Aerospace Systems最新文献

{"title":"A survey on synthetic jets as active flow control","authors":"D. Sai Naga Bharghava,&nbsp;Tamal Jana,&nbsp;Mrinal Kaushik","doi":"10.1007/s42401-024-00301-5","DOIUrl":"10.1007/s42401-024-00301-5","url":null,"abstract":"<div><p>Synthetic jets (SJs) are becoming increasingly popular in aerospace engineering due to their potential applications in flow mixing enhancement, boundary layer control, and thermal load reduction. These pulsating jets involve the periodic motion of fluid in and out of a cavity through an orifice generated by a vibrating diaphragm at the cavity base. SJs are unique because they comprise working fluid and do not require an external fluid source, setting them apart from conventional flow control techniques. Although the net mass flux is zero in a complete cycle, there is a finite net momentum flux due to the imbalanced flow conditions across the orifice, and hence SJs are also known as Zero Net Mass Flux (ZNMF) jets. Numerous experimental and numerical studies have evaluated the efficacy of SJs in controlling the flow and heat transfer characteristics under various conditions, including quiescent and cross-flow situations. This review provides a comprehensive overview of the progress in synthetic jet applications in the last 40 years, specifically focusing on their potential use in flow control, heat transfer, and related applications in aerospace engineering. The strengths and limitations of SJs are discussed, and critical areas are identified for future research and development, including further optimization and refinement of these unique jets.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 3","pages":"435 - 451"},"PeriodicalIF":0.0,"publicationDate":"2024-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141000898","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}

{"title":"Deconvolution of mode composition beamforming for rotating source localization","authors":"Ce Zhang,&nbsp;Wei Ma","doi":"10.1007/s42401-024-00297-y","DOIUrl":"10.1007/s42401-024-00297-y","url":null,"abstract":"<div><p>Mode composition beamforming (MCB) is a frequency-domain rotating beamforming method for rotating acoustic source localization. Compared with other rotating beamforming methods, MCB has both wide applicability and high computational efficiency. The expression for MCB in literature is however not suitable for the application of deconvolution algorithms, which limits further improvements of dynamic range and spatial resolution of MCB. In this work, application of deconvolution algorithms to MCB is investigated. Firstly, the expression of MCB is transformed into a matrix form. Then the deconvolution algorithms of MCB, including DAMAS and CLEAN-SC, are derived based on the matrix form of MCB. Nextly the deconvolution algorithms of MCB are verified through a benchmark simulation case. Lastly deconvolution algorithms of MCB are applied in a phased array measurement for the rotor of an unmanned aerial vehicle to improve the dynamic range and spatial resolution of rotating source localization.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 4","pages":"727 - 734"},"PeriodicalIF":0.0,"publicationDate":"2024-05-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-024-00297-y.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141008403","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}

{"title":"Computational study on effect of free-stream turbulence on bio-inspired corrugated airfoil at different sections at low Reynolds number","authors":"N. S. Divyasharada,&nbsp;Vikas Kumar,&nbsp;Ganapati N. Joshi","doi":"10.1007/s42401-024-00296-z","DOIUrl":"10.1007/s42401-024-00296-z","url":null,"abstract":"<div><p>During flight, dragonfly wings can be thought of as an extreme light-weight airfoil. Many of the flight properties of tiny dragonfly wings are also shared by micro aerial vehicles (MAVs), which are nowadays finding widespread use in military and other commercial applications. It is observed that dragonflies have distinct cross-sectional corrugation that function to produce different local-aerodynamic characteristics. Along the wing’s longitudinal axis, there are significant variations in corrugation profile which adapts to different flight condition accordingly. Dragonflies fly in the extremely low-Reynolds-number zone, showcasing their outstanding flying characteristics even in turbulent conditions. The current study focuses on understanding the effect of free-stream turbulence on three distinct 2D corrugation profile located at 0.3, 0.5, 0.7 relative to wing span length during dragonfly’s gliding phase. The corrugation pattern required for computational analysis was designed in CATIA and imported to the commercially available CFD software ANSYS. The computational study is conducted on 2D, static non-flapping three corrugated profile at 10,000 Reynolds number subject to turbulence intensity of 0.5%, 1–10% at various angle of attack. This study examines the aerodynamic performance of each corrugation profile. The current numerical analysis shows that at a positive angle of attack, the increase in the lift coefficient remains largely unaffected by the corrugated pattern on the wing’s suction area. Virtual airfoils are created by rotating vortices that are trapped in profile valleys of corrugation patterns.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 1","pages":"219 - 235"},"PeriodicalIF":0.0,"publicationDate":"2024-05-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-024-00296-z.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141017941","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}

