Astrodynamics最新文献_第6页

Applications of knot theory to the detection of heteroclinic connections between quasi-periodic orbits 绳结理论在探测准周期轨道间异质连接中的应用

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-04-15 DOI: 10.1007/s42064-024-0201-0

Danny Owen, Nicola Baresi

引用次数: 0

Precise orbit determination for low Earth orbit satellites using GNSS: Observations, models, and methods 利用全球导航卫星系统精确确定低地球轨道卫星的轨道：观测、模型和方法

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-04-11 DOI: 10.1007/s42064-023-0195-z

Xinyuan Mao, Wenbing Wang, Yang Gao

{"title":"Precise orbit determination for low Earth orbit satellites using GNSS: Observations, models, and methods","authors":"Xinyuan Mao, Wenbing Wang, Yang Gao","doi":"10.1007/s42064-023-0195-z","DOIUrl":"10.1007/s42064-023-0195-z","url":null,"abstract":"<div><p>Spaceborne global navigation satellite system (GNSS) has significantly revolutionized the development of autonomous orbit determination techniques for low Earth orbit satellites for decades. Using a state-of-the-art combination of GNSS observations and satellite dynamics, the absolute orbit determination for a single satellite reached a precision of 1 cm. Relative orbit determination (i.e., precise baseline determination) for the dual satellites reached a precision of 1 mm. This paper reviews the recent advancements in GNSS products, observation processing, satellite gravitational and non-gravitational force modeling, and precise orbit determination methods. These key aspects have increased the precision of the orbit determination to fulfill the requirements of various scientific objectives. Finally, recommendations are made to further investigate multi-GNSS combinations, satellite high-fidelity geometric models, geometric offset calibration, and comprehensive orbit determination strategies for satellite constellations.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"8 3","pages":""},"PeriodicalIF":2.7,"publicationDate":"2024-04-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140714002","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

On-ground validation of orbital GNC: Visual navigation assessment in robotic testbed facility 轨道 GNC 的地面验证：机器人试验台设施中的视觉导航评估

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2024-03-20 DOI: 10.1007/s42064-024-0198-4

Vivek Muralidharan, Mohatashem Reyaz Makhdoomi, Augustinas Žinys, Bronislovas Razgus, Marius Klimavičius, Miguel Olivares-Mendez, Carol Martinez

{"title":"On-ground validation of orbital GNC: Visual navigation assessment in robotic testbed facility","authors":"Vivek Muralidharan, Mohatashem Reyaz Makhdoomi, Augustinas Žinys, Bronislovas Razgus, Marius Klimavičius, Miguel Olivares-Mendez, Carol Martinez","doi":"10.1007/s42064-024-0198-4","DOIUrl":"10.1007/s42064-024-0198-4","url":null,"abstract":"<div><p>CubeSats have become versatile platforms for various space missions (e.g., on-orbit servicing and debris removal) owing to their low cost and flexibility. Many space tasks involve proximity operations that require precise guidance, navigation, and control (GNC) algorithms. Vision-based navigation is attracting interest for such operations. However, extreme lighting conditions in space challenge optical techniques. The on-ground validation of such navigation systems for orbital GNC becomes crucial to ensure their reliability during space operations. These systems undergo rigorous testing within their anticipated operational parameters, including the exploration of potential edge cases. The ability of GNC algorithms to function effectively under extreme space conditions that exceed anticipated scenarios is crucial, particularly in space missions where the scope of errors is negligible. This paper presents the ground validation of a GNC algorithm designed for autonomous satellite rendezvous by leveraging hardware-in-the-loop experiments. This study focuses on two key areas. First, the rationale underlying the augmentation of the robot workspace (six-degree-of-freedom UR10e robot + linear rail) is investigated to emulate relatively longer trajectories with complete position and orientation states. Second, the control algorithm is assessed in response to uncertain pose observations from a vision-based navigation system. The results indicate increased control costs with uncertain navigation and exemplify the importance of on-ground testing for system validation before launch, particularly in extreme cases that are typically difficult to assess using software-based testing.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 3","pages":"343 - 367"},"PeriodicalIF":6.5,"publicationDate":"2024-03-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-024-0198-4.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140224546","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

