Progress in Aerospace Sciences最新文献

Ammonia versus kerosene contrails: A review

IF 11.5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Progress in Aerospace Sciences

Pub Date : 2025-02-01 DOI: 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.

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引用次数: 0

Recent innovations to advance space electric propulsion technologies 推进空间电力推进技术的最新创新

IF 11.5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Progress in Aerospace Sciences

Pub Date : 2025-01-01 DOI: 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.

虽然许多类型的成熟空间推进系统正在积极使用中，但要满足新任务的要求仍需取得重大进展。新出现的挑战包括火星和月球探测计划、建立庞大的卫星星座（如 Starlink 和 OneWeb）、先进的天体物理研究（包括天基引力波探测系统）、精确的空间天体物理和天文测量、寻找系外行星上的生命、深空任务等。有鉴于此，本综述概述并简要讨论了与空间推进有关的最新、最先进和最创新的方法、技术、概念和物理原理。此外，我们还介绍了未来更宏伟的设想，这些设想已在实验室中作为原型空间系统进行了演示，以提高成熟的空间推进推进器的性能，并提出了供未来空间推进器系统考虑的概念。我们讨论了应用先进旋转磁场系统进行太空推进的最新进展、可凝结推进剂推进器、推进剂供应系统的创新、毛细管和窄通道推进器、分段推进器、分段电极的应用以及其他技术。该手稿为全球未来的综合研究工作带来了最新的创新成果，有助于为未来雄心勃勃的任务确定空间推进系统的关键参数，并最终有助于为未来的空间探索创建实质性的新型推力平台。

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引用次数: 0

Advances in exit simulations of airdrop configurations 空投配置出口模拟方面的进展

IF 11.5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Progress in Aerospace Sciences

Pub Date : 2025-01-01 DOI: 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.

本文探讨了空投配置模拟的最新进展。利用建模和仿真技术可以在进行昂贵和危险的实验试验之前增强对空投操作的理解。经过验证的模拟还提供了检查更广泛的非标准案例、设计、系统和组件的机会。正在研究的关键物理和模拟参数包括各种空投配置、流动条件、提取和释放时间以及弹射力，所有这些都将与多种降落伞配置和不同几何形状和质量分布的货物有效载荷集成。综述了先进的网格生成技术，湍流建模，自适应网格细化方法，规定和响应的身体运动，接触建模，螺旋桨和发动机建模，降落伞充气的流固耦合，以及研究有效载荷和降落伞稳定性的方法，包括悬挂和提取线的建模。本文详细介绍了两项具体研究：利用重力和降落伞从C-17斜坡上提取各种尺寸的容器，以及考虑到伞兵剖面、重心和质量数据的变化，从C-130飞机部队门提取人员的敏感性分析。

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引用次数: 0

Direct Lift Control: A review of its principles, merits, current and future implementations 直接升力控制：对其原理、优点、当前和未来实施的综述

IF 11.5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Progress in Aerospace Sciences

Pub Date : 2025-01-01 DOI: 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.

直接升力控制（Direct升力控制，DLC）是指在固定翼飞机的迎角变化最小的情况下，通过气动控制装置直接、有意地影响飞机升力的能力。尽管存在几种不同程度的定义，但DLC和俯仰姿态控制的结合已被明确证明可以减少飞行员的工作量并大大提高飞行舒适度。DLC历来在所谓的飞行模拟器上有几个应用，最近，这种能力已经在美国海军舰队的几种飞机上推广，大大减少了航母着陆时飞行员的工作量。在民用方面，只有一种类型的飞机配备了这种能力，尽管机组人员和乘客对它的接受非常积极。本文的目的是通过深入回顾DLC的基本原理、特征、优点和实现，重振对民用DLC应用的兴趣。从飞行物理、系统和软件的角度来看，一些现代飞机和破坏性的机翼配置似乎具有适应DLC功能的内在能力。DLC所带来的好处远远超过了添加功能所带来的成本。

