Progress in Aerospace Sciences最新文献

{"title":"Designing high aspect ratio wings: A review of concepts and approaches","authors":"Yiyuan Ma ,&nbsp;Ali Elham","doi":"10.1016/j.paerosci.2024.100983","DOIUrl":"https://doi.org/10.1016/j.paerosci.2024.100983","url":null,"abstract":"<div><p>In response to escalating environmental concerns and stringent economic constraints, there is an urgent need to develop aircraft technologies and configurations that substantially enhance efficiency. A prominent trend in aircraft design aimed at minimizing lift-induced drag, improving fuel efficiency, and mitigating emissions is the adoption of increased wing Aspect Ratio (AR). This paper examines the evolution and current advancements in High Aspect Ratio Wing (HARW) and Ultra-High Aspect Ratio Wing (UHARW) configurations for next-generation transport aircraft. Beginning with a historical overview of wing AR in transport, the paper examines the progress in designing both conventional and novel HARW/UHARW configurations. It reviews a range of promising concepts, such as strut-braced wing, truss-braced wing, twin-fuselage, and folding wingtips, for their potential in HARW applications. The paper emphasizes tailored conceptual design methods and tools specifically developed for HARW/UHARW configurations. It provides an in-depth analysis of preliminary design approaches for HARW aircraft, systematically covering aspects including aerodynamic, aeroelastic, aerostructural, and experimental designs. Key insights from leading-edge research are distilled, highlighting the significant advancements and pinpointing the current challenges in the field. The comprehensive review underscores the critical role of HARW/UHARW in enhancing aircraft performance, particularly in fuel efficiency and environmental impact, setting the stage for future transformative developments in aircraft efficiency.</p></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"145 ","pages":"Article 100983"},"PeriodicalIF":9.6,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139936657","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Artificial Intelligence for Trusted Autonomous Satellite Operations","authors":"Kathiravan Thangavel ,&nbsp;Roberto Sabatini ,&nbsp;Alessandro Gardi ,&nbsp;Kavindu Ranasinghe ,&nbsp;Samuel Hilton ,&nbsp;Pablo Servidia ,&nbsp;Dario Spiller","doi":"10.1016/j.paerosci.2023.100960","DOIUrl":"10.1016/j.paerosci.2023.100960","url":null,"abstract":"<div><p>Recent advances in Artificial Intelligence (AI) and Cyber-Physical Systems (CPS) for aerospace applications have brought about new opportunities for the fast-growing satellite industry. The progressive introduction of connected satellite systems and associated mission concepts is stimulating the development of intelligent CPS (iCPS) architectures, which can support high levels of flexibility and resilience in an increasingly congested near-Earth space environment. The need for higher levels of automation and autonomy in satellite operations has stimulated numerous research initiatives in recent years, focusing on the progressive enhancement of systemic performance (e.g., addressing safety, integrity and cyber-physical security metrics) and associated monitoring/augmentation approaches that can support Trusted Autonomous Satellite Operations (TASO). Despite these advances, in most contemporary satellite platforms, autonomy is restricted to a specific set of rules and cases, while the transition to TASO requires a paradigm shift in the design of both space vehicles and ground-based systems. In particular, the use of AI is seen as an essential enabler for TASO as it enhances system performance/adaptability and supports both predictive and reactive integrity augmentation capabilities, especially in Distributed Satellite Systems (DSS). This article provides a critical review of AI for satellite operations, with a special focus on current and likely future DSS architectures for communication, navigation and remote sensing missions. The aim is to identify key contemporary challenges and opportunities associated with space iCPS design methodologies to enhance the performance and resilience of satellite systems, supporting the progressive transition to TASO. A comprehensive review of relevant AI techniques is presented to critically assess the potential benefits and challenges of each method for different space applications. After describing the specificities of DSS and the opportunities offered by iCPS architectures, the co-evolution of space and control (ground and on-board) segments is highlighted as an essential next step towards enabling TASO. As an integral part of this evolutionary approach, the most important legal and regulatory challenges associated with the adoption of AI in TASO are also discussed.