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No laughing matter: How autonomous agents can improve well-being and teamwork 没有笑料:自主代理如何改善福利和团队合作
IF 3.1 2区 物理与天体物理 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-10-18 DOI: 10.1016/j.actaastro.2024.10.039
Rylee M. Linhardt, Lila Berger, Eduardo Salas
Autonomous agents are a critical factor for maintaining the well-being and health of astronaut teams in long duration spaceflight. As autonomous agents become more independent, and interdependent the need to understand how they can interact effectively with humans not only becomes more necessary, but will become the paradigm for future team research. In our paper, we describe a conceptual model that explains how autonomous agents and human team members can learn to implicitly coordinate through humorous social interaction and effective task interdependence. We argue that to build a shared mental model between autonomous agents and human team members, HATs need to develop trust with one another, albeit through different mechanisms, to work together effectively.
在长时间太空飞行中,自主代理是维持宇航员团队福祉和健康的关键因素。随着自主代理变得更加独立和相互依赖,了解它们如何与人类有效互动不仅变得更加必要,而且将成为未来团队研究的范例。在我们的论文中,我们描述了一个概念模型,解释了自主代理和人类团队成员如何通过幽默的社交互动和有效的任务相互依存学会隐性协调。我们认为,要在自主代理和人类团队成员之间建立一个共享的心智模型,HATs 需要通过不同的机制建立彼此间的信任,从而有效地协同工作。
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引用次数: 0
Analysis of fly-around mission with spinning tether system for space station observation 利用旋转系绳系统进行空间站观测的绕飞飞行任务分析
IF 3.1 2区 物理与天体物理 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-10-18 DOI: 10.1016/j.actaastro.2024.10.032
Hang Yang , Changqing Wang , Hongshi Lu , Aijun Li
This paper presents the mission scenarios of using spinning tether system to conduct space stations fly-around mission and validates its feasibility. The main challenge of fly-around mission lies in the difficulty of balancing low fuel consumption and long-term fly-around observation. To deal with this problem, a novel spinning tether system is proposed. Firstly, the fly-around process with spinning tether system is introduced, and the tether system is modeled based on Newton-Euler method with a novel description of spinning motion. Secondly, Given the unique structural limitations of space stations, two fly-around schemes and referenced fly-around trajectories are detailed. Thirdly, a backstepping controller is proposed for tracking the reference motion of fly-around satellites, and the fuel consumption among different fly-around schemes is compared and analyzed. In the end, numerical results validate that under the proposed control strategy, the spinning tether system can maintain a stable fly-around configuration in both the planar and vertical plane, the symmetrical formation configuration prevents the central space station from being affected by the motion of fly-around satellites. Moreover, energy consumption analysis indicates that tethered system can save 62.8 % of impulse compared to traditional schemes when flying in the planar plane, making it the most energy-efficient option.
