Pub Date : 2025-02-01DOI: 10.1016/j.paerosci.2025.101084
Eytan J. Adler, Joaquim R.R.A. Martins
Aviation’s emissions are among the hardest to eliminate. There are a handful of solutions: battery-electric propulsion, hydrogen fuel cells, hydrogen combustion, and synthetic hydrocarbon fuel produced with carbon from the air. All of these solutions rely on renewable electricity, a resource that will be in short supply as other industries use it to decarbonize. Depending on the flight distance and speed, some carbon-neutral aircraft types demand less renewable electricity, while others are infeasible. Previous work focuses on the cost and climate impact of these alternative fuels and their effects on individual aircraft designs, but not when each solution is viable. We determine the cruise speed and flight range limitations of each. We find that battery-electric aircraft are the most efficient option for short flights, and a combination of hydrogen combustion and fuel cell aircraft are most efficient when batteries are too heavy. We also show that battery and fuel cell technology improvements could enable them to serve all missions. Determining the potential and limitations of different sustainable aircraft enables future efforts to focus on the most impactful technologies.
{"title":"Reprint of : Energy demand comparison for carbon-neutral flight","authors":"Eytan J. Adler, Joaquim R.R.A. Martins","doi":"10.1016/j.paerosci.2025.101084","DOIUrl":"10.1016/j.paerosci.2025.101084","url":null,"abstract":"<div><div>Aviation’s emissions are among the hardest to eliminate. There are a handful of solutions: battery-electric propulsion, hydrogen fuel cells, hydrogen combustion, and synthetic hydrocarbon fuel produced with carbon from the air. All of these solutions rely on renewable electricity, a resource that will be in short supply as other industries use it to decarbonize. Depending on the flight distance and speed, some carbon-neutral aircraft types demand less renewable electricity, while others are infeasible. Previous work focuses on the cost and climate impact of these alternative fuels and their effects on individual aircraft designs, but not when each solution is viable. We determine the cruise speed and flight range limitations of each. We find that battery-electric aircraft are the most efficient option for short flights, and a combination of hydrogen combustion and fuel cell aircraft are most efficient when batteries are too heavy. We also show that battery and fuel cell technology improvements could enable them to serve all missions. Determining the potential and limitations of different sustainable aircraft enables future efforts to focus on the most impactful technologies.</div></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"153 ","pages":"Article 101084"},"PeriodicalIF":11.5,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143619261","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}
Pub Date : 2025-02-01DOI: 10.1016/j.paerosci.2024.101049
Max F. Platzer
{"title":"On pathways to green aviation","authors":"Max F. Platzer","doi":"10.1016/j.paerosci.2024.101049","DOIUrl":"10.1016/j.paerosci.2024.101049","url":null,"abstract":"","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"153 ","pages":"Article 101049"},"PeriodicalIF":11.5,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143619259","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}
Pub Date : 2025-02-01DOI: 10.1016/j.paerosci.2025.101083
E.G. Waddington, P.J. Ansell
Sustainable aviation is a frequently discussed concept in contemporary aviation literature, industry, and policy. However, a review of definitions for sustainable aviation indicates that there is limited agreement as to what sustainable aviation entails. Most definitions include an increase in aircraft efficiency or introduce alternate energy systems in an attempt to decrease overall emissions, but fall short of considering the broader effects of aviation on the globe and its inhabitants. To make progress towards sustainable aviation, it is necessary to synthesize a definition for sustainable aviation from the key elements of aviation and sustainability. Sustainable aviation is the process of creating the air transportation system that maintains the connectivity of communities and mobility of people, goods, and services while minimizing negative impacts to human health, fostering productive quality of life, and conserving natural resources. We then apply this definition to create a theoretical framework, the Five Circles of Sustainable Aviation, which can be utilized to establish sustainability goals for the broad aviation ecosystem. We then apply the theoretical framework to the sustainability of contemporary and concept aircraft. We provide an example sustainability metric analysis that subdivides the Five Circles of Sustainable Aviation into a series of preliminary, illustrative, quantitative and qualitative metrics that can be used to assess aviation systems for their sustainability performance. The importance of applying this framework within a system-of-systems perspective of the aviation value stream is emphasized, with can be used for the practical development of engineered systems pursuant to these sustainability goals. We also address the effects of our definition and sustainable aviation perspective to governance, education, regulation, and safety. Finally, we provide context for the historical perspectives of aviation and sustainability from which we synthesize our definition and tools.
