Astrodynamics最新文献_第2页

Multi-target spacecraft mission design using convex optimization and binary integer programming 基于凸优化和二进制整数规划的航天器多目标任务设计

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2026-02-24 DOI: 10.1007/s42064-025-0274-4

Jack Yarndley, Harry Holt, Roberto Armellin

{"title":"Multi-target spacecraft mission design using convex optimization and binary integer programming","authors":"Jack Yarndley, Harry Holt, Roberto Armellin","doi":"10.1007/s42064-025-0274-4","DOIUrl":"10.1007/s42064-025-0274-4","url":null,"abstract":"<div><p>The optimal design of multi-target rendezvous and flyby missions is challenging due to the combination of traditional spacecraft trajectory optimization and high-dimensional combinatorial problems. The typical approach to these problems generally requires large-scale global search techniques or simplified approximations relying on large amounts of manual labour to be performant. However, global search techniques are generally difficult to use in time- or cost-constrained scenarios due to their computational expense. This work proposes a novel combination of computationally efficient stages which work together to form a nested global optimization approach for multi-target mission design. The multi-target problem is split into seperate combinatorial and optimal control subproblems, which are recursively solved: the combinatorial problem using a novel Binary Integer Programming (BIP) formulation with fixed rendezvous timings obtaining optimal rendezvous ordering, and the optimal control problem with an adaptive-mesh Sequential Convex Programming (SCP) formulation obtaining optimal rendezvous timings for a fixed rendezvous ordering. These stages work recursively in tandem to improve the inputs to each subsequent stage until convergence is obtained. This methodology is demonstrated to offer state-of-the-art performance when applied to the Global Trajectory Optimization Competition 12 (GTOC 12) problem, to which several new best-known solutions are found.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 1","pages":"139 - 163"},"PeriodicalIF":6.5,"publicationDate":"2026-02-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-025-0274-4.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147341334","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

Design of natural Lissajous formations with nearly constant baselines 自然利萨尤地层的设计与几乎恒定的基线

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2026-02-16 DOI: 10.1007/s42064-025-0277-1

Sergey P. Trofimov, Maksim G. Shirobokov, Denis G. Perepukhov, Sergey A. Shestakov

引用次数: 0

Random Fibonacci sampling and region division: A numerical analysis of constellation coverage 随机斐波那契抽样和区域划分：星座覆盖的数值分析

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2026-02-07 DOI: 10.1007/s42064-025-0268-2

Yiqiang Zeng, Caohuo Ban, Kefei Zhang, Hexi Baoyin, Peng Zhang

{"title":"Random Fibonacci sampling and region division: A numerical analysis of constellation coverage","authors":"Yiqiang Zeng, Caohuo Ban, Kefei Zhang, Hexi Baoyin, Peng Zhang","doi":"10.1007/s42064-025-0268-2","DOIUrl":"10.1007/s42064-025-0268-2","url":null,"abstract":"<div><p>Coverage analysis serves as the foundation for designing the communication or remote sensing satellite constellations. The classical numerical method, grid-point approach (GPA), is widely utilized in constellation coverage analysis, yet it encounters challenges such as uneven grid distribution and substantial computational demands. In this paper, we introduce a random Fibonacci sampling method (RFSM) to achieve a more balanced distribution of sampling points, alongside a k-means region division method (KRDM) to enhance computational efficiency. In the RFSM, discrete sampling points replace grids for evaluating coverage performance. By incorporating randomness into the Fibonacci lattices method, we ensure that the sampling points exhibit a random uniform distribution. This allows for the amalgamation of coverage data from different sets of sampling points and the dynamic adjustment of the number of sampling points during computation. In the KRDM, we divide the whole target region into several sub-regions using the k-means algorithm, followed by calculating their respective visible windows. Numerical simulations demonstrate that the proposed method significantly enhances computational efficiency without compromising accuracy, achieving speed improvements of one or two orders of magnitude compared to the classical GPA. These findings suggest that the proposed method holds considerable promise for expediting constellation coverage performance calculations on a broader scale.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 1","pages":"73 - 88"},"PeriodicalIF":6.5,"publicationDate":"2026-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147338027","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

Disturbance observer-based fixed-time control for space tether system with prescribed performance after capturing debris 基于扰动观测器的空间系绳系统捕获碎片后的定时控制

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2026-02-04 DOI: 10.1007/s42064-025-0271-7