本文介绍了利用旋转系绳系统执行空间站绕飞任务的飞行方案,并验证了其可行性。绕飞任务的主要挑战在于难以兼顾低燃料消耗和长期绕飞观测。为解决这一问题,提出了一种新型旋转系绳系统。首先,介绍了旋转系链系统的绕飞过程,并基于牛顿-欧拉法建立了系链系统模型,对旋转运动进行了新颖的描述。其次,考虑到空间站独特的结构限制,详细介绍了两种绕飞方案和参考绕飞轨迹。第三,提出了一种用于跟踪绕飞卫星参考运动的反步进控制器,并对不同绕飞方案的燃料消耗进行了比较和分析。最后,数值结果验证了在所提出的控制策略下,旋转系绳系统可以在平面和垂直面上保持稳定的绕飞配置,对称的编队配置可以防止中心空间站受到绕飞卫星运动的影响。此外,能耗分析表明,与传统方案相比,系留系统在平面飞行时可节省 62.8%的冲量,是最节能的方案。
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引用次数: 0
Influence of constant and alternating electric fields on the deformation and destruction of a liquid droplet 恒定和交变电场对液滴变形和破坏的影响
IF 3.1 2区 物理与天体物理 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-10-17 DOI: 10.1016/j.actaastro.2024.10.012
V.N. Kireev , B.S. Shalabayeva , K.N. Volkov
Examining the impact of electromagnetic field, which provides thrust in contemporary rocket engines, is turning into a significant issue. Its resolution is required to guarantee the safety of space flight by enhancing engine performance and lowering fuel consumption. Spacecraft propulsion is achieved by low-thrust rocket engines. The principle of operation for ion colloid engines is the electrostatic acceleration of charged droplets. A static electric field accelerates charged liquid droplets created by electrospraying them in a low-thrust colloid engine. A promising technology in many industries is the active control of droplet motion and deformation with electric field. An electromagnetic field impact on droplet deformation and destruction in a viscous liquid is examined. The effect of electromagnetic field on individual droplets and emulsions is examined in terms of their physical mechanisms. Constant and alternating electric field effects on liquid droplet are represented numerically. The effects of droplet electric capillary number and viscosity ratio on droplet unsteady deformations is explored. The parameters that correspond to the droplet destruction are found. The results obtained have potential applications in enhancing the efficiency of current industrial electric dehydrators and in advancing the development of new electromagnetic field-based demulsification technologies.
电磁场为当代火箭发动机提供推力,研究电磁场的影响正成为一个重要问题。要通过提高发动机性能和降低燃料消耗来保证太空飞行的安全,就必须解决这个问题。航天器的推进由低推力火箭发动机实现。离子胶体发动机的工作原理是带电液滴的静电加速。在低推力胶体发动机中,通过电喷雾产生的静态电场可加速带电液滴。利用电场主动控制液滴的运动和变形是许多行业中一项前景广阔的技术。本文研究了电磁场对粘性液体中液滴变形和破坏的影响。从物理机制的角度研究了电磁场对单个液滴和乳液的影响。用数值表示了恒定和交变电场对液滴的影响。探讨了液滴电毛细管数和粘度比对液滴非稳态变形的影响。找到了与液滴破坏相对应的参数。所得结果可用于提高当前工业电脱水机的效率,并推动基于电磁场的新型破乳化技术的发展。
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引用次数: 0
Femtosatellite mission architectures and mission assurance strategies 超小型卫星飞行任务架构和飞行任务保证战略
IF 3.1 2区 物理与天体物理 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-10-17 DOI: 10.1016/j.actaastro.2024.10.019
Christopher Teale, James Beeley, Gilles Baillet, Colin R. McInnes
Since its inception, the femtosatellite has developed into a complex and capable spacecraft. However, despite such advances the implementation of predicted applications remains elusive. In response, this paper explores three femtosatellite mission architectures, the drone, swarm, and hive, to characterize what possible femtosatellite mission could be envisioned for true space applications. Starting from a single femtosatellite, each architecture represents an increase in network complexity, so the use of graph theory is proposed as a means for characterizing, understanding, and modelling femtosatellite systems. A simple reliability model is also proposed for each of the mission architectures, and a simulation is carried out to generate a profile of the system’s lifecycle. The results are discussed for each of the architectures in relation to potential applications. Each of the architectures was shown to be feasible for short duration missions due to the inherent unreliability of femtosatellites. Additionally, mid- and long-duration missions were shown to be possible for swarms and hives with sufficiently large populations. Finally, applications are re-examined considering the lifecycle profile exhibited by each system.