{"title":"Reprint of: A definition, conceptual framework, and pathway towards sustainable aviation","authors":"E.G. Waddington, P.J. Ansell","doi":"10.1016/j.paerosci.2025.101083","DOIUrl":"10.1016/j.paerosci.2025.101083","url":null,"abstract":"<div><div>Sustainable aviation is a frequently discussed concept in contemporary aviation literature, industry, and policy. However, a review of definitions for sustainable aviation indicates that there is limited agreement as to what sustainable aviation entails. Most definitions include an increase in aircraft efficiency or introduce alternate energy systems in an attempt to decrease overall emissions, but fall short of considering the broader effects of aviation on the globe and its inhabitants. To make progress towards sustainable aviation, it is necessary to synthesize a definition for sustainable aviation from the key elements of aviation and sustainability. <strong>Sustainable aviation is the process of creating the air transportation system that maintains the connectivity of communities and mobility of people, goods, and services while minimizing negative impacts to human health, fostering productive quality of life, and conserving natural resources.</strong> We then apply this definition to create a theoretical framework, the Five Circles of Sustainable Aviation, which can be utilized to establish sustainability goals for the broad aviation ecosystem. We then apply the theoretical framework to the sustainability of contemporary and concept aircraft. We provide an example sustainability metric analysis that subdivides the Five Circles of Sustainable Aviation into a series of preliminary, illustrative, quantitative and qualitative metrics that can be used to assess aviation systems for their sustainability performance. The importance of applying this framework within a system-of-systems perspective of the aviation value stream is emphasized, with can be used for the practical development of engineered systems pursuant to these sustainability goals. We also address the effects of our definition and sustainable aviation perspective to governance, education, regulation, and safety. Finally, we provide context for the historical perspectives of aviation and sustainability from which we synthesize our definition and tools.</div></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"153 ","pages":"Article 101083"},"PeriodicalIF":11.5,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143619260","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}
Pub Date : 2025-02-01DOI: 10.1016/j.paerosci.2024.101054
Can Ruan , Liang Yu , Xingcai Lu
The application of sustainable aviation fuels (SAFs) in aviation industry has emerged as a key strategy for reducing the net carbon oxide (CO2) emissions while minimizing modifications to the current aircraft and engine systems. SAFs, which are derived from sustainable feedstocks through biological, thermal and chemical (or their combinations) conversion pathways, can be used in current aero engines, however, at a maximum blending ratio of 50 % with conventional fossil-based jet fuels due to their distinct physical and chemical properties. To enable the use of 100 % ‘drop-in’ SAFs, extensive research has been conducted to obtain a better understanding of the fuel effects on the combustion performance of aero engine combustors, especially the comparison between SAFs and conventional jet fuels. The present paper aims to provide a comprehensive review on this topic by firstly introducing the production pathways of both conventional jet fuels and SAFs, which serve as the root cause of the distinct physiochemical properties among the fuels of interest. Then, the relationship between fundamental combustion properties (atomization, ignition and flame speed) and fuel peculiarities is explored and discussed. This is followed by a summary of the currently available component- and engine-level tests/simulations which compare the emissions, lean blowout (LBO) limit and combustion instabilities of conventional jet fuels and SAFs. Finally, representative flight tests fueled by SAFs ranging from 2006 to the most recent 2023 are summarized and discussed. The paper closes with key conclusions and future directions for the development of SAFs.