The OPS-SAT case: A data-centric competition for onboard satellite image classification OPS-SAT 案例：以数据为中心的机载卫星图像分类竞赛

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-03-16 DOI: 10.1007/s42064-023-0196-y

Gabriele Meoni, Marcus Märtens, Dawa Derksen, Kenneth See, Toby Lightheart, Anthony Sécher, Arnaud Martin, David Rijlaarsdam, Vincenzo Fanizza, Dario Izzo

{"title":"The OPS-SAT case: A data-centric competition for onboard satellite image classification","authors":"Gabriele Meoni, Marcus Märtens, Dawa Derksen, Kenneth See, Toby Lightheart, Anthony Sécher, Arnaud Martin, David Rijlaarsdam, Vincenzo Fanizza, Dario Izzo","doi":"10.1007/s42064-023-0196-y","DOIUrl":"10.1007/s42064-023-0196-y","url":null,"abstract":"<div><p>While novel artificial intelligence and machine learning techniques are evolving and disrupting established terrestrial technologies at an unprecedented speed, their adaptation onboard satellites is seemingly lagging. A major hindrance in this regard is the need for high-quality annotated data for training such systems, which makes the development process of machine learning solutions costly, time-consuming, and inefficient. This paper presents “the OPS-SAT case”, a novel data-centric competition that seeks to address these challenges. The powerful computational capabilities of the European Space Agency’s OPS-SAT satellite are utilized to showcase the design of machine learning systems for space by using only the small amount of available labeled data, relying on the widely adopted and freely available open-source software. The generation of a suitable dataset, design and evaluation of a public data-centric competition, and results of an onboard experimental campaign by using the competition winners’ machine learning model directly on OPS-SAT are detailed. The results indicate that adoption of open standards and deployment of advanced data augmentation techniques can retrieve meaningful onboard results comparatively quickly, simplifying and expediting an otherwise prolonged development period.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"8 4","pages":"507 - 528"},"PeriodicalIF":2.7,"publicationDate":"2024-03-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-023-0196-y.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142412054","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

Spaceborne and ground-based sensor collaboration: Advancing resident space objects’ orbit determination for space sustainability 空间和地面传感器合作：推进常驻空间物体的轨道确定，促进空间可持续性

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-03-14 DOI: 10.1007/s42064-023-0193-1

Niki Sajjad, Mehran Mirshams, Andreas Makoto Hein

{"title":"Spaceborne and ground-based sensor collaboration: Advancing resident space objects’ orbit determination for space sustainability","authors":"Niki Sajjad, Mehran Mirshams, Andreas Makoto Hein","doi":"10.1007/s42064-023-0193-1","DOIUrl":"10.1007/s42064-023-0193-1","url":null,"abstract":"<div><p>The limited space around the Earth is getting cluttered with leftover fragments from old missions, creating a real challenge. As more satellites are launched, even debris pieces as small as 5 mm must be tracked to avoid collisions. However, it is an arduous and challenging task in space. This paper presents a technical exploration of ground-based and in-orbit space debris tracking and orbit determination methods. It highlights the challenges faced during on-ground and in-orbit demonstrations, identifies current gaps, and proposes solutions following technological advancements, such as low-power pose estimation methods. Owing to the numerous atmospheric barriers to ground-based sensors, this study emphasizes the significance of spaceborne sensors for precise orbit determination, complemented by advanced data processing algorithms and collaborative efforts. The ultimate goal is to create a comprehensive catalog of resident space objects (RSO) around the Earth and promote space environment sustainability. By exploring different methods and finding innovative solutions, this study contributes to the protection of space for future exploration and the creation of a more transparent and precise map of orbital objects.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"8 3","pages":""},"PeriodicalIF":2.7,"publicationDate":"2024-03-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140241860","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

