Aerotecnica Missili & Spazio最新文献_第6页

AstroDART: Astronomical Data Analysis and Recovery from Tracklets AstroDART:轨道数据分析和恢复

Aerotecnica Missili & Spazio Pub Date : 2023-09-13 DOI: 10.1007/s42496-023-00174-5

Joaquín G. López-Cepero

引用次数: 0

Safety and Accidents Involving Aircraft Manufactured from Polymer Composite Materials: A Review 高分子复合材料制造飞机的安全与事故:综述

Aerotecnica Missili & Spazio Pub Date : 2023-08-30 DOI: 10.1007/s42496-023-00170-9

Giovanni Di Giorgio

{"title":"Safety and Accidents Involving Aircraft Manufactured from Polymer Composite Materials: A Review","authors":"Giovanni Di Giorgio","doi":"10.1007/s42496-023-00170-9","DOIUrl":"10.1007/s42496-023-00170-9","url":null,"abstract":"<div><p>The aviation accident investigation process includes the detailed examination of the aircraft wreckage, as well as the analysis of both primary and secondary elements of the aircraft structure. This requires examination of the wreckage at the accident site, and is followed by additional analysis, often driven by the first results on the field. Therefore, one of the most important tasks of investigators is to determine the sequence of events of the accident. This means that much evidence should be collected to accurately determine the order in which events occurred. With regard to construction materials involved, the interpretation of fracture surfaces can provide very important information. However, metallic and composite structures demonstrate very different behaviors during the operative service, from corrosion and fatigue to fire and combustion resistance. This paper performs a literature review on the identification of failure mode, damage and safety of polymer composite aircraft structures from a point of view that may be useful to aviation safety investigations, with the aim to provide suggestions for future research.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"102 4","pages":"337 - 353"},"PeriodicalIF":0.0,"publicationDate":"2023-08-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-023-00170-9.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117224482","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

Simulation of High-Enthalpy Turbulent Shock Wave/Boundary Layer Interaction Using a RANS Approach 用RANS方法模拟高焓湍流激波/边界层相互作用

Aerotecnica Missili & Spazio Pub Date : 2023-08-30 DOI: 10.1007/s42496-023-00169-2

Davide Ninni, Francesco Bonelli, Giuseppe Pascazio

{"title":"Simulation of High-Enthalpy Turbulent Shock Wave/Boundary Layer Interaction Using a RANS Approach","authors":"Davide Ninni, Francesco Bonelli, Giuseppe Pascazio","doi":"10.1007/s42496-023-00169-2","DOIUrl":"10.1007/s42496-023-00169-2","url":null,"abstract":"<div><p>In the era of space exploration, the scientific community is strongly focusing on the analysis of hypersonic flows in the presence of shock wave/boundary layer interaction. In these conditions, the flow field presents a complex shock structure due to the interaction of different shock waves with the boundary layer. The strong adverse pressure gradient makes the boundary layer separate, giving rise to a separation bubble. In the reattachment zone, the temperature can reach very high values, inducing thermochemical non-equilibrium effects. This research field is recently achieving more and more relevance in aerospace research, as the analysis of turbulent shock wave/boundary layer interaction so far has been mainly focused on perfect gas flows. In this manuscript, a Reynolds averaged Navier–Stokes (RANS) approach is considered, the shear stress transport (SST) model being coupled with the multitemperature approach proposed by Park to investigate thermochemical non-equilibrium effects in hypersonic turbulent shock wave/boundary layer interaction. The first part of the manuscript is devoted to the validation of the solver, and results for low enthalpy flat plate and compression ramp flows are presented. The numerical results are shown to be in good agreement with numerical solutions and experimental measurements. Afterward, the free stream conditions are modulated to make non-equilibrium relevant and analyze a reacting flow.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"102 4","pages":"323 - 335"},"PeriodicalIF":0.0,"publicationDate":"2023-08-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-023-00169-2.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130425665","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 Ptolemaic Approach Improving the Conjunction Analysis Pipeline for Leo 一种改进Leo连接分析管道的托勒密方法