Peijie Sun, Changqing Wang, Hongshi Lu, Aijun Li, Yuriy Zabolotnov

{"title":"Disturbance observer-based fixed-time control for space tether system with prescribed performance after capturing debris","authors":"Peijie Sun, Changqing Wang, Hongshi Lu, Aijun Li, Yuriy Zabolotnov","doi":"10.1007/s42064-025-0271-7","DOIUrl":"10.1007/s42064-025-0271-7","url":null,"abstract":"<div><p>This paper studies the dynamic and control problems of space tether system (STS) after capturing space debris. The fully integrated system post-capture is referred to as space tether debris-assembly (STDA), while the system comprising the capture device and debris is termed the debris assembly. A significant challenge in stabilizing STS after debris capture lies in the residual angular momentum of the debris, which, if unmitigated, coupled with the relative angular velocity difference between the debris and the tether, can lead to detrimental effects such as tether entanglement and system destabilization. Furthermore, STDA system experiences unknown mass parameter variations that exacerbate control difficulties. To address these challenges, this paper proposes a nonlinear control strategy designed to rapidly stabilize the attitude motion of the end body, despite uncertainties in mass parameters and boundary constraints. A dynamic model of STDA system, encompassing the host spacecraft, tether, capture device, and space debris, is formulated based on Lagrangian equation. This model accounts for the relative attitude motion between the debris-assembly and the tether, as well as the attitude dynamics of the tether itself, thereby enabling an analysis of disturbances arising from unknown mass parameters and collision-induced angular motion. To mitigate these disturbances, a sliding mode disturbance observer is developed to compensate for dynamic uncertainties associated with the space debris’ unknown mass. Furthermore, an error transformation is performed, and a prescribed performance controller is designed to ensure that the system remains within predefined boundaries during stabilization. The effectiveness of the proposed method is validated through numerical simulations.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 1","pages":"123 - 137"},"PeriodicalIF":6.5,"publicationDate":"2026-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147336748","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 model-free prescribed performance control for spacecraft proximity operations with safety concerns 具有安全考虑的航天器近距离操作自适应无模型规定性能控制

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2026-02-04 DOI: 10.1007/s42064-025-0269-1

Qi Li, Shuo Song, Chong Sun, Zhiqi Niu, Yungang Yang, Sheng Luo

{"title":"Adaptive model-free prescribed performance control for spacecraft proximity operations with safety concerns","authors":"Qi Li, Shuo Song, Chong Sun, Zhiqi Niu, Yungang Yang, Sheng Luo","doi":"10.1007/s42064-025-0269-1","DOIUrl":"10.1007/s42064-025-0269-1","url":null,"abstract":"<div><p>In this paper, the issue of robust safety control for spacecraft proximity operations is investigated in the presence of model uncertainties and external disturbances. Initially, a line-of-sight-based relative dynamics model is established to describe the translational motion between the chaser spacecraft and the target spacecraft, based on this, a novel two-stage safety constraint including keep-out zone (Stage I) and field-of-view (FOV) corridor (Stage II) is introduced. Then, an adaptive model-based control scheme is proposed by exploiting the prescribed performance control approach. In addition, a neural networks-based model-free controller that relies only on the input/output measurement data is designed, which is more effective in the unknown and complex proximity process. It is shown that the derived controller can provide an online safety proximity trajectory for the chaser spacecraft while guaranteeing a prescribed convergence performance. Finally, simulations are given to verify the superiorities of the proposed method.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 1","pages":"89 - 102"},"PeriodicalIF":6.5,"publicationDate":"2026-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147336747","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

Dynamics modeling and optimization of an asymmetric two-stage torsion pendulum for drag-free testing in the Taiji mission 太极任务非对称两级无阻扭摆动力学建模与优化

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2026-02-04 DOI: 10.1007/s42064-025-0270-8