{"title":"Anchored to features: an image-feature-aware planner for stable visual localization","authors":"Senmao Li,&nbsp;Chengxi Zhang,&nbsp;Jiaolong Wang,&nbsp;Jin Wu,&nbsp;Lining Tan,&nbsp;Peng Dong","doi":"10.1007/s42401-024-00298-x","DOIUrl":"10.1007/s42401-024-00298-x","url":null,"abstract":"<div><p>This paper presents an image-feature-aware (IFA) planner for quadrotors, which integrates image feature tracking into its path-planning framework. The IFA-planner aims to improve the visual localization performance of quadrotors in multifarious environments where feature points may be sparse or diverse. Unlike traditional methods that decouple visual localization and path planning, the IFA-planner adaptively identifies and tracks feature-rich spatial units, called anchors, along a feasible path. The anchors provide additional feature points to the visual localization module, especially in scenarios with sparse or uneven features, thus enhancing localization robustness. Via clustering-based method, the anchor selection can handle different feature point distributions without manual tuning. Moreover, a detachment prediction mechanism is incorporated to convert the selected anchors into yaw constraints and update them according to the quadrotor’s predicted state. This mechanism ensures the environmental adaptability of the anchors and avoids sudden feature changes. The effectiveness of the IFA-planner is demonstrated in simulation experiments. The source code has been released at https://github.com/ximuzi2023/IFA-planner.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 4","pages":"735 - 745"},"PeriodicalIF":0.0,"publicationDate":"2024-04-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142519119","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}

{"title":"Quantitative analysis of hazardous areas in a micro downburst 3D wind field","authors":"Wenrui Jin,&nbsp;Tao Zhang,&nbsp;Xiaoxiao Lv,&nbsp;Jiaxue Li,&nbsp;Wei Li,&nbsp;Fandong Meng","doi":"10.1007/s42401-024-00288-z","DOIUrl":"10.1007/s42401-024-00288-z","url":null,"abstract":"<div><p>Microburst is a common low-level wind shear weather, and it seriously threatens the safety of civil aviation flights. It is characterized by suddenness, short duration, small scale and large intensity, which leads to difficulties in accurately obtaining real data, in real-time assessing the degree of harm. In this paper, based on the characteristics of microburst, according to computational fluid dynamics, taking into account the changes of temperature and pressure with height, establish a three-dimensional wind field simulation model, and verify the validity of the model by experimental data. Using the F-factor, construct the quantitative model of each position in the wind shear region, and analyze the danger degree of the micro downwash storm flow. Investigate the influence of inlet velocity, inlet height and inlet diameter on the hazard radius, and the simulation results show that the hazard radius increases logistically with the decrease of altitude, and when the inlet velocity increases by 5 m/s or the inlet height increases by 80 m, the hazard radius increases by about 10% on average. The method of this paper can provide a new way to quantitatively analyze the wind field characteristics of micro downburst storms.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 3","pages":"453 - 463"},"PeriodicalIF":0.0,"publicationDate":"2024-04-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142414757","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}

{"title":"Optimal control model as an approach to the synthesis of a supersonic transport control system","authors":"Ilias Kh. Irgaleev,&nbsp;Aleksandr V. Efremov,&nbsp;Alyona Yu. Grishina,&nbsp;Eugene V. Efremov","doi":"10.1007/s42401-024-00291-4","DOIUrl":"10.1007/s42401-024-00291-4","url":null,"abstract":"<div><p>The present article considers a modified optimal control model (MOCM) of the pilot. The main idea behind the proposed modification is moving the time delay element, initially located at the input of the model, to its output. Such relocation eliminates the need for introducing a “predictor” block to the model’s structure, which simplifies the algorithm for calculating the parameters of the optimal model. Besides a description of the modified algorithm, the paper assesses the agreement between the performance achieved using the algorithm and the results of experimental investigations. In addition, the results of modeling are compared to the results obtained using a structural model. The comparison is carried out for a model of a second-generation supersonic transport for this vehicle. The MOCM’s potential in evaluating alternative flight control system laws is discussed as well.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 1","pages":"117 - 124"},"PeriodicalIF":0.0,"publicationDate":"2024-04-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-024-00291-4.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140678453","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}