Aerotecnica Missili & Spazio Pub Date : 2023-08-21 DOI: 10.1007/s42496-023-00164-7

De Marchi Pietro

{"title":"A Ptolemaic Approach Improving the Conjunction Analysis Pipeline for Leo","authors":"De Marchi Pietro","doi":"10.1007/s42496-023-00164-7","DOIUrl":"10.1007/s42496-023-00164-7","url":null,"abstract":"<div><p>Low-Earth-Orbit (LEO) region congestion is becoming one of the big issues of the modern space era. To avoid the Kessler syndrome, now more than ever it is needed to improve awareness about space traffic, and upgrade the entire monitoring process. Extensive literature is available covering the topics of orbital conjunction filtering techniques and computation of the Minimum Orbital Intersection Distance (MOID). The present paper investigates Funding and/or Conflicts of interests/Conflict of interest. An alternative filtering method exploits the near-circularity of certain orbits (a condition often verified in LEO), to improve conjunction analysis performance. Elliptical orbits are reshaped through an auxiliary <i>deferent</i> model, inspired by C. Ptolemy’s orbital theory, replacing the real motion along conjunction analysis. To recover satellites’ averaged mean orbital elements, CelesTrack LEO catalogue was considered and propagated. Based on averaged parameters, off-centric circular orbits are considered instead of elliptical ones. The resulting deferents (off-centric circles) are not far from osculating orbits due to LEOs low eccentricities, becoming the basis for the conjunction analysis algorithm. The algorithm is conceived as a sequence of pre-filters and a final MOID computation. Performances are inspected through an all-vs-all analysis, taking as reference a combination of Hoots’ and Gronchi’s algorithms. This method achieves good performance as compared with these traditional benchmarks. Adopting this approach could reduce the time needed for a preliminary conjunction inspection during the first phases of the Collision Avoidance (CA) process, especially in LEO, where pre-filtering aims to reduce the number of orbit couples where precise MOID computation is needed.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"102 4","pages":"309 - 321"},"PeriodicalIF":0.0,"publicationDate":"2023-08-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129282508","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

High-order Accurate Beam Models Based on Discontinuous Galerkin Methods 基于不连续伽辽金方法的高阶精确光束模型

Aerotecnica Missili & Spazio Pub Date : 2023-08-18 DOI: 10.1007/s42496-023-00168-3

Vincenzo Gulizzi, Ivano Benedetti, Alberto Milazzo

{"title":"High-order Accurate Beam Models Based on Discontinuous Galerkin Methods","authors":"Vincenzo Gulizzi, Ivano Benedetti, Alberto Milazzo","doi":"10.1007/s42496-023-00168-3","DOIUrl":"10.1007/s42496-023-00168-3","url":null,"abstract":"<div><p>A novel high-order accurate approach to the analysis of beam structures with bulk and thin-walled cross-sections is presented. The approach is based on the use of a variable-order polynomial expansion of the displacement field throughout both the beam cross-section and the length of the beam elements. The corresponding weak formulation is derived using the symmetric Interior Penalty discontinuous Galerkin method, whereby the continuity of the solution at the interface between contiguous elements as well as the application of the boundary conditions is weakly enforced by suitably defined boundary terms. The accuracy and the flexibility of the proposed approach are assessed by modeling slender and short beams with standard square cross-sections and airfoil-shaped thin-walled cross-sections subjected to bending, torsional and aerodynamic loads. The comparison between the obtained numerical results and those available in the literature or computed using a standard finite-element method shows that the present method allows recovering three-dimensional distributions of displacement and stress fields using a significantly reduced number of degrees of freedom.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"102 4","pages":"293 - 308"},"PeriodicalIF":0.0,"publicationDate":"2023-08-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-023-00168-3.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132855875","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: 1