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引用次数: 0

Review of unsteady aerodynamic problems and control strategies for the blade tip flow of axial compressors 轴流压气机叶尖非定常气动问题及控制策略综述

IF 11.5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Progress in Aerospace Sciences

Pub Date : 2024-12-02 DOI: 10.1016/j.paerosci.2024.101063

Yanhui Wu , Xiang Zhang , Fan Yang , Stephen Spence

When axial compressors operate under high-loading conditions, inherent unsteady flow phenomena emerge in the tip region as a consequence of the tip leakage flow. These aerodynamic phenomena are collectively known as tip flow unsteadiness. It has been proven that tip flow unsteadiness not only serves as an excitation source of both non-synchronous vibration and tip noise but is also the cause of short-length-scale stall inception. These structural and aerodynamic problems have become common issues in highly loaded axial compressors, which require a breakthrough in the study of tip flow unsteadiness. This article begins with a review of past research on unsteady tip flow phenomena, examining them from the perspectives of self-excited unsteadiness and rotating instability (RI). Detailed discussions are presented on the relationships between RI and tip clearance noise, non-synchronous vibrations, and stall inceptions. This is followed by explanations for the origin of the tip flow unsteadiness. Six theories proposed in existing literature are classified, including vortex shedding, tip leakage vortex breakdown, the interaction between tip leakage flow and adjacent flow, rotating instability vortex, tip secondary vortex, and shear layer instability. There have been only limited investigations of control techniques aimed at suppressing tip flow unsteadiness. These methods are classified according to their control mechanisms and the corresponding control effects are presented. Additionally, recommendations for future advancements in these fields are presented.

轴流压气机在高负荷工况下运行时，由于叶尖泄漏流动，在叶尖区域产生固有的非定常流动现象。这些空气动力学现象统称为叶尖流动不稳定。研究表明，叶尖流动的非定常性不仅是非同步振动和叶尖噪声的激励源，而且是引起短长度尺度失速的原因。这些结构和气动问题已成为高负荷轴流压气机的普遍问题，这就要求在叶尖非定常研究方面取得突破。本文首先从自激不稳定和旋转不稳定的角度对非定常叶尖流动现象的研究进行了综述。详细讨论了RI与叶尖间隙噪声、非同步振动和失速开始之间的关系。接下来是对叶尖流动不稳定的起源的解释。现有文献中提出的六种理论包括：旋涡脱落、叶尖泄漏涡击穿、叶尖泄漏流与邻近流的相互作用、旋转不稳定涡、叶尖二次涡和剪切层不稳定。针对抑制叶尖流动不稳定的控制技术的研究非常有限。根据控制机理对这些方法进行了分类，并给出了相应的控制效果。此外，对这些领域的未来发展提出了建议。

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引用次数: 0

Energy demand comparison for carbon-neutral flight 碳中和飞行的能源需求比较

IF 11.5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Progress in Aerospace Sciences

Pub Date : 2024-11-30 DOI: 10.1016/j.paerosci.2024.101051

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.

航空业的排放是最难消除的。有几个解决方案：电池电力推进、氢燃料电池、氢燃烧和用空气中的碳生产的合成碳氢化合物燃料。所有这些解决方案都依赖于可再生电力，随着其他行业使用可再生电力来脱碳，这种资源将会供不应求。根据飞行距离和速度的不同，一些碳中和型飞机对可再生电力的需求更少，而另一些则不可行。以前的工作主要集中在这些替代燃料的成本和气候影响，以及它们对单个飞机设计的影响，但不是在每个解决方案都可行的情况下。我们确定了每架飞机的巡航速度和飞行距离限制。我们发现，对于短途飞行来说，电池电动飞机是最有效的选择，当电池太重时，氢燃烧和燃料电池飞机的结合是最有效的。我们还表明，电池和燃料电池技术的改进可以使它们服务于所有任务。确定不同可持续飞机的潜力和局限性，可以使未来的努力集中在最具影响力的技术上。

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引用次数: 0

A definition, conceptual framework, and pathway towards sustainable aviation 定义、概念框架和实现可持续航空的途径

IF 11.5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Progress in Aerospace Sciences

Pub Date : 2024-11-01 DOI: 10.1016/j.paerosci.2024.101050

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.

