Astrodynamics最新文献

{"title":"Self-organized control of spacecraft formation flying on irregular curves for cooperative observation","authors":"Hao Zhou,&nbsp;Zhaohui Dang,&nbsp;Jianping Yuan","doi":"10.1007/s42064-025-0284-2","DOIUrl":"10.1007/s42064-025-0284-2","url":null,"abstract":"<div><p>This paper comprehensively studies the self-organized deployment of a spacecraft cluster on a smooth irregular closed curve for cooperative on-orbit observation of a target spacecraft. The expected configuration curve is constructed by a set of control points through cubic B-spline interpolation, and it is closed and C2 continuous on the entire curve including its endpoints. As a necessary step for designing the control law, an efficient iterative algorithm for calculating the maneuvering spacecraft’s nearest point on the curve is developed using Newton downhill method. Then the double-layer feedback controllers are designed, in which the inner controller makes the temporary target positions approximately uniformly converge to the curve, and the outer controller guides the actual positions to the temporary target positions. In this way, the spacecraft cluster can be accurately deployed on the desired curvilinear formation. The stability of the closed-loop system with the double-layer controller is also proved. Finally, a boat-shaped target configuration curve for comprehensively cooperatively observing a spherical target spacecraft is simulated and analyzed. The detailed results demonstrate that the designed self-organized control law can successfully achieve the desired formation flying with low control magnitude, acceptable accuracy, and reduce the influence of single spacecraft’s failure to the final configuration’s uniformity and the observation tasks.</p><div><figure><div><div><picture><source><img></source></picture><span>The alternative text for this image may have been generated using AI.</span></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 2","pages":"339 - 363"},"PeriodicalIF":6.5,"publicationDate":"2026-04-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147751216","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}

{"title":"Dynamic modeling and active vibration control of an on-orbit assembled planar phased array antenna with numerous revolute clearance hinges","authors":"Chaochen Jin,&nbsp;Xiang Liu,&nbsp;Guoping Cai,&nbsp;Fucheng Liu,&nbsp;Jun Sun,&nbsp;Dongfang Zhu","doi":"10.1007/s42064-025-0286-0","DOIUrl":"10.1007/s42064-025-0286-0","url":null,"abstract":"<div><p>The shape accuracy of a space phased array antenna is crucial in determining its performance. In the antenna structure, the clearances, geometric deviations, and flexibilities of numerous revolute hinges significantly affect the analysis and control of antenna shape accuracy. This paper proposes the comprehensive dynamic modeling method and active vibration control method of the antenna structure with numerous hinges. First, by introducing the nonlinear contact force of hinges into the finite element method, the nonlinear dynamic model of the antenna structure with hinge clearances and flexibilities is established. Based on the polynomial fitting method, a model order reduction method is employed to simplify the nonlinear dynamic model. Then, to address the geometric deviation problem of numerous hinges, a model updating method based on clustering optimization and frequency criterion is proposed. Finally, an active vibration control method using cable actuators is proposed to reduce the nonlinear vibration of the antenna structure with numerous hinges, and an actuator distribution optimization method is established. The numerical simulation results demonstrate that the proposed nonlinear dynamic model can well reflect the influence of the hinges on the antenna structure and that the proposed control method can effectively suppress the nonlinear vibration.</p><div><figure><div><div><picture><source><img></source></picture><span>The alternative text for this image may have been generated using AI.</span></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 2","pages":"365 - 382"},"PeriodicalIF":6.5,"publicationDate":"2026-04-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147751220","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}

{"title":"Field-of-view constrained three-dimensional impact time and angle guidance via dual-step joint approach","authors":"Peng Zhang,&nbsp;Nan Zhang,&nbsp;Zheng Dai,&nbsp;Yu Chen,&nbsp;Shengping Gong","doi":"10.1007/s42064-025-0280-6","DOIUrl":"10.1007/s42064-025-0280-6","url":null,"abstract":"<div><p>A field-of-view constrained three-dimensional impact time and angle guidance law is proposed in this paper. The challenging guidance problem formulated in the three-dimensional scenario while considering multiple constraints is addressed via the proposed dual-step joint approach. The guidance process consists of two steps. In the first step, the equiangular spiral shaping trajectory is conducted to achieve the desired impact time while adhering to the field-of-view constraint. In the second step, the field-of-view constrained impact angle guidance law is derived by employing the error dynamics and auxiliary function. The switching point between the guidance laws in the two steps needs to be determined quickly and accurately. The guidance parameters can be obtained efficiently by employing the three-point secant method, solving a nonlinear implicit equality with 2–3 iterations. Numerical simulation examples are provided to verify the performance of the proposed guidance law on different guidance constraints.</p><div><figure><div><div><picture><source><img></source></picture><span>The alternative text for this image may have been generated using AI.</span></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 2","pages":"299 - 317"},"PeriodicalIF":6.5,"publicationDate":"2026-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147751215","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}

