the tests loading the specimen statically and dynamically, to observe the differences in the behavior of the beam in correspondence with the two different types of applied load. The result obtained through the comparison between the numerical model and the experimental test is that the dynamic buckling is triggered by a quantitatively smaller load than in the static case. Furthermore, it has been observed that the experimental compressive displacement to trigger the dynamic buckling instability is greater than the displacement observed in the static case.","PeriodicalId":87445,"journal":{"name":"Materials Research Society symposia proceedings. Materials Research Society","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135116444","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
Electro-thermal dynamic simulations and results of a deorbiting tethered system 脱轨系留系统的电热动力学模拟与结果
Materials Research Society symposia proceedings. Materials Research Society Pub Date : 2023-11-01 DOI: 10.21741/9781644902813-117
G. Anese
{"title":"Electro-thermal dynamic simulations and results of a deorbiting tethered system","authors":"G. Anese","doi":"10.21741/9781644902813-117","DOIUrl":"https://doi.org/10.21741/9781644902813-117","url":null,"abstract":"Abstract. Deorbiting techniques with small or better no propellant consumption are an important and critical field of space studies for the mitigation of orbital debris. Electrodynamic tethers (EDTs) are of particular interest because they make possible to deorbit space debris by exploiting the Lorentz force that is provided by the current flowing in the tether thanks to the interaction of the system with the Earth’s magnetosphere and the ionosphere. This paper focuses on the differences between two software packages built at the University of Padova (FLEX and FLEXSIM) and their results in simulating various deorbiting scenarios. Both FLEXSIM and FLEX simulate the electro-thermal behaviour and the dynamics of an EDT. However, while the first one has the simplifying assumption that the tether is always aligned with the local vertical, the second one considers also the overall system attitude with respect to the radial direction and the tether flexibility. The computational times of these S/W are very different and it is important to understand the scenarios that are more appropriate for their use. Results aim to show the impact of different solar activity (simulations are done at different epochs) and lengths of conductive and non conductive segments of tether, in the range of a few hundreds of meters, on the total re-entry time. As expected, deorbiting is faster for high solar activity and conductive tether length but the performance must be balanced against the dynamics stability. The issue of stability over the deorbiting time is evaluated numerically for specific cases by using FLEX.","PeriodicalId":87445,"journal":{"name":"Materials Research Society symposia proceedings. Materials Research Society","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135116445","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
On the influence of airframe flexibility on rotorcraft pilot couplings 机身柔性对旋翼机驾驶员联轴器的影响
Materials Research Society symposia proceedings. Materials Research Society Pub Date : 2023-11-01 DOI: 10.21741/9781644902813-6
C. Talamo
{"title":"On the influence of airframe flexibility on rotorcraft pilot couplings","authors":"C. Talamo","doi":"10.21741/9781644902813-6","DOIUrl":"https://doi.org/10.21741/9781644902813-6","url":null,"abstract":"Abstract. A set of numerical simulations of the interactional dynamics of the pilot-rotorcraft system is performed. The aim of the numerical analysis is to evaluate the stability of the closed-loop system in hovering conditions, focusing on the influence of the first airframe flexible mode, the one with the most participation in relative motion between the main rotor and the pilot’s seat and closest in frequency to pilot-vehicle interaction. Two approaches are employed. First, a linear analysis, in which the modal representation of the airframe flexible mode is added to a linearized model of the helicopter vertical motion and the helicopter dynamics is coupled with a single degree of freedom linearized model of the pilot biomechanics. Subsequently, a multibody model of the helicopter is coupled with the same linear model of the pilot, trimmed in hover and perturbed by a vertical gust. A sensitivity analysis shows that such mode has a significant influence on the stability of the closed loop system, especially if its frequency is close to the natural frequency of the pilot’s biomechanics, as one might expect.","PeriodicalId":87445,"journal":{"name":"Materials Research Society symposia proceedings. Materials Research Society","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135117451","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
