Acta Astronautica最新文献_第2页

Explosion risks: Variety of deflagration-to-detonation transition scenarios in smooth tubes 爆炸风险：光滑管道中从爆燃到爆炸的各种过渡情况

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-10-21 DOI: 10.1016/j.actaastro.2024.10.038

{"title":"Explosion risks: Variety of deflagration-to-detonation transition scenarios in smooth tubes","authors":"","doi":"10.1016/j.actaastro.2024.10.038","DOIUrl":"10.1016/j.actaastro.2024.10.038","url":null,"abstract":"<div><div>In the framework of comprehensive assessment of explosion risks on board of spacecrafts and on the facilities of launch places, the paper is focused on the detailed analysis of particular scenarios of deflagration-to-detonation transition taking place in smooth tubes filled with acetylene-oxygen mixtures of different compositions. By means of precise numerical simulation it is demonstrated that various scenarios of detonation onset can take place depending on the mixture composition and its initial thermodynamic state. It is demonstrated that independent on the particular scenario always the basic mechanism of detonation onset via the formation of strong enough shock wave takes place. In more reactive mixtures the strong shock originates from the self-sustained process of joint pressure build up and reaction intensification exactly at the flame front. In less reactive mixtures the transient flow behavior leads to the shock waves generation and interaction. As a result, a brand new reaction kernel could arise in the area of shock waves interaction. In number of cases, that leads to the coupling between the shock wave and the newborn reaction front and results in the strong shock formation and further detonation onset.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":null,"pages":null},"PeriodicalIF":3.1,"publicationDate":"2024-10-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142538881","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Joint acceleration based adaptive reactionless manipulation of closed-loop multi-arm space robot in post-capture phase 基于联合加速度的闭环多臂空间机器人后捕捉阶段自适应无反作用力操纵

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-10-20 DOI: 10.1016/j.actaastro.2024.10.022

{"title":"Joint acceleration based adaptive reactionless manipulation of closed-loop multi-arm space robot in post-capture phase","authors":"","doi":"10.1016/j.actaastro.2024.10.022","DOIUrl":"10.1016/j.actaastro.2024.10.022","url":null,"abstract":"<div><div>Space robots will play a crucial role in on-orbit operations like refuelling, servicing, and capture of debris. This paper focuses on capturing a non-cooperative target using a multi-arm space robot and its post-capture control. In the post-capture phase, a target object gets rigidly attached to end-effectors, and arms get into a closed-loop configuration, resulting in added constraints. Further, due to a target object’s unknown inertial parameters, system behaviour becomes unpredictable and poses difficulty in achieving reactionless manipulation to minimize base attitude disturbance. We present acceleration-based adaptive reactionless manipulation in the post-capture phase considering the unknown inertial parameter of a target. The regressor form required for adapting the joint states is derived using the acceleration-based approach. To update unknown parameters recursively immediately after impact, three methods, namely, recursive least square (RLS), weighted recursive least square (WRLS), and Kalman filter (KF), are used and compared. The efficacy of these methods has been demonstrated by using numerical studies of a dual-arm space robot that captures a non-cooperative target. Further, the acceleration-based and the velocity-based approaches are individually compared with RLS, WRLS and KF methods. Investigations have also been carried out to study the effects of change in ratios of base-to-target and base-to-robot masses, as well as angular velocities of a target.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":null,"pages":null},"PeriodicalIF":3.1,"publicationDate":"2024-10-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142572362","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Numerical search for the effective thermal conductivity of cracked media 裂纹介质有效热导率的数值搜索

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-10-19 DOI: 10.1016/j.actaastro.2024.10.042

{"title":"Numerical search for the effective thermal conductivity of cracked media","authors":"","doi":"10.1016/j.actaastro.2024.10.042","DOIUrl":"10.1016/j.actaastro.2024.10.042","url":null,"abstract":"<div><div>Spacecraft parts accumulate damage during operation and defects that are invariably present even in new designs may grow. This leads to changes in the behavior of individual parts of the space vehicle and, consequently, to the risk of fracture. A more accurate assessment of spacecraft safety requires internal defects to be included in the material models under consideration. One of the main hazardous effects on space objects is multiple temperature heating and cooling due to periodic action of solar rays. This paper presents a study of thermal conduction of media containing cracks. It is carried out with the help of a technique developed by the authors to determine the effective thermal conductivity of materials and based on approximate numerical solution of the steady-state thermal conduction problem for a three-dimensional medium with cracks by the boundary element method. This technique allows to obtain the distribution of the temperature field and heat flux density at any point of the body under consideration, as well as to calculate the effective parameters of materials with high accuracy at relatively low calculation time using ordinary personal computers of average power. The basis of the numerical method presented in this paper is the decomposition of the desired solution into a series of some pre-calculated analytical solutions of the heat conduction equations. The dependence of the effective thermal conductivity on the density of thermally insulated cracks was considered. The formula of this dependence is proposed. Verification of the proposed methodology was carried out by comparing the numerical results of a number of problems with the results of other authors.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":null,"pages":null},"PeriodicalIF":3.1,"publicationDate":"2024-10-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142534981","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