</p></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"144 ","pages":"Article 100960"},"PeriodicalIF":9.6,"publicationDate":"2023-12-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S0376042123000763/pdfft?md5=dac3f137aca3409077f6192f3d4d44f7&pid=1-s2.0-S0376042123000763-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139047625","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Thermal management challenges in hybrid-electric propulsion aircraft","authors":"Majid Asli ,&nbsp;Paul König ,&nbsp;Dikshant Sharma ,&nbsp;Evangelia Pontika ,&nbsp;Jon Huete ,&nbsp;Karunakar Reddy Konda ,&nbsp;Akilan Mathiazhagan ,&nbsp;Tianxiao Xie ,&nbsp;Klaus Höschler ,&nbsp;Panagiotis Laskaridis","doi":"10.1016/j.paerosci.2023.100967","DOIUrl":"10.1016/j.paerosci.2023.100967","url":null,"abstract":"<div><p>The utilization of hybrid electric propulsion concept in aviation offers a viable solution to address the limitations posed by the relatively low energy density of batteries in fully electric aviation. These hybrid systems enable the aircraft to achieve a significant range while simultaneously minimizing carbon emissions. While the individual components of a Hybrid Electric Propulsion (HEP) system, such as electric motors and batteries, are designed with high efficiency, their integration presents a significant challenge in the realm of thermal management. Designing an efficient system for managing the substantial waste heat generated by heat sources and effectively transferring it to heat sinks during various flight phases is a complex task. This challenge becomes even more critical as the design must adhere to system weight limits and prioritize aviation safety considerations. In this review article, we performed a systematic review of the challenges related to the key elements in a thermal management system. These elements encompass every component or subsystem that contributes to the thermal management of a generic hybrid-electric propulsion system. This includes electric motors and generators, batteries, heat exchangers, power transmission systems, power distribution systems, storages, fuel cells, cooling fluids and pipes, control system, pumps and fans. Following the identification of the challenges, the paper provides a comprehensive summary of the existing solutions that have been offered and pursued by the community to address the challenges. Furthermore, the paper also discusses emerging technologies related to each element, highlighting their potential in overcoming these challenges.</p></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"144 ","pages":"Article 100967"},"PeriodicalIF":9.6,"publicationDate":"2023-12-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S0376042123000830/pdfft?md5=62e23d8b3d7e3d9523657a776d3e77b7&pid=1-s2.0-S0376042123000830-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138551216","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"A review of the shock-dominated flow in a hypersonic inlet/isolator","authors":"He-xia Huang ,&nbsp;Hui-jun Tan ,&nbsp;Fang-bo Li ,&nbsp;Xue-bin Tang ,&nbsp;Yuan Qin ,&nbsp;Li-Bin Xie ,&nbsp;Yao-Yu Xu ,&nbsp;Can-min Li ,&nbsp;Si-min Gao ,&nbsp;Yue Zhang ,&nbsp;Shu Sun ,&nbsp;Dan Zhao","doi":"10.1016/j.paerosci.2023.100952","DOIUrl":"10.1016/j.paerosci.2023.100952","url":null,"abstract":"<div><p>A hypersonic inlet/isolator acts as the “compressor” for scramjet engines through a series of shocks, which induces complex internal flows. This paper comprehensively reviews the recent research achievements, focusing on the shock-dominated internal flow of an inlet/isolator. Considering the specific geometrical feature of the hypersonic inlet, the shock wave/boundary layer interactions (SWBLIs) are characterized by multiple successive shocks. Three types of couplings have been observed between adjacent interaction regions. Moreover, shock and expansion waves, which are induced by the SWBLIs and named “background wave”, are reflected in an isolator<span>, forming a background wave/shock train interaction flow. The shock train behavior significantly differs from that in direct-connect facilities under uniform incoming flow conditions, and energy-level-transition-like phenomenon is observed when the shock train intersects with the background wave. Four types of quasi-steady background wave/shock train interactions have been reported, and three types of dynamic transitions have been observed when the shock train passes across the reflection point of the background shock. After the shock train is expelled from the internal duct, the inlet/isolator falls into unstart, and the unsteady shock-dominated flow with violent low-frequency shock oscillation occurs. A typical unstart period contains several stages, including the motion of the shock train in the isolator, large-scale separation in the inlet, and shock oscillation at the external part of the inlet. The flow mechanics of the hypersonic inlet/isolator unstart differs from that of a supersonic inlet. An unstart loop for a hypersonic inlet/isolator has been proposed, including convection wave, shock train, and acoustic wave. Once the induced factor of the unstart is removed, the unstarted shock retreats and the inlet experiences restart with the rebuilding of the supersonic flow<span>. The restart process is highly dependent on the initial flow state and the historical effect. An instantaneous buzz arises before the unstarted shock retreats into the internal duct. Finally, the related passive (e.g., micro-vortex generator, bump, boundary layer bleed and self-circulation secondary flow control method) and active flow control methods (e.g., air jet vortex generator, plasma jet flow control, and solid-particle injection) for weakening the unfavorable impact of these shock-dominated flows are reviewed. Furthermore, the control mechanics and control effects of these flow control methods are analyzed.