A comparative assessment of gravitational field modeling methods for binary asteroid landing 双小行星着陆引力场建模方法比较评估

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-03-13 DOI: 10.1007/s42064-024-0202-z

Tongge Wen, Xiangyuan Zeng, Ziwen Li, Yang Yu

引用次数: 0

Evaluation of E-sail parameters on central spacecraft attitude stability using a high-fidelity rigid-flexible coupling model 利用高保真刚柔耦合模型评估电子风帆参数对中心航天器姿态稳定性的影响

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-03-13 DOI: 10.1007/s42064-023-0190-4

Chonggang Du, Zheng H. Zhu, Changqing Wang, Aijun Li, Tuanjie Li

{"title":"Evaluation of E-sail parameters on central spacecraft attitude stability using a high-fidelity rigid-flexible coupling model","authors":"Chonggang Du, Zheng H. Zhu, Changqing Wang, Aijun Li, Tuanjie Li","doi":"10.1007/s42064-023-0190-4","DOIUrl":"10.1007/s42064-023-0190-4","url":null,"abstract":"<div><p>This study examines the impact of electric solar wind sail (E-sail) parameters on the attitude stability of E-sail’s central spacecraft by using a comprehensive rigid-flexible coupling dynamic model. In this model, the nodal position finite element method is used to model the elastic deformation of the tethers through interconnected two-node tensile elements. The attitude dynamics of the central spacecraft is described using a natural coordinate formulation. The rigid-flexible coupling between the central spacecraft and its flexible tethers is established using Lagrange multipliers. Our research reveals the significant influences of parameters such as tether numbers, tether’s electric potential, and solar wind velocity on attitude stability. Specifically, solar wind fluctuations and the distribution of electric potential on the main tethers considerably affect the attitude stability of the spacecraft. For consistent management, the angular velocities of the spacecraft must remain at target values. Moreover, the attitude stability of a spacecraft has a pronounced dependence on the geometrical configuration of the E-sail, with axisymmetric E-sails proving to be more stable.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"8 2","pages":"271 - 284"},"PeriodicalIF":2.7,"publicationDate":"2024-03-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140245287","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

Optimization of body configuration and joint-driven attitude stabilization for transformable spacecraft under solar radiation pressure 太阳辐射压力下可变型航天器的机体配置和关节驱动姿态稳定优化

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-02-08 DOI: 10.1007/s42064-023-0167-3

Yuki Kubo, Toshihiro Chujo

{"title":"Optimization of body configuration and joint-driven attitude stabilization for transformable spacecraft under solar radiation pressure","authors":"Yuki Kubo, Toshihiro Chujo","doi":"10.1007/s42064-023-0167-3","DOIUrl":"10.1007/s42064-023-0167-3","url":null,"abstract":"<div><p>The solar sail is one of the most promising space exploration systems due to its theoretically infinite specific impulse achieved through solar radiation pressure (SRP). Recently, researchers have proposed “transformable spacecraft” capable of actively reconfiguring their body configurations using actuatable joints. Transformable spacecraft, if used similarly to solar sails, are expected to significantly enhance orbit and attitude control capabilities owing to their high redundancy in control degrees of freedom. However, controlling them becomes challenging due to their large number of inputs, leading previous researchers to impose strong constraints to limit their potential control capabilities. This study focuses on novel attitude control techniques for transformable spacecraft under SRP. We developed two methods, namely, joint angle optimization to obtain arbitrary SRP force and torque, and momentum damping control driven by joint angle actuation. Our proposed methods are formulated in a general manner and can be applied to any transformable spacecraft comprising front faces that can predominantly receive the SRP on each body. The validity of our proposed method is confirmed through numerical simulations. Our study contributes to making most of the high control redundancy of transformable spacecraft without the need for expendable propellants, thus significantly enhancing the orbit and attitude control capabilities.\u0000</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"8 1","pages":"47 - 60"},"PeriodicalIF":2.7,"publicationDate":"2024-02-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142410577","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