Qifan Liu, Xiaokui Yue, Zhaohui Dang, Chu Zhang, Yonghe Zhang

{"title":"Dynamics modeling and optimization of an asymmetric two-stage torsion pendulum for drag-free testing in the Taiji mission","authors":"Qifan Liu, Xiaokui Yue, Zhaohui Dang, Chu Zhang, Yonghe Zhang","doi":"10.1007/s42064-025-0270-8","DOIUrl":"10.1007/s42064-025-0270-8","url":null,"abstract":"<div><p>This paper investigates the dynamics modeling and structural optimization of an asymmetric two-stage torsion pendulum designed for drag-free testing in the Taiji mission. This torsion pendulum serves as a critical experimental apparatus for ground-based verification of drag-free control technology in space gravitational wave detection, addressing limitations in dynamic stability and parameter applicability found in traditional testbeds. Using the Lagrangian dynamics method, the equations of motion relative to inertial space are derived and simplified into a linearized dynamics model under the assumption of small-amplitude oscillations. A state-space approach is further employed to analyze the system’s free oscillation behavior, with equilibrium stability rigorously assessed through eigenvalue analysis. Compared to existing approaches, the proposed model significantly enhances computational efficiency and systematically reveals the influence of key structural parameters on system stability. The study identifies critical parameter ranges essential for ensuring system stability, with optimization results demonstrating that proper design and adjustment of structural parameters can substantially improve system robustness and performance. Numerical simulations validate the accuracy of the proposed models and methods, with the optimization scheme showing clear superiority in enhancing system performance and simplifying experimental design. This work establishes a rigorous theoretical framework for ground-based verification of drag-free control technology. It not only effectively addresses bottlenecks in traditional testbed designs but also offers innovative guidance for the development of experimental systems in the Taiji mission.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 1","pages":"103 - 122"},"PeriodicalIF":6.5,"publicationDate":"2026-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147336629","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

Implementation and analysis of different geomagnetic field models for attitude determination and control system (ADCS) of a satellite 卫星姿态确定与控制系统中不同地磁场模型的实现与分析

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2026-02-03 DOI: 10.1007/s42064-025-0283-3

Hoor Bano, Tatiana Podladchikova, Bisma Sajid, Dmitry Ris

{"title":"Implementation and analysis of different geomagnetic field models for attitude determination and control system (ADCS) of a satellite","authors":"Hoor Bano, Tatiana Podladchikova, Bisma Sajid, Dmitry Ris","doi":"10.1007/s42064-025-0283-3","DOIUrl":"10.1007/s42064-025-0283-3","url":null,"abstract":"<div><p>An attitude determination and control system (ADCS) is essential for orientation stability and performance of slew maneuvers on the satellite. This research focuses on comparing two different geomagnetic field models, direct dipole model and International Geomagnetic Reference Field model, for modeling of magnetometer and magnetorquers. Both these magnetic field models are compared and analyzed for two satellite attitude cases: orientation stability and unloading of reaction wheels. Magnetometer modeling is utilized to get sensor data for attitude determination and control to attain orientation stability. Whereas, the magnetorquer model aids in reaction wheel unloading, by performing the required actuation on the satellite, upon interaction with the Earth’s magnetic field. The study offers a comprehensive lookout on the impact of geomagnetic field models on the overall ADCS performance, incorporating both attitude estimation and control via the sensor and actuator modeling. Apart from this, valuable insights are gained into selecting optimal models based on specific mission requirements and available computational resources. Finally, this comparison and analysis results in unique findings for an actual future satellite mission, that is to be launched soon.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 1","pages":"165 - 177"},"PeriodicalIF":6.5,"publicationDate":"2026-02-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147336789","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

Disturbance-Free Payload spacecraft modeling and control: Non-contact architecture for high-precision space missions 无干扰有效载荷航天器建模与控制：高精度空间任务的非接触结构

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2026-02-03 DOI: 10.1007/s42064-025-0266-4

Wei Zhang, Yanbin Zhao, Dongyu Li

{"title":"Disturbance-Free Payload spacecraft modeling and control: Non-contact architecture for high-precision space missions","authors":"Wei Zhang, Yanbin Zhao, Dongyu Li","doi":"10.1007/s42064-025-0266-4","DOIUrl":"10.1007/s42064-025-0266-4","url":null,"abstract":"<div><p>In-orbit pointing accuracy and pointing stability are two of the most important technical indicators for ensuring the effective operation of the payload. Traditionally, these two indicators are guaranteed by the attitude control system of the support module. The ever-increasing demands of space missions, along with the flexibility of spacecraft and the presence of both internal and external disturbances, make it a challenge to enhance the accuracy and stability of the attitude control system in the overall design. The Disturbance-Free Payload architecture, which separates the payload module from the support module to provide natural vibration isolation, has been developed and promoted. This article provides an overview of its modeling and control methods, introducing general dynamic equations and advanced motion control techniques. In addition, this article presents the performance verification methods, including the numerical simulation logic, the ground verification platform setup, and the in-orbit model. Written in a tutorial style to familiarize researchers with the essentials, this paper serves as a reference for the design and practice of Disturbance-Free Payload high-performance spacecraft.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 1","pages":"1 - 24"},"PeriodicalIF":6.5,"publicationDate":"2026-02-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147336788","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