可持续航空是当代航空文献、行业和政策中经常讨论的一个概念。然而，对可持续航空定义的审查表明，人们对可持续航空的内涵达成的一致意见有限。大多数定义包括提高飞机效率或引入替代能源系统，以试图减少总体排放量，但没有考虑到航空对全球及其居民的更广泛影响。为了在可持续航空方面取得进展，有必要从航空和可持续发展的关键要素中综合出一个可持续航空的定义。可持续航空是创建航空运输系统的过程，该系统既能保持社区的连通性以及人员、货物和服务的流动性，又能最大限度地减少对人类健康的负面影响，提高生活质量，保护自然资源。然后，我们运用这一定义创建了一个理论框架，即可持续航空五环，可用于为广泛的航空生态系统制定可持续发展目标。然后，我们将该理论框架应用于当代飞机和概念飞机的可持续发展。我们提供了一个可持续性指标分析示例，将可持续航空五环细分为一系列初步的、说明性的定量和定性指标，可用于评估航空系统的可持续性表现。我们强调了在航空价值流的系统视角下应用该框架的重要性，该框架可用于根据这些可持续发展目标对工程系统进行实际开发。我们还讨论了我们的定义和可持续航空视角对治理、教育、监管和安全的影响。最后，我们提供了航空和可持续发展的历史背景，并从中总结出我们的定义和工具。

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引用次数: 0

Progress and prospects of artificial intelligence development and applications in supersonic flow and combustion

IF 11.5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Progress in Aerospace Sciences

Pub Date : 2024-11-01 DOI: 10.1016/j.paerosci.2024.101046

Jialing Le , Maotao Yang , Mingming Guo , Ye Tian , Hua Zhang

Due to the significant improvement in computing power and the rapid advancement of data processing technologies, artificial intelligence (AI) has introduced new tools and methodologies to address the challenges posed by high nonlinearity and strong coupling characteristics in traditional supersonic flow and combustion. This article reviews the considerable progress AI has made in applications within the fields of supersonic flow and combustion, covering three main aspects: intelligent turbulence combustion simulation, supersonic flow field intelligent reconstruction based on deep learning, and the intelligent design of the full-flow passage of supersonic engines. In recent years, the field of turbulent combustion has seen the utilization of large volume of data combined with implementation of advanced machine learning models, enabling accurate predictions of combustion efficiency and optimization of the combustion process. Flow field intelligent reconstruction employs deep learning networks to accurately reconstruct the detailed information of the entire flow field from limited observational data, enhancing the capacity to analyze and predict supersonic flows. The intelligent design of the full-flow passage of supersonic engines has led to efficient design and optimization of complex flow systems through the integration of advanced optimization algorithms and AI technology. These advancements have driven the development of supersonic flow and combustion theories and provided innovative solutions for related engineering applications. Finally, the challenges and future applications of machine learning in combustion research are discussed.

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引用次数: 0

Robotic manipulators for in-orbit servicing and active debris removal: Review and comparison 用于在轨维修和主动碎片清除的机器人机械手：回顾与比较

IF 11.5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Progress in Aerospace Sciences