Characterization of Gauss–Markov stochastic sequences for mission analysis 用于任务分析的高斯-马尔科夫随机序列的特征描述

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-02-08 DOI: 10.1007/s42064-023-0183-3

Carmine Giordano

{"title":"Characterization of Gauss–Markov stochastic sequences for mission analysis","authors":"Carmine Giordano","doi":"10.1007/s42064-023-0183-3","DOIUrl":"10.1007/s42064-023-0183-3","url":null,"abstract":"<div><p>In real scenarios, the spacecraft deviates from the intended paths owing to uncertainties in dynamics, navigation, and command actuation. Accurately quantifying these uncertainties is crucial for assessing the observability, collision risks, and mission viability. This issue is further magnified for CubeSats because they have limited control authority and thus require accurate dispersion estimates to avoid rejecting viable trajectories or selecting unviable ones. Trajectory uncertainties arise from random variables (e.g., measurement errors and drag coefficients) and processes (e.g., solar radiation pressure and low-thrust acceleration). Although random variables generally present minimal computational complexity, handling stochastic processes can be challenging because of their noisy dynamics. Nonetheless, accurately modeling these processes is essential, as they significantly influence the uncertain propagation of space trajectories, and an inadequate representation can result in either underestimation or overestimation of the stochastic characteristics associated with a given trajectory. This study addresses the gap in characterizing process uncertainties, represented as Gauss–Markov processes in mission analysis, by presenting models, evaluating derived quantities, and providing results on the impact of spacecraft trajectories. This study emphasizes the importance of accurately modeling random processes to properly characterize stochastic spacecraft paths.\u0000</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"8 1","pages":"135 - 148"},"PeriodicalIF":2.7,"publicationDate":"2024-02-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-023-0183-3.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142410561","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

Direct-to-indirect mapping for optimal low-thrust trajectories 优化低推力轨迹的直接到直接映射

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-02-08 DOI: 10.1007/s42064-023-0164-6

David Ottesen, Ryan P. Russell

{"title":"Direct-to-indirect mapping for optimal low-thrust trajectories","authors":"David Ottesen, Ryan P. Russell","doi":"10.1007/s42064-023-0164-6","DOIUrl":"10.1007/s42064-023-0164-6","url":null,"abstract":"<div><p>Optimal, many-revolution spacecraft trajectories are challenging to solve. A connection is made for a class of models between optimal direct and indirect solutions. For transfers that minimize thrust-acceleration-squared, primer vector theory maps direct, many-impulsive-maneuver trajectories to the indirect, continuous-thrust-acceleration equivalent. The mapping algorithm is independent of how the direct solution is obtained and requires only a solver for a boundary value problem and its partial derivatives. A Lambert solver is used for the two-body problem in this work. The mapping is simple because the impulsive maneuvers and co-states share the same linear space around an optimal trajectory. For numerical results, the direct coast-impulse solutions are demonstrated to converge to the indirect continuous solutions as the number of impulses and segments increases. The two-body design space is explored with a set of three many-revolution, many-segment examples changing semimajor axis, eccentricity, and inclination. The first two examples involve a small change to either semimajor axis or eccentricity, and the third example is a transfer to geosynchronous orbit. Using a single processor, the optimization runtime is seconds to minutes for revolution counts of 10 to 100, and on the order of one hour for examples with up to 500 revolutions. Any of these thrust-acceleration-squared solutions are good candidates to start a homotopy to a higher-fidelity minimization problem with practical constraints.\u0000</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"8 1","pages":"27 - 46"},"PeriodicalIF":2.7,"publicationDate":"2024-02-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139790911","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