Astrodynamics最新文献_第6页

Astrometric calibration and source characterisation of the latest generation neuromorphic event-based cameras for space imaging 最新一代基于神经形态事件的空间成像相机的天体测量校准和源特性

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-08-24 DOI: 10.1007/s42064-023-0168-2

Nicholas Owen Ralph, Alexandre Marcireau, Saeed Afshar, Nicholas Tothill, André van Schaik, Gregory Cohen

{"title":"Astrometric calibration and source characterisation of the latest generation neuromorphic event-based cameras for space imaging","authors":"Nicholas Owen Ralph, Alexandre Marcireau, Saeed Afshar, Nicholas Tothill, André van Schaik, Gregory Cohen","doi":"10.1007/s42064-023-0168-2","DOIUrl":"10.1007/s42064-023-0168-2","url":null,"abstract":"<div><p>As an emerging approach to space situational awareness and space imaging, the practical use of an event-based camera (EBC) in space imaging for precise source analysis is still in its infancy. The nature of event-based space imaging and data collection needs to be further explored to develop more effective event-based space imaging systems and advance the capabilities of event-based tracking systems with improved target measurement models. Moreover, for event measurements to be meaningful, a framework must be investigated for EBC calibration to project events from pixel array coordinates in the image plane to coordinates in a target resident space object’s reference frame. In this paper, the traditional techniques of conventional astronomy are reconsidered to properly utilise the EBC for space imaging and space situational awareness. This paper presents the techniques and systems used for calibrating an EBC for reliable and accurate measurement acquisition. These techniques are vital in building event-based space imaging systems capable of real-world space situational awareness tasks. By calibrating sources detected using the EBC, the spatiotemporal characteristics of detected sources or “event sources” can be related to the photometric characteristics of the underlying astrophysical objects. Finally, these characteristics are analysed to establish a foundation for principled processing and observing techniques which appropriately exploit the capabilities of the EBC.\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":"2023-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"71910006","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: 3

Self-induced collision risk of the Starlink constellation based on long-term orbital evolution analysis 基于长期轨道演化分析的星链星座自感碰撞风险

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-08-10 DOI: 10.1007/s42064-023-0171-7

Wei Zhang, Xiuhong Wang, Wen Cui, Zhi Zhao, Sirui Chen

{"title":"Self-induced collision risk of the Starlink constellation based on long-term orbital evolution analysis","authors":"Wei Zhang, Xiuhong Wang, Wen Cui, Zhi Zhao, Sirui Chen","doi":"10.1007/s42064-023-0171-7","DOIUrl":"10.1007/s42064-023-0171-7","url":null,"abstract":"<div><p>The deployment of mega constellations has had a significant effect on the compounding space debris environment, increasing the number of on-orbit objects in all conditions and damaging the stability of the space debris environment. The increased density of space objects is associated with an increased risk of on-orbit collisions. Collision risk exists not only between a mega constellation and the space debris environment but also inside a mega constellation. In this study, we used the Starlink constellation to investigate the self-induced collision risk caused by malfunctioning satellites. First, we analyzed the conjunction condition between malfunctioning and operative satellites based on long-term orbital evolution characteristics. The collision probability was then calculated based on the conjunction analysis results. The results show that malfunctioning satellites in Phase 1 cause an 86.2% self-induced collision probability based on a malfunctioning rate of 1%, which is close to the collision probability caused by objects larger than 6 cm during five years of service. Therefore, self-induced collisions are another important risk factor for the Starlink constellation.\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":"2023-08-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"71909486","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

Self-induced collision risk of the Starlink constellation based on long-term orbital evolution analysis 基于长期轨道演化分析的星链星座自致碰撞风险

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-08-10 DOI: 10.1007/s42064-023-0171-7

Wei Zhang, Xiuhong Wang, Wen Cui, Zhi-ru Zhao, Sirui Chen

引用次数: 0

Safe-event pruning in spacecraft conjunction management 航天器协同管理中的安全事件修剪

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-07-15 DOI: 10.1007/s42064-023-0165-5