{"title":"Comparative evaluation of mathematical models of polymer composite material with the implementation of a three-dimensional stress–strain state in the simulation of impact","authors":"Aleksandr Bolshikh, K. Shelkov, Dmitry Borovkov, Nikolay Turbin","doi":"10.1007/s42401-024-00286-1","DOIUrl":"https://doi.org/10.1007/s42401-024-00286-1","url":null,"abstract":"","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":" 1225","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140681821","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}

{"title":"Comparative evaluation of the efficiency of manufacturing composite caisson panels of a wing/stabilizer for a medium-haul aircraft using automated laying and autoclave-free technologies","authors":"Fedor Nasonov,&nbsp;Pavel Milovanov,&nbsp;Razmik Melkonyan","doi":"10.1007/s42401-024-00294-1","DOIUrl":"10.1007/s42401-024-00294-1","url":null,"abstract":"<div><p>Polymer composite materials (PCM) are increasingly used in various fields of technology, primarily in the aviation industry, due to their high specific characteristics of structural properties and high manufacturability of molding methods for products of various functionality and undeniable advantages over traditional metal materials. The volume of PCM application in the airframe design of a number of modern and promising passenger aircraft is currently beginning to exceed 40% by weight and 80% by the area of the external contour of the aircraft. The development of automated technologies for laying out prepregs determines global trends in this direction, which consist in replacing traditional, manual methods of forming packages with automated methods of laying out. This gives significant advantages, such as a significant increase in the speed and accuracy of the process of laying out a semi-finished composite. The high demand for automation is due to increased requirements for the mechanical and precision characteristics of products. The key place in the article is given to determining the economic efficiency of methods of manufacturing composite parts for civil aviation equipment. The results of a comparative analysis of the technological cost of manufacturing parts from composite materials are presented, including assessment of the labor intensity of manufacturing work piece, material usage coefficients, share of manual labor, and degree of automation for polymer products through manual and automated technological calculations. It is shown that the use of automated technologies in the production of standard large-sized PCM panels makes it possible to reduce the consumption of basic materials by 15%, the labor intensity of manufacturing by 36% and the total manufacturing time by 28% compared to the existing level of pilot production. The key indicator of waste-free technological process (material utilization coefficient (MUC)) reaches values of 0.85–0.95.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 1","pages":"141 - 147"},"PeriodicalIF":0.0,"publicationDate":"2024-04-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-024-00294-1.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140687053","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}

{"title":"Damage prediction and failure mode analysis of composite aeroengine blade impacted by the breakstone","authors":"Xiaojing Zhang,&nbsp;Fangrui Yu","doi":"10.1007/s42401-024-00293-2","DOIUrl":"10.1007/s42401-024-00293-2","url":null,"abstract":"<div><p>Due to the excellent performance of carbon fiber-reinforced polymer (CFRP), they are widely used in the world's aircraft manufacturing industry, including aeroengine blades. During aircraft service, engine blades are often impacted by foreign objects such as breakstone, seriously affecting the airworthiness and safety of aircraft. Therefore, studying the impact resistance of carbon fiber composite materials is crucial for improving aircraft safety. In this paper, ABAQUS is used to establish a simulation model for impacting composite blades with breakstone. The VUMAT user subroutine is compiled to predict the damage of inner layer elements based on 3D-Hashin failure criterion and stiffness reduction scheme; cohesive elements based on the bilinear model are inserted between adjacent laminas to predict the delamination damage of the composite material. The damage initiation of cohesive elements is judged by QUADS criterion, and the damage evolution is performed using the B–K criterion of the energy method. Finally, based on the simulation results, the impact force, failure mode, and energy transformation during the impact process are analyzed.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 1","pages":"183 - 189"},"PeriodicalIF":0.0,"publicationDate":"2024-04-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140695266","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}

{"title":"Optimize design of composite laminate scarf patch repair by numerical analysis and experiments","authors":"Ziling Leng, Keyao Song, Xiangyu Liu, Yin Yu, Xiang Zhou","doi":"10.1007/s42401-024-00289-y","DOIUrl":"https://doi.org/10.1007/s42401-024-00289-y","url":null,"abstract":"","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"29 6","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140728101","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}