自问世以来,超小型卫星已发展成为一个复杂而有能力的航天器。然而,尽管取得了这些进步,预期应用的实现仍然遥遥无期。为此,本文探讨了三种飞星任务架构,即无人机、蜂群和蜂巢,以描述真正太空应用中可能的飞星任务。从单个飞卫星开始,每种架构都代表着网络复杂性的增加,因此本文提出使用图论来描述、理解和模拟飞卫星系统。还为每种任务架构提出了一个简单的可靠性模型,并进行了模拟,以生成系统生命周期的概况。针对每种结构的潜在应用对结果进行了讨论。由于微小卫星固有的不稳定性,每种结构对于短时间飞行任务来说都是可行的。此外,中长期飞行任务对于具有足够大种群的蜂群和蜂巢来说也是可行的。最后,考虑到每个系统的生命周期情况,对其应用进行了重新审查。
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引用次数: 0
Along-track deployment control of space tether system for SAR-GMTI mission 用于 SAR-GMTI 飞行任务的空间系留系统的沿轨部署控制
IF 3.1 2区 物理与天体物理 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-10-17 DOI: 10.1016/j.actaastro.2024.10.041
Linxiao Li , Aijun Li , Hongshi Lu , Changqing Wang
Global, 24/7, and all-weather Synthetic Aperture Radars (SARs) are optimal platforms for Ground Moving Target Indication (GMTI) missions, and the tether constraint provides a stable mechanic connection for such configurations. To fulfill the requirements of such missions, the Space Tether System (STS) must be deployed to horizontal positions to form the necessary along-track interference baseline, which is unstable relative to traditional vertical positions and has not received adequate focus. To deal with this problem, this study focuses on the deployment control of the STS to the unstable horizontal positions. Firstly, the properties of the STS at the horizontal position are analyzed, and a synthetic criterion of measurement error is defined based on the observation principle of the GMTI mission. Secondly, two deployment control strategies are proposed, and corresponding desired trajectories are generated by considering two occasions respectively. In the end, considering the instability of horizontal positions, an adaptive closed-loop controller is designed utilizing the backstepping method to address gravitational moment and other disturbances. Simulations demonstrate that the system can successfully attain the desired horizontal positions under both deployment strategies, and the designed controller can quickly track trajectories under initial state errors and external disturbances.
全球、全天候和全天时合成孔径雷达(SAR)是地面移动目标指示(GMTI)任务的最佳平台,系留约束为此类配置提供了稳定的机械连接。为满足此类任务的要求,空间系留系统(STS)必须部署到水平位置,以形成必要的沿轨干扰基线,而这相对于传统的垂直位置是不稳定的,也没有得到足够的重视。为解决这一问题,本研究将重点放在将空间系留系统部署到不稳定水平位置的控制上。首先,分析了 STS 在水平位置的特性,并根据 GMTI 任务的观测原理定义了测量误差的合成标准。其次,提出两种部署控制策略,并分别考虑两种情况生成相应的期望轨迹。最后,考虑到水平位置的不稳定性,设计了一个自适应闭环控制器,利用反步进方法来解决重力力矩和其他干扰。仿真结果表明,在两种部署策略下,系统都能成功达到所需的水平位置,并且所设计的控制器能在初始状态误差和外部干扰下快速跟踪轨迹。
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引用次数: 0
Motion and self-motion of thin bodies in rarefied gas 稀薄气体中薄体的运动和自运动
IF 3.1 2区 物理与天体物理 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-10-16 DOI: 10.1016/j.actaastro.2024.10.037
A.A. Shamina , A.V. Zvyagin , A.Y. Shamin
One of the important tasks of space flight safety is the ability of a wing to maintain stability in an oncoming turbulent flow. In this case, the spacecraft must move the greatest distance. The paper studies the motion of a thin plate near a boundary in an oncoming flow of rarefied gas. At low Reynolds numbers, the effect of the boundary on the plate is studied, and the possibility of self-propulsion is shown.