Real-time onboard orbit propagator for planetary missions 用于行星任务的实时机载轨道传播器

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2026-01-21 DOI: 10.1007/s42064-025-0264-6

Tommaso Torrini, Antonio Genova, Simone Andolfo, Anna Maria Gargiulo, Pierluigi Federici, Riccardo Teodori, Martina Ciambellini

{"title":"Real-time onboard orbit propagator for planetary missions","authors":"Tommaso Torrini, Antonio Genova, Simone Andolfo, Anna Maria Gargiulo, Pierluigi Federici, Riccardo Teodori, Martina Ciambellini","doi":"10.1007/s42064-025-0264-6","DOIUrl":"10.1007/s42064-025-0264-6","url":null,"abstract":"<div><p>Developing autonomous navigation systems for orbital platforms represents a frontier challenge in solar system exploration. A crucial element of such systems is the orbital propagator, which must accurately predict the spacecraft trajectory. Over short time scales, accurate state propagation is essential for processing data from onboard sensors within a sequential filter, ensuring consistent state updates and preventing filter divergence. Over extended time spans, the capability to accurately propagate the spacecraft trajectory could enhance onboard autonomy, enabling tasks like planning orbit correction maneuvers or supporting on-orbit servicing. This paper presents an orbital propagation scheme tailored for planetary and close-proximity scenarios, achieving high accuracy through comprehensive modeling of gravitational and non-conservative forces. While high-sensitivity scientific payloads, such as accelerometers, can measure small non-conservative perturbations, their high costs and the need for offline calibration to mitigate noise and spurious signals limit their real-time applicability. Instead, the proposed propagator integrates these perturbations through mathematical modeling, ensuring robust and cost-effective trajectory predictions for extended durations. A software-in-the-loop testing and validation campaign, focused on mission scenarios around the Moon and Mars, demonstrates the propagator’s compliance with accuracy and performance requirements for autonomous orbit determination and control. These results validate the scheme’s applicability for future exploration missions requiring minimal ground-based support.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 1","pages":"25 - 51"},"PeriodicalIF":6.5,"publicationDate":"2026-01-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147341222","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

TABLF-based finite-time cooperative guidance law for a maneuvering target with a field-of-view constraint 具有视场约束的机动目标基于tabf的有限时间协同制导律

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2026-01-21 DOI: 10.1007/s42064-025-0265-5

Haoyu Cheng, Chengxuan Li, Biyu Zheng, Hanqiao Huang, Xin Liu

{"title":"TABLF-based finite-time cooperative guidance law for a maneuvering target with a field-of-view constraint","authors":"Haoyu Cheng, Chengxuan Li, Biyu Zheng, Hanqiao Huang, Xin Liu","doi":"10.1007/s42064-025-0265-5","DOIUrl":"10.1007/s42064-025-0265-5","url":null,"abstract":"<div><p>This paper presents a finite-time cooperative guidance approach aimed at intercepting maneuverable targets while ensuring that multiple missiles adhere to field-of-view (FOV) constraints throughout the interception process. A model for the missile-target relative motion is constructed, where the FOV constraint is redefined as an asymmetric, time-varying limit on the missile’s relative velocity perpendicular to the line-of-sight (LOS) direction. The proposed guidance method is divided into two components: one along the LOS direction and the other perpendicular to it. For the LOS direction, a multiagent consensus protocol is employed alongside a finite-time disturbance observer, ensuring that the interception timing of multiple missiles converges to a consistent value within a finite period. Perpendicular to the LOS, a finite-time guidance law is formulated using a time-varying asymmetric barrier Lyapunov function (TABLF) combined with adaptive control theory, ensuring that all missiles achieve the desired impact angle while maintaining compliance with the FOV constraints. The finite-time stability of the guidance law is validated using Lyapunov theory. Finally, the effectiveness of the cooperative guidance strategy, including FOV compliance, is demonstrated through numerical simulations.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 1","pages":"53 - 71"},"PeriodicalIF":6.5,"publicationDate":"2026-01-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147341223","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