在航空工业中应用可持续航空燃料（SAFs）已成为减少二氧化碳（CO2）净排放量的一项关键战略，同时可最大限度地减少对现有飞机和发动机系统的改装。可持续航空燃料是通过生物、热和化学（或其组合）转化途径从可持续原料中提取的，但由于其独特的物理和化学性质，目前可用于航空发动机的可持续航空燃料与传统化石基喷气燃料的最大混合比例为 50%。为了能够使用 100% 的 "无须添加 "的 SAF，已经开展了大量研究，以更好地了解燃料对航空发动机燃烧器燃烧性能的影响，特别是 SAF 与传统喷气燃料之间的比较。本文旨在对这一主题进行全面综述，首先介绍了传统喷气燃料和 SAF 的生产途径，这是导致相关燃料具有不同理化特性的根本原因。然后，探讨和讨论基本燃烧特性（雾化、点火和火焰速度）与燃料特性之间的关系。随后，总结了目前可用的组件和发动机级测试/模拟，对传统喷气燃料和 SAF 的排放、贫喷（LBO）极限和燃烧不稳定性进行了比较。最后，总结并讨论了从 2006 年到最近 2023 年使用 SAF 燃料的代表性飞行测试。最后，本文提出了重要结论和 SAF 的未来发展方向。
{"title":"Towards drop-in sustainable aviation fuels in aero engine combustors: Fuel effects on combustion performance","authors":"Can Ruan , Liang Yu , Xingcai Lu","doi":"10.1016/j.paerosci.2024.101054","DOIUrl":"10.1016/j.paerosci.2024.101054","url":null,"abstract":"<div><div>The application of sustainable aviation fuels (SAFs) in aviation industry has emerged as a key strategy for reducing the net carbon oxide (CO<sub>2</sub>) emissions while minimizing modifications to the current aircraft and engine systems. SAFs, which are derived from sustainable feedstocks through biological, thermal and chemical (or their combinations) conversion pathways, can be used in current aero engines, however, at a maximum blending ratio of 50 % with conventional fossil-based jet fuels due to their distinct physical and chemical properties. To enable the use of 100 % ‘drop-in’ SAFs, extensive research has been conducted to obtain a better understanding of the fuel effects on the combustion performance of aero engine combustors, especially the comparison between SAFs and conventional jet fuels. The present paper aims to provide a comprehensive review on this topic by firstly introducing the production pathways of both conventional jet fuels and SAFs, which serve as the root cause of the distinct physiochemical properties among the fuels of interest. Then, the relationship between fundamental combustion properties (atomization, ignition and flame speed) and fuel peculiarities is explored and discussed. This is followed by a summary of the currently available component- and engine-level tests/simulations which compare the emissions, lean blowout (LBO) limit and combustion instabilities of conventional jet fuels and SAFs. Finally, representative flight tests fueled by SAFs ranging from 2006 to the most recent 2023 are summarized and discussed. The paper closes with key conclusions and future directions for the development of SAFs.</div></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"153 ","pages":"Article 101054"},"PeriodicalIF":11.5,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143619366","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}
Pub Date : 2025-02-01DOI: 10.1016/j.paerosci.2024.101074
Ryan Medlin , Spencer Meeks , Ahmad Vasel-Be-Hagh , Jason Damazo , Rory Roberts
Hydrogen-rich fuels, such as liquid ammonia (LNH3), are being considered for new commercial aircraft propulsion systems to reduce aviation’s CO2 climate impact. It is crucial to ensure that integrating these fuels does not increase non-CO2 climate impacts, defeating the purpose of decarbonizing aviation. Specifically, there are concerns about increased atmospheric radiative forcing (RF) via more frequent and persistent condensation trails (contrails). Some recent analyses show that ammonia contrails could form at lower altitudes (i.e., warmer air) and more frequently than kerosene contrails. On an equal energy basis, NH3-powered engines can exhaust six times more mass of water in every kilogram of air per unit Kelvin temperature increase compared to their kerosene-powered counterparts. The vastly different thermodynamic and microphysical conditions in the exhaust plume of NH3-powered engines query the existing understanding of contrail prediction. Current literature suggests that reducing soot particles as efficient ice nuclei (IN) in plumes of conventional kerosene-fueled engines could eliminate contrails by decreasing ice crystal number density. Such a proposal fails to consider the dissimilar plume properties and a range of microphysical phenomena that affect contrail formation—and thus may not be easily conjectured to NH3-contrails. Examples include an increase in the supersaturation temperature threshold, ambient particle effects, preexisting soot emitted from airplanes burning carbon-based fuels, the feasibility of a homogeneous freezing mechanism, and any non-soot system-exhausted particles serving as efficient IN. Hence, this review seeks to consolidate knowledge of kerosene and ammonia contrails and offer thermodynamic and microphysical perspectives on contrail formation.
