Astrodynamics最新文献_第5页

Analytical libration control law for electrodynamic tether system with current constraint 带电流约束的电动系绳系统的解析振动控制法则

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-02-02 DOI: 10.1007/s42064-023-0174-4

Shidong Xu, Ti Chen, Hao Wen, Dongping Jin

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引用次数: 0

Collision-avoidance strategy for a spinning electrodynamic tether system 旋转电动系绳系统的防撞策略

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-02-02 DOI: 10.1007/s42064-023-0175-3

Linxiao Li, Aijun Li, Hongshi Lu, Changqing Wang, Yuriy Mikhailovich Zabolotnov, Yong Guo

{"title":"Collision-avoidance strategy for a spinning electrodynamic tether system","authors":"Linxiao Li, Aijun Li, Hongshi Lu, Changqing Wang, Yuriy Mikhailovich Zabolotnov, Yong Guo","doi":"10.1007/s42064-023-0175-3","DOIUrl":"10.1007/s42064-023-0175-3","url":null,"abstract":"<div><p>Spinning electrodynamic tether systems (SEDTs) have promising potential for the active removal of space debris, the construction of observation platforms, and the formation of artificial gravity. However, owing to the survivability problem of long tethers, designing collision-avoidance strategies for SEDTs with space debris is an urgent issue. This study focuses on the design of collision-avoidance strategies for SEDTs with an electrodynamic force (Ampere force). The relative distance between the debris and the SEDT is first derived, and then two collision-avoidance strategies are proposed according to the two different cases. When debris collides closer to a lighter subsatellite, a stationary avoidance strategy is proposed to change the spatial position of the subsatellite by adjusting only the angular motion of the tether, which maintains the original orbit of the SEDT. When debris collides closer to a heavier main spacecraft, a comprehensive avoidance strategy is proposed to change the spatial position of the SEDT by slightly modifying the orbital height and changing the tether angular motion simultaneously. The numerical results illustrate that the proposed strategies promptly avoid potential collisions of an SEDT with space debris without significant changes in the orbital \tparameters of the SEDT.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":null,"pages":null},"PeriodicalIF":2.7,"publicationDate":"2024-02-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142409390","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"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

Adaptive neural dynamic-based hybrid control strategy for stable retrieval of tethered satellite systems 用于系留卫星系统稳定回收的基于神经动态的自适应混合控制策略

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-02-02 DOI: 10.1007/s42064-023-0178-0

Zhixiong Ji, Gefei Shi

引用次数: 0

Perturbed initial orbit determination 扰动初始轨道确定

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-02-02 DOI: 10.1007/s42064-023-0179-z

Alberto Fossà, Matteo Losacco, Roberto Armellin

引用次数: 0

Prediction and experimental verification of tether net entanglement for space debris capture 用于捕获空间碎片的系绳网缠结的预测和实验验证

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2024-02-01 DOI: 10.1007/s42064-023-0170-8

Kaito Kosuge, Hirohisa Kojima

引用次数: 0

Prediction and experimental verification of tether net entanglement for space debris capture 用于捕获空间碎片的系绳网缠结的预测和实验验证

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-02-01 DOI: 10.1007/s42064-023-0170-8

Kaito Kosuge, Hirohisa Kojima

{"title":"Prediction and experimental verification of tether net entanglement for space debris capture","authors":"Kaito Kosuge, Hirohisa Kojima","doi":"10.1007/s42064-023-0170-8","DOIUrl":"10.1007/s42064-023-0170-8","url":null,"abstract":"<div><p>This study involved simulations and experiments aimed at assessing the efficacy of a tether net in encapsulating space debris. The tether net was modeled as a spring–mass–damper system considering the influence of aerodynamic and gravitational forces and the occurrence of debris collisions. To examine the influence of collision position and size disparity between the debris and the net on debris capture status, the entanglement nodes of the net were identified. Experiments were conducted to evaluate the wrapping capabilities of the tether net, focusing specifically on debris capture. Subsequently, the results were compared with those of the numerical simulation. In the experiments, radio frequency identification was used to identify the entanglement points of the tether net. Previous studies have indicated that the ideal collision point for capturing debris using a tether net with the debris intended to be captured is located at the center of the net. However, the experimental results of this study revealed that a collision position that is slightly shifted from the center of the tether net is more advantageous for capturing debris in terms of tether net entanglement.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":null,"pages":null},"PeriodicalIF":2.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139878816","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"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

Autonomous navigation of an asteroid orbiter enhanced by a beacon satellite in a high-altitude orbit 通过高空轨道上的信标卫星加强小行星轨道器的自主导航

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-02-01 DOI: 10.1007/s42064-023-0172-6