Sébastien Henry, Roberto Armellin, Thibault Gateau

{"title":"Safe-event pruning in spacecraft conjunction management","authors":"Sébastien Henry, Roberto Armellin, Thibault Gateau","doi":"10.1007/s42064-023-0165-5","DOIUrl":"10.1007/s42064-023-0165-5","url":null,"abstract":"<div><p>Spacecraft conjunction management plays a crucial role in the mitigation of space collisions. When a conjunction event occurs, resources and time are spent analyzing, planning, and potentially maneuvering the spacecraft. This work contributes to a subpart of the problem: Confidently identifying events that will not lead to a high collision probability, and therefore do not require further investigation. The method reduces the dimensionality of the data via principal component analysis (PCA) on a subset of features. High-risk regions are then determined by clustering the projected data, and events that do not belong to a high-risk cluster are pruned. A genetic algorithm (GA) is developed to optimize the number of clusters and feature selection of the model. Furthermore, an ensemble learning framework is proposed to combine the suboptimal models for better generalization. The results show that the first set of parameters pruned approximately 50% of the events in the testing set with no false negatives, whereas the second set of parameters pruned 70% of the events and maintained a near-perfect recall. These results could benefit the optimization of operational resources and allow operators to focus better on the events of interest.\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":"2023-07-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"71909558","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

Safe-event pruning in spacecraft conjunction management 航天器连接管理中的安全事件修剪

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-07-15 DOI: 10.1007/s42064-023-0165-5

S. Henry, R. Armellin, Thibault Gateau

引用次数: 0

Covariance analysis of periodic and quasi-periodic orbits around Phobos with applications to the Martian Moons eXploration mission 火卫一周期和准周期轨道的协方差分析及其在火星卫星探测任务中的应用

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-07-05 DOI: 10.1007/s42064-023-0166-4

Edoardo Ciccarelli, Nicola Baresi

{"title":"Covariance analysis of periodic and quasi-periodic orbits around Phobos with applications to the Martian Moons eXploration mission","authors":"Edoardo Ciccarelli, Nicola Baresi","doi":"10.1007/s42064-023-0166-4","DOIUrl":"10.1007/s42064-023-0166-4","url":null,"abstract":"<div><p>Understanding the internal composition of a celestial body is fundamental for formulating theories regarding its origin. Deep knowledge of the distribution of mass under the body’s crust can be achieved by analyzing its moments of inertia and gravity field. In this regard, the two moons of the Martian system have not yet been closely studied and continue to pose questions regarding their origin to the space community; thus, they deserve further characterization. The Martian Moons eXploration mission will be the first of its kind to sample and study Phobos over a prolonged period. This study aims to demonstrate that the adoption of periodic and quasi-periodic retrograde trajectories would be beneficial for the scientific value of the mission. Here, a covariance analysis was implemented to compare the estimation of high-order gravitational field coefficients from different orbital geometries and for different sets of processed observables. It was shown that the adoption of low-altitude non-planar quasi-satellite orbits would help to refine the knowledge of the moon’s libration angle and gravitational field.</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":"2023-07-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-023-0166-4.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50009544","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"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: 1

Optimal interplanetary trajectories for Sun-facing ideal diffractive sails 面向太阳的理想衍射帆的最佳行星际轨迹

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-06-16 DOI: 10.1007/s42064-023-0158-4

Alessandro A. Quarta, Giovanni Mengali, Marco Bassetto, Lorenzo Niccolai

{"title":"Optimal interplanetary trajectories for Sun-facing ideal diffractive sails","authors":"Alessandro A. Quarta, Giovanni Mengali, Marco Bassetto, Lorenzo Niccolai","doi":"10.1007/s42064-023-0158-4","DOIUrl":"10.1007/s42064-023-0158-4","url":null,"abstract":"<div><p>A diffractive sail is a solar sail whose exposed surface is covered by an advanced diffractive metamaterial film with engineered optical properties. This study examines the optimal performance of a diffractive solar sail with a Sun-facing attitude in a typical orbit-to-orbit heliocentric transfer. A Sun-facing attitude, which can be passively maintained through the suitable design of the sail shape, is obtained when the sail nominal plane is perpendicular to the Sun–spacecraft line. Unlike an ideal reflective sail, a Sun-facing diffractive sail generates a large transverse thrust component that can be effectively exploited to change the orbital angular momentum. Using a recent thrust model, this study determines the optimal control law of a Sun-facing ideal diffractive sail and simulates the minimum transfer times for a set of interplanetary mission scenarios. It also quantifies the performance difference between Sun-facing diffractive sail and reflective sail. A case study presents the results of a potential mission to the asteroid 16 Psyche.</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":"2023-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-023-0158-4.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50031769","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"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: 3