{"title":"Ammonia versus kerosene contrails: A review","authors":"Ryan Medlin , Spencer Meeks , Ahmad Vasel-Be-Hagh , Jason Damazo , Rory Roberts","doi":"10.1016/j.paerosci.2024.101074","DOIUrl":"10.1016/j.paerosci.2024.101074","url":null,"abstract":"<div><div>Hydrogen-rich fuels, such as liquid ammonia (LNH<sub>3</sub>), are being considered for new commercial aircraft propulsion systems to reduce aviation’s CO<sub>2</sub> climate impact. It is crucial to ensure that integrating these fuels does not increase non-CO<sub>2</sub> climate impacts, defeating the purpose of decarbonizing aviation. Specifically, there are concerns about increased atmospheric radiative forcing (RF) via more frequent and persistent condensation trails (contrails). Some recent analyses show that ammonia contrails could form at lower altitudes (i.e., warmer air) and more frequently than kerosene contrails. On an equal energy basis, NH<sub>3</sub>-powered engines can exhaust six times more mass of water in every kilogram of air per unit Kelvin temperature increase compared to their kerosene-powered counterparts. The vastly different thermodynamic and microphysical conditions in the exhaust plume of NH<sub>3</sub>-powered engines query the existing understanding of contrail prediction. Current literature suggests that reducing soot particles as efficient ice nuclei (IN) in plumes of conventional kerosene-fueled engines could eliminate contrails by decreasing ice crystal number density. Such a proposal fails to consider the dissimilar plume properties and a range of microphysical phenomena that affect contrail formation—and thus may not be easily conjectured to NH<sub>3</sub>-contrails. Examples include an increase in the supersaturation temperature threshold, ambient particle effects, preexisting soot emitted from airplanes burning carbon-based fuels, the feasibility of a homogeneous freezing mechanism, and any non-soot system-exhausted particles serving as efficient IN. Hence, this review seeks to consolidate knowledge of kerosene and ammonia contrails and offer thermodynamic and microphysical perspectives on contrail formation.</div></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"153 ","pages":"Article 101074"},"PeriodicalIF":11.5,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143031408","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}
The aviation industry faces the challenge of reducing its environmental impact while maintaining economic competitiveness. This study presents an extensive review of cryogenic fuels, specifically Liquefied Natural Gas (LNG) and hydrogen/liquified hydrogen (LH2), along with their renewable counterparts, as potential alternatives to conventional fuels and Sustainable Aviation Fuels (SAFs). The study examines fuel properties, comparing performance metrics and environmental consequences with a focus on payload capacity, operational range, and aircraft design, including necessary fuel tank specifications for cryogenic fuels. Additionally, this paper delves into the production, transportation, and refueling processes for LNG, hydrogen, and their renewable equivalents, exploring the challenges, opportunities, and infrastructure requirements associated with each fuel type. The emissions generated by these fuels are thoroughly assessed to highlight their potential in mitigating the aviation industry's contribution to climate change, considering their entire life cycle. Moreover, the study also investigates the economic implications of adopting cryogenic and renewable fuels, encompassing production costs, Direct Operating Costs (DOC) and the impact on flight ticket prices. This comprehensive study aims to provide valuable insights into the feasibility and long-term viability of integrating these innovative fuel sources into the aviation sector, guiding the industry toward a more sustainable future.