An Application of the Functional Resonance Analysis Method (FRAM) to Risk Assessment of Low-Speed Helicopter Operations to Avoid the Aerodynamic Phenomenon Known as Vortex Ring State 功能共振分析法（FRAM）在低速直升机运行风险评估中的应用以避免涡环状态的气动现象

Aerotecnica Missili & Spazio Pub Date : 2023-08-08 DOI: 10.1007/s42496-023-00166-5

Giovanni Di Giorgio

{"title":"An Application of the Functional Resonance Analysis Method (FRAM) to Risk Assessment of Low-Speed Helicopter Operations to Avoid the Aerodynamic Phenomenon Known as Vortex Ring State","authors":"Giovanni Di Giorgio","doi":"10.1007/s42496-023-00166-5","DOIUrl":"10.1007/s42496-023-00166-5","url":null,"abstract":"<div><p>This paper presents an application of the functional resonance analysis method (FRAM) to the risk assessment of low-speed legs of a helicopter flight mission. A combination of low forward speed and a specific rate of vertical descent could lead to meet a region of the helicopter’s flight envelope that shall be avoided to prevent the vortex ring state, an aerodynamic phenomenon which could cause uncontrolled high rates of descent. A fully developed vortex ring state (VRS) is characterized by an unstable situation in which the helicopter experiences uncommanded pitch and roll oscillations, with a reduced or no collective authority, and a helicopter descent rate that may approach more than 5000 feet per minute. If the recognition of VRS signs is performed early by the pilot in a condition of sufficient altitude, then the required recovery may be performed. However, some mission legs require to descend close to the ground, as the case of a firefighting mission, in which one of the fundamental task requires to fill a tank with water. This type of mission has been selected as the case study of this paper, and a qualitative risk assessment is performed using FRAM. The model developed using FRAM is systemic, where both accidents and successes are seen to emerge in the system from combinations of normal variability. Moreover, the model is complex and non-linear, providing a complete overview of functions and tasks performed by the whole system and the related couplings. The paper presents the potential events related to the mission selected and provides results in terms of possible safety barriers.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"102 3","pages":"233 - 255"},"PeriodicalIF":0.0,"publicationDate":"2023-08-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50461452","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

Assessment of New Adaptive Finite Elements Based on Carrera Unified Formulation for Meshes with Arbitrary Polygons 基于Carrera统一公式的任意多边形网格自适应有限元评估

Aerotecnica Missili & Spazio Pub Date : 2023-08-08 DOI: 10.1007/s42496-023-00165-6

M. Cinefra, A. Rubino

{"title":"Assessment of New Adaptive Finite Elements Based on Carrera Unified Formulation for Meshes with Arbitrary Polygons","authors":"M. Cinefra, A. Rubino","doi":"10.1007/s42496-023-00165-6","DOIUrl":"10.1007/s42496-023-00165-6","url":null,"abstract":"<div><p>The meshing technique represents the capability to discretize the domain of interest, to fit the real physical continuum in the best possible way. The most used approach is the finite-element method (FEM), a numerical method to solve partial differential equations. To overcome the classical issues presented by FEM, other models are investigated. The goal is to allow the problem domain to be discretized by elements represented by arbitrary polygons, which can be concave and convex. Moreover, different polynomial consistency is sought within these methods with the possibility to handle non-conforming discretizations, mainly for local refinement and so on. This work aims to present the new adaptive elements, which are finite elements based on Carrera unified formulation, to demonstrate that all the previous capabilities can be done with these new elements, with easy implementation of the relative model. First, a classical patch test is done to investigate the mesh distortion sensitivity. Then, different study cases are presented with more complex meshes combining very distorted concave and convex elements.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"102 4","pages":"279 - 292"},"PeriodicalIF":0.0,"publicationDate":"2023-08-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-023-00165-6.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134031053","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 #19 AIDAA新闻#19