Weidong Yin, Yu Shi, Leizheng Shu, Yang Gao

{"title":"Autonomous navigation of an asteroid orbiter enhanced by a beacon satellite in a high-altitude orbit","authors":"Weidong Yin, Yu Shi, Leizheng Shu, Yang Gao","doi":"10.1007/s42064-023-0172-6","DOIUrl":"10.1007/s42064-023-0172-6","url":null,"abstract":"<div><p>This study aims to assess the autonomous navigation performance of an asteroid orbiter enhanced using an inter-satellite link to a beacon satellite. Autonomous navigation includes the orbit determination of the orbiter and beacon, and asteroid gravity estimation without any ground station support. Navigation measurements were acquired using satellite-to-satellite tracking (SST) and optical observation of asteroid surface landmarks. This study presents a new orbiter–beacon SST scheme, in which the orbiter circumnavigates the asteroid in a low-altitude strongly-perturbed orbit, and the beacon remains in a high-altitude weakly-perturbed orbit. We used Asteroid 433 Eros as an example, and analyzed and designed low- and high-altitude orbits for the orbiter and beacon. The navigation measurements were precisely modeled, extended Kalman filters were devised, and observation configuration was analyzed using the Cramer–Rao lower bound (CRLB). Monte Carlo simulations were carried out to assess the effects of the orbital inclination and altitudes of the orbiter and beacon as key influencing factors. The simulation results showed that the proposed SST scheme was an effective solution for enhancing the autonomous navigation performance of the orbiter, particularly for improving the accuracy of gravity estimation.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":null,"pages":null},"PeriodicalIF":2.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139686685","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"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

Debris falling forecast method for spacecraft disintegrating separation 航天器解体分离碎片下落预测方法

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-10-26 DOI: 10.1007/s42064-023-0177-1

Dun Li, Zhi-Hui Li, Yue-Long He, Jing-Jiang Chu, Yu Jiang

{"title":"Debris falling forecast method for spacecraft disintegrating separation","authors":"Dun Li, Zhi-Hui Li, Yue-Long He, Jing-Jiang Chu, Yu Jiang","doi":"10.1007/s42064-023-0177-1","DOIUrl":"10.1007/s42064-023-0177-1","url":null,"abstract":"<div><p>Large spacecraft fall out of orbit and re-enter the atmosphere at the end of their lifetime, and they can break up into small debris upon re-entry. The spacecraft debris generated by the disintegration may lead to high risk when the surviving debris reaches the ground. One way to reduce the damage risk of spacecraft is to simulate the spacecraft disintegration process and accurately predict the falling area. Aerodynamics seriously affects the reentering process, especially in the continuous flow regime. Aerodynamic force and heat are the main factors leading to debris disintegration. High dynamic pressure leads to sharp changes in attitude and complex trajectories during debris fall. A numerical method based on an unstructured Cartesian grid was developed to simulate the disintegrating separation problem by coupling the Navier-Stokes equation and the six-degree-of-freedom trajectory equation. A method combining the numerical method for dynamic processes with numerical simulation based on a static aerodynamic/dynamic characteristic database was developed for forecasting the falling area. Spacecraft disintegrating separation from 60 km was simulated using the method, and the multibody aerodynamic interference and the separation trajectory were predicted. The falling process was forecast by a numerical simulation method based on the static aerodynamic database/dynamic characteristic database when the debris went out of the influence domain. This method has good forecasting efficiency while considering the aerodynamic interference, making it a valuable method for forecasting disintegrating separation and falling debris.\u0000</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":null,"pages":null},"PeriodicalIF":6.1,"publicationDate":"2023-10-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"71910918","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"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

Determining origins of satellite breakup events in LEO region 确定低轨区域卫星解体事件的起源

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-10-26 DOI: 10.1007/s42064-023-0182-4

Yongjie Liu, Yu Jiang, Hengnian Li, Zongbo Huyan, Hongchao Wang

{"title":"Determining origins of satellite breakup events in LEO region","authors":"Yongjie Liu, Yu Jiang, Hengnian Li, Zongbo Huyan, Hongchao Wang","doi":"10.1007/s42064-023-0182-4","DOIUrl":"10.1007/s42064-023-0182-4","url":null,"abstract":"<div><p>Currently, a surge in the number of spacecraft and fragments is observed, leading to more frequent breakup events in low Earth orbits (LEOs). The causes of these events are being identified, and specific triggers, such as collisions or explosions, are being examined for their importance to space traffic management. Backward propagation methods were employed to trace the origins of these types of breakup events. Simulations were conducted using the NASA standard breakup model, and satellite Hitomi’s breakup was analyzed. Kullback-Leibler (KL) divergences, Euclidean 2-norms, and Jensen-Shannon (JS) divergences were computed to deduce potential types of breakups and the associated fragmentation masses. In the simulated case, a discrepancy of 22.12 s between the estimated and actual time was noted. Additionally, the breakup of the Hitomi satellite was estimated to have occurred around UTC 1:49:26.4 on March 26, 2016. This contrasts with the epoch provided by the Joint Space Operation Center, which was estimated to be at 1:42 UTC ± 11 min. From the findings, it was suggested that the techniques introduced in the study can be effectively used to trace the origins of short-term breakup events and to deduce the types of collisions and fragmentation masses under certain conditions.\u0000</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":null,"pages":null},"PeriodicalIF":6.1,"publicationDate":"2023-10-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"71910916","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"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

Message from the Guest Editors of the Special Issue on Space Traffic Management 空间交通管理特刊客座编辑寄语

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-10-26 DOI: 10.1007/s42064-023-0187-z

Yu Jiang, Roberto Armellin, Zhihui Li

引用次数: 0