{"title":"Technical and economic assessment of cryogenic fuels for future aviation","authors":"Chuming Wei, Vamsi Krishna Undavalli, Chris Perkins, Katie Heglas, Ethan Oswald, Olanrewaju Bilikis Gbadamosi-Olatunde, Bhupendra Khandelwal","doi":"10.1016/j.paerosci.2024.101053","DOIUrl":"10.1016/j.paerosci.2024.101053","url":null,"abstract":"<div><div>The aviation industry faces the challenge of reducing its environmental impact while maintaining economic competitiveness. This study presents an extensive review of cryogenic fuels, specifically Liquefied Natural Gas (LNG) and hydrogen/liquified hydrogen (LH<sub>2</sub>), along with their renewable counterparts, as potential alternatives to conventional fuels and Sustainable Aviation Fuels (SAFs). The study examines fuel properties, comparing performance metrics and environmental consequences with a focus on payload capacity, operational range, and aircraft design, including necessary fuel tank specifications for cryogenic fuels. Additionally, this paper delves into the production, transportation, and refueling processes for LNG, hydrogen, and their renewable equivalents, exploring the challenges, opportunities, and infrastructure requirements associated with each fuel type. The emissions generated by these fuels are thoroughly assessed to highlight their potential in mitigating the aviation industry's contribution to climate change, considering their entire life cycle. Moreover, the study also investigates the economic implications of adopting cryogenic and renewable fuels, encompassing production costs, Direct Operating Costs (DOC) and the impact on flight ticket prices. This comprehensive study aims to provide valuable insights into the feasibility and long-term viability of integrating these innovative fuel sources into the aviation sector, guiding the industry toward a more sustainable future.</div></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"153 ","pages":"Article 101053"},"PeriodicalIF":11.5,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143619263","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}
Pub Date : 2025-02-01DOI: 10.1016/j.paerosci.2024.101052
Adam C. Frey , David Bosak , Elena Madrid , Joseph Stonham , Carl M. Sangan , Oliver J. Pountney
Proton Exchange Membrane Fuel Cells (PEMFCs) are a leading propulsion technology candidate for net zero carbon dioxide emission aircraft. PEMFCs generate electrical power and byproduct heat via an electrochemical reaction between hydrogen and oxygen reactants. The electrical power generates thrust from motor driven propellers and the byproduct heat is rejected to atmosphere through a Thermal Management System (TMS). Thermal management of PEMFCs is more complex than jet engines because the heat cannot be as readily dissipated to the atmosphere. Increasing the operating temperature of PEMFCs is desirable as it increases the driving temperature between the TMS coolant and the atmosphere. This is advantageous from an aerospace perspective because for a given heat load it enables downsizing (and thus lightweighting) of the TMS with an associated reduction in drag. This review considers High Temperature (HT) PEMFCs that operate at temperatures between 100 and 250 °C owing to these advantages. In wider literature there are several TMS architectures that are being actively considered for HT-PEMFCs. A detailed review of literature pertinent to these HT-PEMFC TMS architectures, and their design and operation, is presented in this paper. This review is subsequently used to identify gaps in knowledge in the following thematic areas: powerplant, direct cooling, indirect cooling, heat absorption, primary heat exchanger, and operation (shutdown, cold start, and thermal transients). These gaps provide future research challenges that need to be expediently addressed to facilitate convergence to suitable solutions for HT-PEMFC TMS in aviation.
{"title":"Thermal management in high temperature proton exchange membrane fuel cells for aircraft propulsion systems","authors":"Adam C. Frey , David Bosak , Elena Madrid , Joseph Stonham , Carl M. Sangan , Oliver J. Pountney","doi":"10.1016/j.paerosci.2024.101052","DOIUrl":"10.1016/j.paerosci.2024.101052","url":null,"abstract":"<div><div>Proton Exchange Membrane Fuel Cells (PEMFCs) are a leading propulsion technology candidate for net zero carbon dioxide emission aircraft. PEMFCs generate electrical power and byproduct heat via an electrochemical reaction between hydrogen and oxygen reactants. The electrical power generates thrust from motor driven propellers and the byproduct heat is rejected to atmosphere through a Thermal Management System (TMS). Thermal management of PEMFCs is more complex than jet engines because the heat cannot be as readily dissipated to the atmosphere. Increasing the operating temperature of PEMFCs is desirable as it increases the driving temperature between the TMS coolant and the atmosphere. This is advantageous from an aerospace perspective because for a given heat load it enables downsizing (and thus lightweighting) of the TMS with an associated reduction in drag. This review considers High Temperature (HT) PEMFCs that operate at temperatures between 100 and 250 °C owing to these advantages. In wider literature there are several TMS architectures that are being actively considered for HT-PEMFCs. A detailed review of literature pertinent to these HT-PEMFC TMS architectures, and their design and operation, is presented in this paper. This review is subsequently used to identify gaps in knowledge in the following thematic areas: powerplant, direct cooling, indirect cooling, heat absorption, primary heat exchanger, and operation (shutdown, cold start, and thermal transients). These gaps provide future research challenges that need to be expediently addressed to facilitate convergence to suitable solutions for HT-PEMFC TMS in aviation.</div></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"153 ","pages":"Article 101052"},"PeriodicalIF":11.5,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143619262","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}