Pub Date : 2024-11-01 DOI: 10.1016/j.paerosci.2024.101055

Tomasz Rybus

Due to the growing threat from space debris and the accelerating increase in the number of active satellites, Active Debris Removal (ADR) and In-Orbit Servicing (IOS) missions are currently being developed. A robotic manipulator mounted on a servicing satellite will enable precise grasping of a target object and is needed to perform complex servicing tasks. This paper presents a comprehensive review of robotic manipulators developed for ADR and IOS missions. This review includes the manipulators that have already been used in orbital missions, those developed in the past for missions that were cancelled, technology demonstrators, and the manipulators currently in development for planned missions. The review includes the following manipulators: the Shuttle Remote Manipulator System, the manipulator developed for the ETS-VII mission, the Orbital Express Demonstration Manipulator System, the manipulator developed for the DEOS mission, the CAESAR, the LARAD, the VISPA, the WMS 1 Lemur, the TITAN, the FREND, the STAARK, and the TINA manipulators. Small manipulators designed for nanosatellites are also reviewed. Basic parameters of manipulators, such as the number of degrees of freedom, mass, and length, are compared. The Denavit-Hartenberg parameters and kinematic structures of the selected manipulators are presented. The paper includes a discussion of specific design features, such as the manipulator joint design. Finally, recent trends and future prospects are explored.

由于空间碎片的威胁日益增大，在役卫星的数量加速增加，目前正在开发主动碎片清除（ADR）和在轨服务（IOS）任务。安装在维修卫星上的机器人机械手可以精确抓取目标物体，是执行复杂维修任务所必需的。本文全面回顾了为 ADR 和 IOS 任务开发的机器人机械手。审查内容包括已在轨道任务中使用过的机械手、过去为已取消的任务开发的机械手、技术演示器，以及目前正在为计划中的任务开发的机械手。审查包括以下操纵器：航天飞机遥控操纵器系统、为 ETS-VII 任务开发的操纵器、轨道快车演示操纵器系统、为 DEOS 任务开发的操纵器、CAESAR、LARAD、VISPA、WMS 1 Lemur、TITAN、FREND、STAARK 和 TINA 操纵器。此外还回顾了为纳卫星设计的小型机械手。比较了机械手的基本参数，如自由度数、质量和长度。介绍了所选机械手的 Denavit-Hartenberg 参数和运动学结构。论文还讨论了具体的设计特点，如机械手的关节设计。最后，还探讨了最近的发展趋势和未来前景。

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引用次数: 0

Retro-propulsion in rocket systems: Recent advancements and challenges for the prediction of aerodynamic characteristics and thermal loads 火箭系统中的反推力：气动特性和热负荷预测的最新进展和挑战

IF 11.5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Progress in Aerospace Sciences

Pub Date : 2024-11-01 DOI: 10.1016/j.paerosci.2024.101044

Tamas Bykerk, Sebastian Karl, Mariasole Laureti, Moritz Ertl, Tobias Ecker

This paper presents a review of recent literature on the application of retro-propulsion in earth based rocket systems, with a specific focus on the recent advancements and challenges associated with the prediction of aerothermal and aerodynamic characteristics of re-usable boosters. It gives an overview of current system architectures and mission profiles, while discussing the trends in future vehicle design. The effects of various flight conditions on thermal loads and vehicle aerodynamics are discussed, with particular attention given to the interactions between plume and vehicle, as well as the interplay between individual nozzle exhausts. A short evaluation of wind tunnel testing capabilities and scaling challenges is given, before the use of computational fluid dynamics for retro-propulsion applications is discussed. Finally, a summary is given, which emphasises future needs surrounding the accurate prediction of the vehicle aerothermal and aerodynamic characteristics.

本文综述了有关在地基火箭系统中应用反推力的最新文献，特别侧重于与可重复使用助推器气热和气动特性预测相关的最新进展和挑战。它概述了当前的系统结构和任务概况，同时讨论了未来飞行器设计的趋势。讨论了各种飞行条件对热负荷和飞行器空气动力学的影响，特别关注了烟羽和飞行器之间的相互作用，以及单个喷嘴排气之间的相互作用。在讨论计算流体动力学在反推应用中的应用之前，对风洞试验能力和扩展挑战进行了简短评估。最后，进行了总结，强调了未来在准确预测飞行器气动和热动特性方面的需求。

引用次数: 0