</span></span></p></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"143 ","pages":"Article 100952"},"PeriodicalIF":9.6,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138297119","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Screening of metal fuels for use in composite propellants for ramjets","authors":"O.G. Glotov","doi":"10.1016/j.paerosci.2023.100954","DOIUrl":"10.1016/j.paerosci.2023.100954","url":null,"abstract":"<div><p>A review of the literature on the methods for activation of the combustion of metallic fuels, mainly boron-containing ones, as the promising components of composite propellants for ramjets is presented. Some methods and ideas were checked experimentally using a laboratory approach developed for comparing the metallic fuels (MF) of different origin. The approach implies the determination of the set of propellant combustion parameters, such as: burning rate, mass of condensed combustion products (CCP), MF combustion completeness, and heat release efficiency (HRE). The CCP particles are firstly quenched in an inert gas, and then sampled and subjected to particle size and chemical analyses. Seventeen propellants, containing different fuels, were studied at pressures of 1.2 and 2.5 МPа. The formulation factors that affect the burning rate and HRE were revealed. Recommendations on future directions of the studies on promising propellant formulations are given.</p></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"143 ","pages":"Article 100954"},"PeriodicalIF":9.6,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"71416703","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Standing oblique detonation for hypersonic propulsion: A review","authors":"Zonglin Jiang","doi":"10.1016/j.paerosci.2023.100955","DOIUrl":"10.1016/j.paerosci.2023.100955","url":null,"abstract":"<div><p><span><span><span>Standing oblique detonation is a unique pressure-gain combustion phenomenon for hypersonic ramjet propulsion, and its research has been related with supersonic combustion in </span>scramjet engines since its births, for example, absent treatment in its early stage and re-consideration in recent decades. Standing oblique detonations and supersonic combustion share the same features of supersonic chemically-reacting flows, and can be considered as different flow development stages. Combustion instability in a chemically-reacting flow is reviewed first to identify its fundamental mechanisms, and the upstream-propagating shock wave is identified as one of intrinsic characteristics and taken as the key problem for developing hypersonic ramjet propulsion. Critical conditions for the standing oblique detonation are summarized as a theoretical base for standing oblique detonation ramjet engines. Three key parameters are included, that is, the maximum heat that can drive local flow states from supersonic to sonic after combustion, the critical inflow </span>Mach number<span> of combustors, at which supersonic combustion becomes stable, and the critical wedge angle at which a standing oblique detonation can be initiated. The evolution of the standing oblique detonation is reviewed by placing emphasis on its complex wave structure that was found to develop via three stages, that is, shock-induced initiation, the decaying stage and the fully-developed stage. Finally, progress in experimental research is reviewed with detailed discussions on stabilization of the standing oblique detonation, experimental methods and development of adequate test facilities. In conclusion, the stable operation of hypersonic ramjet propulsion is a critical issue to approach its </span></span>engineering application, and the standing oblique detonation ramjet engine is recommended as a promising candidate, deserving more attention in the future.</p></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"143 ","pages":"Article 100955"},"PeriodicalIF":9.6,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"71435925","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Review on the aerodynamic issues of the exhaust system for scramjet and turbine based combined cycle engine","authors":"Zheng Lv,&nbsp;Jinglei Xu,&nbsp;Guangtao Song,&nbsp;Rui Li,&nbsp;Jianhui Ge","doi":"10.1016/j.paerosci.2023.100956","DOIUrl":"10.1016/j.paerosci.2023.100956","url":null,"abstract":"<div><p><span>A review of research progress in the design of the exhaust system for the scramjet and turbine based combined cycle (TBCC) engine is presented. Firstly, the technical challenges encountered in designing the exhaust system for a hypersonic propulsion