Pub Date : 2025-01-01DOI: 10.1016/j.paerosci.2023.100900
Igor Levchenko , Dan Goebel , Daniela Pedrini , Riccardo Albertoni , Oleg Baranov , Igal Kronhaus , Dan Lev , Mitchell L.R. Walker , Shuyan Xu , Kateryna Bazaka
While many types of mature space propulsion systems are in active use, significant progress is still required to meet the requirements of new missions. The emerging challenges include plans for Mars and Moon exploration, building huge satellite constellations like Starlink and OneWeb, advanced astrophysical studies including space-based gravitational wave detection systems, precise astrophysical and astronomical measurements in space, search for life on exoplanets, deep space missions, and others. In this light, this review outlines and briefly discusses the most recent, advanced and innovative approaches, technologies, concepts, and physical principles related to space propulsion. Furthermore, we present more ambitious ideas for the future that have been demonstrated in labs as prototype space systems to enhance the performance of mature space propulsion thrusters and concepts that are proposed for consideration in future space thruster systems. We discuss the recent advances in the application of advanced rotating magnetic field systems for space propulsion, condensable propellant thrusters, innovations in propellant supply systems, capillary and narrow channel thrusters, staged thrusters, application of segmented electrodes, and other techniques. The manuscript brings to light the most recent innovations for future consolidated research efforts worldwide, helps to define the key parameters of space propulsion systems for future ambitious missions, and ultimately contributes to the creation of substantially novel thrust platforms for future space exploration.
{"title":"Recent innovations to advance space electric propulsion technologies","authors":"Igor Levchenko , Dan Goebel , Daniela Pedrini , Riccardo Albertoni , Oleg Baranov , Igal Kronhaus , Dan Lev , Mitchell L.R. Walker , Shuyan Xu , Kateryna Bazaka","doi":"10.1016/j.paerosci.2023.100900","DOIUrl":"10.1016/j.paerosci.2023.100900","url":null,"abstract":"<div><div>While many types of mature space propulsion systems are in active use, significant progress is still required to meet the requirements of new missions. The emerging challenges include plans for Mars and Moon exploration, building huge satellite constellations like Starlink and OneWeb, advanced astrophysical studies including space-based gravitational wave detection systems, precise astrophysical and astronomical measurements in space, search for life on exoplanets, deep space missions, and others. In this light, this review outlines and briefly discusses the most recent, advanced and innovative approaches, technologies, concepts, and physical principles related to space propulsion. Furthermore, we present more ambitious ideas for the future that have been demonstrated in labs as prototype space systems to enhance the performance of mature space propulsion thrusters and concepts that are proposed for consideration in future space thruster systems. We discuss the recent advances in the application of advanced rotating magnetic field systems for space propulsion, condensable propellant thrusters, innovations in propellant supply systems, capillary and narrow channel thrusters, staged thrusters, application of segmented electrodes, and other techniques. The manuscript brings to light the most recent innovations for future consolidated research efforts worldwide, helps to define the key parameters of space propulsion systems for future ambitious missions, and ultimately contributes to the creation of substantially novel thrust platforms for future space exploration.</div></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"152 ","pages":"Article 100900"},"PeriodicalIF":11.5,"publicationDate":"2025-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142867686","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}
Pub Date : 2025-01-01DOI: 10.1016/j.paerosci.2024.101072
Mehdi Ghoreyshi , Keith Bergeron , Jürgen Seidel
This article explores recent advancements in the simulation of air drop configurations. Utilizing modeling and simulation techniques can enhance the understanding of airdrop operations before undertaking costly and risky experimental trials. Validated simulations also offer the opportunity to examine a wider range of non-standard cases, designs, systems, and components. Key physical and simulation parameters under investigation include various airdrop configurations, flow conditions, extraction and release timings, and ejector forces, all of which will be integrated with multiple parachute configurations and cargo payloads of differing geometries and mass distributions. The review covers advanced mesh generation techniques, turbulence modeling, adaptive mesh refinement methods, prescribed and responsive body motions, contact modeling, propeller and engine modeling, fluid–structure interaction for parachute inflation, and methods to study the stability of payloads and parachutes, including the modeling of suspension and extraction lines. The article details two specific studies: the extraction of various-sized containers from the C-17 ramp using gravity and chutes, and a sensitivity analysis of personnel extraction from the C-130 aircraft troop doors, considering variations in paratrooper profiles, center of gravity, and mass data.