Aerotecnica Missili & Spazio Pub Date : 2023-07-18 DOI: 10.1007/s42496-023-00162-9

Marco Petrolo

引用次数: 0

ADCS Design for a Sounding Rocket with Thrust Vectoring 推力矢量探空火箭的ADCS设计

Aerotecnica Missili & Spazio Pub Date : 2023-07-08 DOI: 10.1007/s42496-023-00161-w

Pedro dos Santos, Paulo Oliveira

{"title":"ADCS Design for a Sounding Rocket with Thrust Vectoring","authors":"Pedro dos Santos, Paulo Oliveira","doi":"10.1007/s42496-023-00161-w","DOIUrl":"10.1007/s42496-023-00161-w","url":null,"abstract":"<div><p>This paper addresses the development of an attitude determination and control system (ADCS) for a sounding rocket using thrust vector control (TVC). To design the ADCS, a non-linear 6 degrees-of-freedom (DoF) model for the rocket dynamics and kinematics is deduced and implemented in simulation environment. An optimal attitude controller is designed using the linear quadratic regulator (LQR) with an additional integral action (LQI), and relying on the derived linear, time-varying, state-space representation of the rocket. The controller is tested in the simulation environment, demonstrating satisfactory attitude tracking performance, and robustness to model uncertainties. A navigation system is designed, based on measurements available on-board, to provide accurate real-time estimates on the rocket’s state and on the aerodynamic forces and moments acting on the vehicle. These aerodynamic estimates are used by an adaptive version of the controller that computes the gains in real time after correcting the state-space model. Finally, the ADCS is the result of the integration of the attitude control and navigation systems, with the complete system being implemented and tested in simulation, and demonstrating satisfactory performance.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"102 3","pages":"257 - 270"},"PeriodicalIF":0.0,"publicationDate":"2023-07-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-023-00161-w.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50014724","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

The Effect of Impeller Tip Clearance on the Performance of a MGT Mixed Flow Compressor Stage Fitted with a Crossover Diffuser 叶轮叶尖间隙对带交叉扩压器的MGT混流压气机级性能的影响

Aerotecnica Missili & Spazio Pub Date : 2023-06-24 DOI: 10.1007/s42496-023-00160-x

Hano van Eck, S. J. van der Spuy, A. J. Gannon

{"title":"The Effect of Impeller Tip Clearance on the Performance of a MGT Mixed Flow Compressor Stage Fitted with a Crossover Diffuser","authors":"Hano van Eck, S. J. van der Spuy, A. J. Gannon","doi":"10.1007/s42496-023-00160-x","DOIUrl":"10.1007/s42496-023-00160-x","url":null,"abstract":"<div><p>Mixed flow compressor stage designs are becoming increasingly popular for use in Micro Gas Turbine (MGT) engines. Due to manufacturing constraints and structural considerations, such compressors typically feature unshrouded impeller designs. A numeric investigation of the effect of impeller-shroud tip clearance on the performance of a MGT mixed flow compressor stage fitted with a crossover diffuser is presented. Three baseline test compressors are designed using an in-house-developed application based on one-dimensional mean line theory. These cover a wide range of design mass flow rates, design speeds, and impeller meridional exit (mixed flow) angles. The performance of each of the test compressors are evaluated at an impeller-shroud tip clearance of 0.1 mm, 0.3 mm, and 0.6 mm. Commercial CFD software is used to verify the performance results of the various test compressor configurations. It is found that an increase in impeller tip clearance negatively impacts both compressor performance (total-to-total pressure ratio and efficiency) and choke margin. Conversely, stall margin increases with an increase in impeller tip clearance.</p></div>","PeriodicalId":100054,"journal":{"name":"Aerotecnica Missili & Spazio","volume":"102 3","pages":"219 - 231"},"PeriodicalIF":0.0,"publicationDate":"2023-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42496-023-00160-x.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50045727","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