太空飞行安全的重要任务之一是机翼在迎面而来的湍流中保持稳定的能力。在这种情况下,航天器必须移动最大的距离。本文研究了在迎面而来的稀薄气体流中靠近边界的薄板的运动。在低雷诺数下,研究了边界对薄板的影响,并显示了自推进的可能性。
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引用次数: 0
The three-dimensional maneuver control of spinning tether system under a new Lagrangian model 新拉格朗日模型下旋转系绳系统的三维机动控制
IF 3.1 2区 物理与天体物理 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-10-16 DOI: 10.1016/j.actaastro.2024.10.033
Chenyang Sun , Changqing Wang , Hongshi Lu , Aijun Li , Pavel Fadeenkov
This study explores the modeling and control of the spinning tether system (STS) for maneuvering between arbitrary spinning planes. The spinning tether system garners significant attention for good centrifugal stability and transportation ability. However, conventional STS models face challenges such as singularities and coupling when studying three-dimensional spinning motion. To tackle the aforementioned challenges, a new singularity-adjustable model and a maneuvering control strategy are proposed. Initially, a variable coordinate system is defined, which allows for relocating singularities to unattainable positions during three-dimensional motions. Based on this new coordinate system, the singularity-adjustable Lagrangian model is established. Subsequently, based on the new model, a three-dimensional maneuvering scheme for spatial spinning motions is introduced to define and describe STS maneuvering trajectories in a de-coupled way. Finally, based on the reference maneuvering scheme, a saturated radial basis function network-based controller is designed to attenuate potential disturbances and errors, as electric thrusters used in this work are limited in actuating magnitude. Numerical results demonstrate that, with the new singularity-adjustable Lagrangian model, singularity and coupling phenomena are avoided during the three-dimensional maneuver, and the proposed controller ensures a stable STS three-dimensional maneuvering motion.
本研究探讨了旋转系绳系统(STS)的建模和控制,以实现在任意旋转平面之间的操纵。旋转系绳系统因其良好的离心稳定性和运输能力而备受关注。然而,传统的 STS 模型在研究三维旋转运动时面临着奇点和耦合等挑战。为解决上述难题,本文提出了一种新的奇异性可调模型和操纵控制策略。首先,定义了一个可变坐标系,该坐标系允许在三维运动过程中将奇点重新定位到无法实现的位置。基于这个新坐标系,建立了奇点可调拉格朗日模型。随后,在新模型的基础上,引入了空间旋转运动的三维机动方案,以去耦合的方式定义和描述 STS 机动轨迹。最后,在参考操纵方案的基础上,设计了一个基于饱和径向基函数网络的控制器,以减弱潜在的干扰和误差,因为这项工作中使用的电动推进器在执行幅度上是有限的。数值结果表明,利用新的奇异性可调拉格朗日模型,在三维机动过程中避免了奇异性和耦合现象,所提出的控制器确保了稳定的 STS 三维机动运动。
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引用次数: 0
Laser-optical technologies for space debris removal 用于清除空间碎片的激光光学技术
IF 3.1 2区 物理与天体物理 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-10-16 DOI: 10.1016/j.actaastro.2024.10.027
Vladislav Yu. Khomich , Evgeniy V. Shakhmatov , Konstantin N. Sviridov
Technologies for the removal of space debris fragments of artificial (man-made) origin from near-Earth space is being proposed in order to provide the security of space flights. The fundamental principle of the proposed method is based on the utilization of intense solar radiation to direct and concentrate at space debris fragments with the aim of creating a plasma braking and transferring the fragment from a circular to an elliptical orbit following its subsequent burn up in the dense layers of the atmosphere. At the same time, the generation of substantial solar radiation is facilitated by a synthesized multi-aperture optical system situated in a heliosynchronous space orbit and permanently oriented towards the Sun.
