Astrodynamics最新文献_第3页

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

Attitude-adjusting dynamical behavior of cubic rover on low-gravity testbed 立方体漫游车在低重力试验台上的姿态调整动力学行为

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-02-08 DOI: 10.1007/s42064-023-0185-1

Bowen Jiang, Muhammad Talha Hussain, Xiangyuan Zeng

引用次数: 0

Lunar orbits for telecommunication and navigation services 用于电信和导航服务的月球轨道

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-02-08 DOI: 10.1007/s42064-023-0191-3

Marco Cinelli, Emiliano Ortore, Giovanni Mengali, Alessandro A. Quarta, Christian Circi

引用次数: 0

Review of dynamics and active control of large-scale space membrane antenna 大型空间膜天线动力学和主动控制综述

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-02-08 DOI: 10.1007/s42064-023-0181-5

Xiang Liu, Guoping Cai

{"title":"Review of dynamics and active control of large-scale space membrane antenna","authors":"Xiang Liu, Guoping Cai","doi":"10.1007/s42064-023-0181-5","DOIUrl":"10.1007/s42064-023-0181-5","url":null,"abstract":"<div><p>Large-scale space membrane antennas have significant potential in satellite communication, space-based early warning, and Earth observation. Because of their large size and high flexibility, the dynamic analysis and control of membrane antenna are challenging. To maintain the working performance of the antenna, the pointing and surface accuracies must be strictly maintained. Therefore, the accurate dynamic modeling and effective active control of large-scale space membrane antennas have great theoretical significance and practical value, and have attracted considerable interest in recent years. This paper reviews the dynamics and active control of large-scale space membrane antennas. First, the development and status of large-scale space membrane antennas are summarized. Subsequently, the key problems in the dynamics and active control of large membrane antennas, including the dynamics of wrinkled membranes, large-amplitude nonlinear vibration, nonlinear model reduction, rigid-flexible-thermal coupling dynamic modeling, on-orbit modal parameter identification, active vibration control, and wave-based vibration control, are discussed in detail. Finally, the research outlook and future trends are presented.\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":"1 - 26"},"PeriodicalIF":2.7,"publicationDate":"2024-02-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139850951","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 high-order target phase approach for the station-keeping of periodic orbits 周期轨道驻留的高阶目标相位法

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2024-02-08 DOI: 10.1007/s42064-023-0169-1

Xiaoyu Fu, Nicola Baresi, Roberto Armellin

引用次数: 0