Orbital radius keeping of floating partial space elevator in cargo transposition 浮动部分空间升降机在货物换位中的轨道半径保持

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-06-16 DOI: 10.1007/s42064-022-0156-y

Gefei Shi, Zheng H. Zhu

引用次数: 0

Attitude maneuvers avoiding forbidden directions 姿态机动避开禁止的方向

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-06-16 DOI: 10.1007/s42064-023-0163-7

David Ailabouni, Andreas Meister, Karlheinz Spindler

{"title":"Attitude maneuvers avoiding forbidden directions","authors":"David Ailabouni, Andreas Meister, Karlheinz Spindler","doi":"10.1007/s42064-023-0163-7","DOIUrl":"10.1007/s42064-023-0163-7","url":null,"abstract":"<div><p>Many space missions require the execution of large-angle attitude slews during which stringent pointing constraints must be satisfied. For example, the pointing direction of a space telescope must be kept away from directions to bright objects, maintaining a prescribed safety margin. In this paper we propose an open-loop attitude control algorithm which determines a rest-to-rest maneuver between prescribed attitudes while ensuring that any of an arbitrary number of body-fixed directions of light-sensitive instruments stays clear of any of an arbitrary number of space-fixed directions. The approach is based on an application of a version of Pontryagin’s Maximum Principle tailor-made for optimal control problems on Lie groups, and the pointing constraints are ensured by a judicious choice of the cost functional. The existence of up to three first integrals of the resulting system equations is established, depending on the number of light-sensitive and forbidden directions. These first integrals can be exploited in the numerical implementation of the attitude control algorithm, as is shown in the case of one light-sensitive and several forbidden directions. The results of the test cases presented confirm the applicability of the proposed algorithm.</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":"2023-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-023-0163-7.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50031770","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"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

Midcourse correction of Earth-Moon distant retrograde orbit transfer trajectories based on high-order state transition tensors 基于高阶态跃迁张量的地月远逆行轨道转移轨迹中途修正

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-06-15 DOI: 10.1007/s42064-023-0162-8

Yongchen Yin, Ming Wang, Yu Shi, Hao Zhang

{"title":"Midcourse correction of Earth-Moon distant retrograde orbit transfer trajectories based on high-order state transition tensors","authors":"Yongchen Yin, Ming Wang, Yu Shi, Hao Zhang","doi":"10.1007/s42064-023-0162-8","DOIUrl":"10.1007/s42064-023-0162-8","url":null,"abstract":"<div><p>Midcourse correction design is key to space transfers in the cislunar space. Autonomous guidance has garnered significant attention for its promise to decrease the dependence on ground control systems. This study addresses the problem of midcourse corrections for Earth-Moon transfer orbits based on high-order state transition tensors (STTs). The scenarios considered are direct Earth-Moon transfers and low-energy transfers to lunar distant retrograde orbits (DROs), where the latter involve weak stability boundary (WSB) and lunar gravity assist (LGA) techniques. Semi-analytical formulas are provided for computing the trajectory correction maneuvers (TCMs) using high-order STTs derived using the differential algebraic method. Monte Carlo simulations are performed to evaluate the effectiveness of the proposed approach. Compared with existing explicit guidance algorithms, the STT-based approach is much cheaper computationally and features fewer final position errors. These results are promising for fast and efficient orbital autonomous correction guidance approaches in the cislunar space.</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":"2023-06-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-023-0162-8.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50028907","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"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