A novel tether-net configuration with double-linked bullets for suppressing reshrinking motion after full deployment 新型系绳网配置与双链子弹，用于抑制完全展开后的回缩运动

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-10-19 DOI: 10.1016/j.actaastro.2024.10.035

{"title":"A novel tether-net configuration with double-linked bullets for suppressing reshrinking motion after full deployment","authors":"","doi":"10.1016/j.actaastro.2024.10.035","DOIUrl":"10.1016/j.actaastro.2024.10.035","url":null,"abstract":"<div><div>Tether-nets have attracted considerable attention as tools for capturing space debris. However, owing to the lack of aerodynamic drag to resist collapse in space, tether-nets tend to shrink back after deployment because of tension in the tether. Various strategies have been proposed to suppress this reshrinking motion before debris capture, such as equipping bullets with thruster modules to control their trajectory after ejection and incorporating a bullet ejection-angle adjustment mechanism. However, these approaches complicate the tether-net design and/or ejection systems. In this study, a novel tether-net configuration comprising double-linked bullets, wherein the inner and outer bullets are connected via a tether, was proposed to prevent the tether-net from reshrinking after full deployment. Upon full deployment, as the bullets start to rebound due to impulsive tension, the outer bullets fly outward, pulling the inner bullets and exchanging momentum to suppress their rebounding motion. The effectiveness of the double-linked bullets in suppressing the reshrinking motion of the tether-net was demonstrated by comparing the results with those obtained using typical single-linked bullets. Furthermore, the influence of the inner and outer bullet mass ratio on the tether-net deployment and reshrinking motion was numerically analyzed to identify the optimal mass ratio for effectively suppressing the reshrinking motion. The results indicate that a mass ratio of 1.0, or slightly less, between the outer and inner bullets is most effective in suppressing tether-net reshrinking.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":null,"pages":null},"PeriodicalIF":3.1,"publicationDate":"2024-10-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142534985","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Descriptive models for lunar High-Ti deposits 月球高钛矿床的描述性模型

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-10-18 DOI: 10.1016/j.actaastro.2024.10.031

引用次数: 0

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

Acta Astronautica Pub Date : 2024-10-18 DOI: 10.1016/j.actaastro.2024.10.039

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

Acta Astronautica Pub Date : 2024-10-18 DOI: 10.1016/j.actaastro.2024.10.032

{"title":"Analysis of fly-around mission with spinning tether system for space station observation","authors":"","doi":"10.1016/j.actaastro.2024.10.032","DOIUrl":"10.1016/j.actaastro.2024.10.032","url":null,"abstract":"<div><div>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.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":null,"pages":null},"PeriodicalIF":3.1,"publicationDate":"2024-10-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142534893","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

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

Acta Astronautica Pub Date : 2024-10-17 DOI: 10.1016/j.actaastro.2024.10.012

{"title":"Influence of constant and alternating electric fields on the deformation and destruction of a liquid droplet","authors":"","doi":"10.1016/j.actaastro.2024.10.012","DOIUrl":"10.1016/j.actaastro.2024.10.012","url":null,"abstract":"<div><div>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.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":null,"pages":null},"PeriodicalIF":3.1,"publicationDate":"2024-10-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142534894","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

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

Acta Astronautica Pub Date : 2024-10-17 DOI: 10.1016/j.actaastro.2024.10.019

{"title":"Femtosatellite mission architectures and mission assurance strategies","authors":"","doi":"10.1016/j.actaastro.2024.10.019","DOIUrl":"10.1016/j.actaastro.2024.10.019","url":null,"abstract":"<div><div>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.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":null,"pages":null},"PeriodicalIF":3.1,"publicationDate":"2024-10-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142552371","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

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

Acta Astronautica Pub Date : 2024-10-17 DOI: 10.1016/j.actaastro.2024.10.041

{"title":"Along-track deployment control of space tether system for SAR-GMTI mission","authors":"","doi":"10.1016/j.actaastro.2024.10.041","DOIUrl":"10.1016/j.actaastro.2024.10.041","url":null,"abstract":"<div><div>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.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":null,"pages":null},"PeriodicalIF":3.1,"publicationDate":"2024-10-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142534982","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0