{"title":"Advances in exit simulations of airdrop configurations","authors":"Mehdi Ghoreyshi , Keith Bergeron , Jürgen Seidel","doi":"10.1016/j.paerosci.2024.101072","DOIUrl":"10.1016/j.paerosci.2024.101072","url":null,"abstract":"<div><div>This article explores recent advancements in the simulation of air drop configurations. Utilizing modeling and simulation techniques can enhance the understanding of airdrop operations before undertaking costly and risky experimental trials. Validated simulations also offer the opportunity to examine a wider range of non-standard cases, designs, systems, and components. Key physical and simulation parameters under investigation include various airdrop configurations, flow conditions, extraction and release timings, and ejector forces, all of which will be integrated with multiple parachute configurations and cargo payloads of differing geometries and mass distributions. The review covers advanced mesh generation techniques, turbulence modeling, adaptive mesh refinement methods, prescribed and responsive body motions, contact modeling, propeller and engine modeling, fluid–structure interaction for parachute inflation, and methods to study the stability of payloads and parachutes, including the modeling of suspension and extraction lines. The article details two specific studies: the extraction of various-sized containers from the C-17 ramp using gravity and chutes, and a sensitivity analysis of personnel extraction from the C-130 aircraft troop doors, considering variations in paratrooper profiles, center of gravity, and mass data.</div></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"152 ","pages":"Article 101072"},"PeriodicalIF":11.5,"publicationDate":"2025-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142925062","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}
Pub Date : 2025-01-01DOI: 10.1016/j.paerosci.2024.101073
Carmine Varriale , Thomas Lombaerts , Gertjan Looye
Direct Lift Control (DLC) is the capability to directly and intentionally influence lift on a fixed-wing aircraft by means of aerodynamic control devices, with minimum change of its angle of attack. Although several definitions exist, with various degrees of ambiguity, the combination of DLC and pitch attitude control has unambiguously proven to reduce pilot workload and improve flying comfort considerably. DLC has historically seen several applications on so-called inflight simulators and, recently, this capability has been rolled out over several aircraft types of the US Navy fleet, massively reducing pilot workload during carrier landings. On the civil front, only one aircraft type has been equipped with this capability, despite its very positive reception by flight crews and passengers. The intention of this paper is to revive interest in civil DLC applications, by reviewing in-depth its basic principles, characteristic features, benefits, and implementations so far. Several modern aircraft and disruptive wing configurations appear to be inherently capable of accommodating DLC functionality from a flight physical, systems, and software point of view. The proven benefits of DLC are likely to well outweigh the cost of the added functionality.
{"title":"Direct Lift Control: A review of its principles, merits, current and future implementations","authors":"Carmine Varriale , Thomas Lombaerts , Gertjan Looye","doi":"10.1016/j.paerosci.2024.101073","DOIUrl":"10.1016/j.paerosci.2024.101073","url":null,"abstract":"<div><div>Direct Lift Control (DLC) is the capability to directly and intentionally influence lift on a fixed-wing aircraft by means of aerodynamic control devices, with minimum change of its angle of attack. Although several definitions exist, with various degrees of ambiguity, the combination of DLC and pitch attitude control has unambiguously proven to reduce pilot workload and improve flying comfort considerably. DLC has historically seen several applications on so-called inflight simulators and, recently, this capability has been rolled out over several aircraft types of the US Navy fleet, massively reducing pilot workload during carrier landings. On the civil front, only one aircraft type has been equipped with this capability, despite its very positive reception by flight crews and passengers. The intention of this paper is to revive interest in civil DLC applications, by reviewing in-depth its basic principles, characteristic features, benefits, and implementations so far. Several modern aircraft and disruptive wing configurations appear to be inherently capable of accommodating DLC functionality from a flight physical, systems, and software point of view. The proven benefits of DLC are likely to well outweigh the cost of the added functionality.</div></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"152 ","pages":"Article 101073"},"PeriodicalIF":11.5,"publicationDate":"2025-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142967834","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}
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