system are highlighted and discussed, and the performance parameter definition as well as the theoretical thrust prediction for the exhaust system is introduced. The review of scramjet nozzle focuses on three aspects: 1) the design method of the single expansion ramp nozzle (SERN) for the integration of the </span>airframe<span><span> with the propulsion system, in which the design method developments of the two-dimensional (2D) SERN, SERN with lateral expansion and three-dimensional (3D) SERN with shape transition are all summarized; 2) the unique flow phenomena of the scramjet nozzle, including the nonuniform inflow and chemical nonequilibrium flow in SERN; 3) the coupling and interaction of the internal flow with the external </span>freestream<span>. Besides, the design and flow researches of the TBCC exhaust system is also reviewed for three parts: 1) variable geometry design for wide flight range, in which both a 2D and 3D exhaust system are described; 2) the overexpanded flow separation mechanism and its control at low flight Mach number; 3) mode transition from low-speed flowpath (LSF) to high-speed flowpath (HSF) for over-under exhaust system. Through the above summary and analysis, the current status, bottlenecks, and development trend of the exhaust system for an airbreathing hypersonic propulsion system can be further clarified.</span></span></p></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"143 ","pages":"Article 100956"},"PeriodicalIF":9.6,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"49696048","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Ramjets/scramjets aerodynamics: A progress review","authors":"Dan Zhao","doi":"10.1016/j.paerosci.2023.100958","DOIUrl":"10.1016/j.paerosci.2023.100958","url":null,"abstract":"","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"143 ","pages":"Article 100958"},"PeriodicalIF":9.6,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S037604212300074X/pdfft?md5=2cffeccc682d84651a45353ccda663d6&pid=1-s2.0-S037604212300074X-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"71416704","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"A review of three-dimensional shock wave–boundary-layer interactions","authors":"Kshitij Sabnis ,&nbsp;Holger Babinsky","doi":"10.1016/j.paerosci.2023.100953","DOIUrl":"10.1016/j.paerosci.2023.100953","url":null,"abstract":"<div><p>The vast majority of shock wave–boundary-layer interactions in practical applications like supersonic aircraft intakes are three dimensional in nature. The complex behaviour of such interactions can generally be understood by combining the flow physics of a limited number of canonical cases. The physical understanding of these flow fields developed by numerous investigators over the last half century is reviewed, focusing predominantly on steady aspects of turbulent, uncontrolled interactions in the transonic and supersonic regimes, i.e. for Mach number less than 5. Key physical features of the flow fields and recent developments are described for swept compression corners, various fin interactions, semi-cones, vertical cylinder-induced interactions, swept oblique shock reflections and flared cylinders. In addition to the canonical geometries, a different type of three dimensionality concerning sidewall effects in duct flows, like intakes or propulsion systems, is also reviewed. The underlying mechanisms, centred on pressure waves propagating from the corner regions, are introduced and the implications for separation unsteadiness and flow control are discussed.</p></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"143 ","pages":"Article 100953"},"PeriodicalIF":9.6,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S0376042123000696/pdfft?md5=c2989b401f436737a7b3e96b5444e661&pid=1-s2.0-S0376042123000696-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"71416699","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Engineering perspective on bird flight: Scaling, geometry, kinematics and aerodynamics","authors":"Tianshu Liu ,&nbsp;Shizhao Wang ,&nbsp;Hao Liu ,&nbsp;Guowei He","doi":"10.1016/j.paerosci.2023.100933","DOIUrl":"10.1016/j.paerosci.2023.100933","url":null,"abstract":"<div><p>From the perspective of aeronautical engineers, this paper gives a systematical summary of the technical aspects of bird flight that should be considered in the analysis and design of flapping unmanned and micro air vehicles (UAVs and MAVs). The relevant aspects include the scaling laws, avian wing geometry, avian wing kinematics, aerodynamics models<span>, computations, and special topics. Instead of extensively and uniformly reviewing a wide range of materials studied by avian biologists, we focus on the analytical and semi-analytical models and quantitative data as the useful guidelines for the design of flapping UAVs and MAVs.</span></p></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"142 ","pages":"Article 100933"},"PeriodicalIF":9.6,"publicationDate":"2023-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44899183","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}