为了确保空间飞行的安全,正在提出从近地空间清除人工(人造)空间碎片的技术。所提方法的基本原理是利用强烈的太阳辐射来引导和集中空间碎片,目的是产生等离子体制动,将碎片从圆形轨道转移到椭圆形轨道,然后在大气稠密层中燃烧。与此同时,位于太阳同步空间轨道并永久面向太阳的合成多孔径光学系统为产生大量太阳辐射提供了便利。
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引用次数: 0
Development of means for suppressing the negative effects of interaction between the pilot and reentry and other high-speed vehicles 开发抑制飞行员与重返大气层飞行器和其他高速飞行器之间相互作用的负面影响的手段
IF 3.1 2区 物理与天体物理 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-10-16 DOI: 10.1016/j.actaastro.2024.10.028
A.V. Efremov, E.V. Efremov, A.I. Shcherbakov
Several novel active and passive means for the suppression of pilot-induced oscillations are considered in the paper. The potential of the proposed means in eliminating Category I, II, and III pilot-induced oscillations was studied in ground-based simulation for two controlled element dynamics corresponding to an aerospace vehicle and a second-generation supersonic transport. The experiments demonstrated that the highest effectiveness in suppressing pilot-induced oscillations and improving task performance is provided by integrating both proposed active suppressors with one of the passive prefilters.
文中考虑了几种抑制飞行员诱发振荡的新型主动和被动方法。针对航空飞行器和第二代超音速运输机的两种受控元素动力学进行了地面模拟,研究了所提出的方法在消除第一、第二和第三类飞行员诱发振荡方面的潜力。实验结果表明,将两个拟议的主动抑制器与一个被动预滤波器集成在一起,能最有效地抑制飞行员诱发的振荡并提高任务性能。
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引用次数: 0
Shape of fragments cloud behind heterogeneous screen by a space debris particle impact 空间碎片粒子撞击异质屏幕后碎片云的形状
IF 3.1 2区 物理与天体物理 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-10-16 DOI: 10.1016/j.actaastro.2024.10.036
A.E. Buzyurkin, V.M. Fomin, A.E. Kraus, E.I. Kraus, I.I. Shabalin
Technogenic pollution of near-Earth space poses a threat to the functioning of spacecraft. Collisions between space debris (SD) and spacecraft (SC) structures can have catastrophic consequences or cause localized damage, leading to the loss of SC operability or the failure of certain functions. The SC body must effectively protect the internal equipment from various external impacts, be technologically feasible to manufacture, and have as little mass as possible. As a result, the task of designing spacecraft bodies and protective screens for low-orbit SC is particularly relevant due to the large concentration of SD in low Earth orbits.
A comparative numerical study was conducted to evaluate the effectiveness of various thin shields in protecting against impacts from space debris particles. The study examined homogeneous shields made of A356 aluminum alloy and 316L stainless steel, as well as volumetrically reinforced composite shields produced using additive manufacturing with steel inclusions, and shields with a gradient distribution of steel throughout the thickness of an aluminum matrix, all with the same areal density. In all the heterogeneous plates considered, the volumetric concentration of steel was 36 %. The study covered an interaction velocity range of 2–9 km/s. Numerical modeling results indicated that the structure of the thin heterogeneous plate does not affect the shape of the debris cloud formed behind the protective shield. The findings of this study can serve as a basis for selecting materials for the development of more effective protection for spacecraft against high-velocity impacts.
近地空间的技术污染对航天器的运行构成威胁。空间碎片(SD)与航天器(SC)结构之间的碰撞可能会造成灾难性后果或局部损坏,导致航天器丧失可操作性或某些功能失效。SC 主体必须能有效保护内部设备免受各种外部撞击,在制造技术上可行,并且质量尽可能小。因此,为低轨道 SC 设计航天器本体和保护屏的任务尤为重要,因为低地球轨道上集中了大量的 SD。该研究考察了由 A356 铝合金和 316L 不锈钢制成的均质防护罩,以及利用添加剂制造技术生产的含有钢夹杂物的体积增强复合防护罩,以及在铝基体的整个厚度上梯度分布钢的防护罩,所有防护罩的均方根密度均相同。在所有考虑的异质板中,钢的体积浓度为 36%。研究涵盖的相互作用速度范围为 2-9 千米/秒。数值建模结果表明,异质薄板的结构不会影响保护罩后形成的碎片云的形状。这项研究的结果可以作为选择材料的依据,以便为航天器开发更有效的保护装置,防止高速撞击。
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引用次数: 0
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Acta Astronautica
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