Hygrothermal effects in aeronautical composite materials subjected to freeze-thaw cycling 冻融循环作用下航空复合材料的湿热效应
Materials Research Society symposia proceedings. Materials Research Society Pub Date : 2023-11-01 DOI: 10.21741/9781644902813-72
C. Bianchi
{"title":"Hygrothermal effects in aeronautical composite materials subjected to freeze-thaw cycling","authors":"C. Bianchi","doi":"10.21741/9781644902813-72","DOIUrl":"https://doi.org/10.21741/9781644902813-72","url":null,"abstract":"Abstract. Fiber-reinforced composites (FRC) are becoming increasingly popular in aerospace, automotive and energy sectors. Despite the advantages owed to their strength and lightweight, understanding their behavior in different environments poses challenges. Particularly, humidity, temperature, and freeze-thaw cycles can significantly affect the durability of FRC components. This study investigates the impact of humidity, temperature, and freeze-thaw cycles on FRC inter-laminar areas and the matrix/fiber interface. Experimental methods, including heat analysis, X-Ray tomography and mechanical testing will assess the material's response to changing environmental conditions. This research enhances our understanding of FRC behavior, crucial for designing and maintaining FRC components.","PeriodicalId":87445,"journal":{"name":"Materials Research Society symposia proceedings. Materials Research Society","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135117460","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
Comparison of LARES 1 and LARES 2 missions - one year after the launch LARES 1和LARES 2任务的比较——发射一年后
Materials Research Society symposia proceedings. Materials Research Society Pub Date : 2023-11-01 DOI: 10.21741/9781644902813-123
I. Ciufolini
{"title":"Comparison of LARES 1 and LARES 2 missions - one year after the launch","authors":"I. Ciufolini","doi":"10.21741/9781644902813-123","DOIUrl":"https://doi.org/10.21741/9781644902813-123","url":null,"abstract":"Abstract. The LARES 1 and LARES 2 missions were designed to test an intriguing phenomenon predicted by the theory of general relativity: the Lense-Thirring (frame-dragging) effect. In particular, the LARES 2 mission was designed with the goal of reaching an accuracy 10 times better than that obtained with LARES 1, launched 10 years earlier. To reach this demanding goal a special orbit and a specific satellite design was required. Knowledge of the gravitational field of Earth of ever-increasing accuracy, thanks to the Follow-on GRACE space mission together with the spectacular orbital injection accuracy provided by the Avio-ASI-ESA launcher VEGA C, will make possible an even better accuracy after a few years of data analysis. In this paper the two missions are compared along with the results obtained from the LARES 1 mission and those expected from LARES 2.","PeriodicalId":87445,"journal":{"name":"Materials Research Society symposia proceedings. Materials Research Society","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135117936","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
A boundary element method for thermo-elastic homogenization of polycrystals 多晶热弹性均匀化的边界元法
Materials Research Society symposia proceedings. Materials Research Society Pub Date : 2023-11-01 DOI: 10.21741/9781644902813-75
N. Fonzi
{"title":"A boundary element method for thermo-elastic homogenization of polycrystals","authors":"N. Fonzi","doi":"10.21741/9781644902813-75","DOIUrl":"https://doi.org/10.21741/9781644902813-75","url":null,"abstract":"Abstract. A computational framework for thermo-elastic homogenization of polycrystalline materials is proposed. The formulation is developed at the crystal level and it is based on the explicit Voronoi representation of the micro-morphology. The crystal thermo-elastic equations are formulated in an integral form and numerically treated through the boundary element method. The presence of volume integrals, induced by the inherent physics of the thermo-elastic coupling, is addressed through a Dual Reciprocity Method (DRM), which allows recasting the formulation in terms of boundary integrals only. The developed methodology is applied for estimating the homogenized thermo-elastic constants of two widely employed ceramic materials. The method may find applications in multiscale analysis of polycrystalline structural component.","PeriodicalId":87445,"journal":{"name":"Materials Research Society symposia proceedings. Materials Research Society","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135370226","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
Aerodynamic design of advanced rear end for large passenger aircraft 大型客机先进后端气动设计
Materials Research Society symposia proceedings. Materials Research Society Pub Date : 2023-11-01 DOI: 10.21741/9781644902813-96
S. Corcione
{"title":"Aerodynamic design of advanced rear end for large passenger aircraft","authors":"S. Corcione","doi":"10.21741/9781644902813-96","DOIUrl":"https://doi.org/10.21741/9781644902813-96","url":null,"abstract":"Abstract. This paper focuses on the aerodynamic design of an advanced rear end concept for a large passenger aircraft, such as the Airbus A320. The aim was to reduce the size of the horizontal tailplane to minimize the aerodynamic drawbacks related to longitudinal stability and control requirements. This reduction would lead to improved aircraft performance by reducing fuel burn and rear-end weight. Assuming the same position of the aerodynamic center of the horizontal tailplane of a conventional aircraft, the results of this investigation showed that the required stabilizing performance of the tail could be achieved with a smaller tail surface. A reduction of 6% in tail planform area was achieved by leveraging the unique aerodynamic characteristics of a forward-swept tail, combined with the implementation of a leading-edge extension device. The reduced wetted area and the lower weight of the horizontal empennage could result in fuel savings of 100 to 120 kg of fuel per 1,000 km. This is equivalent to approximately 1.0 to 1.2% for the specific aircraft category being considered.","PeriodicalId":87445,"journal":{"name":"Materials Research Society symposia proceedings. Materials Research Society","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135370279","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
Particle migration modeling in solid propellants 固体推进剂中的颗粒迁移模型
Materials Research Society symposia proceedings. Materials Research Society Pub Date : 2023-11-01 DOI: 10.21741/9781644902813-147
R. Andriulli
{"title":"Particle migration modeling in solid propellants","authors":"R. Andriulli","doi":"10.21741/9781644902813-147","DOIUrl":"https://doi.org/10.21741/9781644902813-147","url":null,"abstract":"Abstract. This work presents the development of an OpenFOAM solver to predict the migration of solid particles in concentrated suspensions under non-uniform shear flow. The solver modifies the pimpleFoam solver by implementing the conservation equation for particle volume fraction. It adapts the equation of motion for non-Newtonian flows and establishes a model for the viscous field using Krieger's correlation. The code is successfully validated by the experimental results from literature.","PeriodicalId":87445,"journal":{"name":"Materials Research Society symposia proceedings. Materials Research Society","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135370358","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
The application of modal effective mass for PCB friction lock compliance against spacecraft launch random vibration spectrum 模态有效质量在PCB摩擦锁柔度对航天器发射随机振动谱的应用
Materials Research Society symposia proceedings. Materials Research Society Pub Date : 2023-11-01 DOI: 10.21741/9781644902813-131
M. Wylie
{"title":"The application of modal effective mass for PCB friction lock compliance against spacecraft launch random vibration spectrum","authors":"M. Wylie","doi":"10.21741/9781644902813-131","DOIUrl":"https://doi.org/10.21741/9781644902813-131","url":null,"abstract":"Abstract. Modern spacecraft design requires high density, low mass, modular electronic system architectures. This format often utilises a common backplane with Printed Circuit Boards (PCBs) interconnects. Adaptable electronic systems, such as modular Data Acquisition (DAq) systems, allow for configuration via insertion and removal of modules to meet the mission requirements. Common methods to mechanically fix the PCB to the chassis are by using stand-offs, with the primary function to minimise displacement through structural rigidity and to provide strain relief to the electronic connectors. Other methods, such as PCB friction lock allow for strain relief, improved thermal grounding of the PCB to the chassis but also allows for easy insertion and removal of the PCBs. One disadvantage of this system is that the retention force of the PCB is carried by a friction lock device and under acceleration loads, typically experienced in the launch environment, may cause failure. This paper presents a method to establish compliance of PCB friction lock devices using modal Finite Element Analysis (FEA) to predict the resonant frequencies and their Mass Participation Factor (MPF). Using this data, it is proposed that the use of an adaptation of the Miles Equation along with an equivalent g-RMS estimation can be used to determine the Random Vibration Load Factors (RVLF). A comparison of the RVLF with the retention force of the friction lock device can then give insight to the friction joint compliance.","PeriodicalId":87445,"journal":{"name":"Materials Research Society symposia proceedings. Materials Research Society","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135370598","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
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