{"title":"Review of trajectory design and optimization methods for ice giant exploration","authors":"Guoliang Liang,&nbsp;Yu Zhang,&nbsp;Hongwei Yang,&nbsp;Hexi Baoyin","doi":"10.1007/s42064-026-0308-6","DOIUrl":"10.1007/s42064-026-0308-6","url":null,"abstract":"<div><p>The exploration of ice giant systems represents one of the priority areas in deep space exploration for the coming decade. Owing to the vast orbital distances of these planets and the need for extensive in-system transfers during missions, trajectory design and optimization constitute a critical enabling technology for the exploration of ice giant systems. While numerous mission concepts and orbital design methodologies have been proposed to date, a comprehensive review of these methodologies is currently lacking, which hinders the further development of novel design techniques and the formulation of new mission proposals. This survey systematically synthesizes both established and state-of-the-art methods across four primary mission phases: interplanetary transfer, ice giant capture, planetary satellite tours, and other scientific observations targeting planets and comets. For each phase, different design strategies are introduced, with their advantages and capabilities described and analyzed to reveal technological progress. Finally, perspectives on future developments are provided, aiming to establish a reference framework for further research in trajectory design and optimization for ice giant system exploration.\u0000</p><div><figure><div><div><picture><source><img></source></picture><span>The alternative text for this image may have been generated using AI.</span></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 2","pages":"199 - 218"},"PeriodicalIF":6.5,"publicationDate":"2026-03-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147751217","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}

{"title":"Orbit reconstruction for HERMES-SP/TP satellite mission","authors":"Mile Karlica,&nbsp;Pavel Jefremov,&nbsp;Andrea Colagrossi,&nbsp;Michèle R. Lavagna,&nbsp;Andreja Gomboc","doi":"10.1007/s42064-025-0289-x","DOIUrl":"10.1007/s42064-025-0289-x","url":null,"abstract":"<div><p>We present techniques for the reconstruction of satellite’s low Earth equatorial orbit during a GPS coverage gap for HERMES Pathfinder mission. The HERMES Scientific+Technological Pathfinder mission is conceived to consist of six satellites in a circular, equatorial, low Earth orbit at a height of 500–550 km. Each satellite will be equipped with a single GPS antenna. Therefore, GPS coverage gaps, where the satellite cannot establish contact with at least four GPS satellites, can last up to 25 min. We developed two methods for orbit determination within the coverage gap using known satellite positions before and after the gap: (1) polynomial and Fourier interpolation and (2) first- and second-order corrections to the Keplerian orbit. We tested both methods on simulated data and found them suitable, giving the accuracy required for the location of a satellite ⩽30 m in &gt; 99% of simulated gaps. The robustness of the methods was examined against simulated orbits with different values of inclinations and eccentricities. The first method gives consistent performance against eccentricity for coverage gaps lasting up to 20 min, while it shows a noticeable drop in performance at eccentricities above 0.01 for 25 min long gaps. The performance of the second method does not change with eccentricity within the investigated range, it also does not strongly depend on inclination and remains &gt; 98%. With varying inclination, in the first method, the decrease in performance becomes evident for gaps longer than 20 min. The first method gives satellite position in the form of analytical function and can be used as a continuous satellite position determination procedure between two GPS telemetry updates, while the second method is limited by discrete output at expected GPS telemetry updates. Concerning the influence of solar activity on nanosatellite motion, all methods show similar levels of robustness and stability.</p><div><figure><div><div><picture><source><img></source></picture><span>The alternative text for this image may have been generated using AI.</span></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 2","pages":"383 - 400"},"PeriodicalIF":6.5,"publicationDate":"2026-03-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147751142","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}

{"title":"Optimization and deployment method of cislunar communication and navigation constellation based on libration point orbits","authors":"Zheyu Xu,&nbsp;Zicong An,&nbsp;Defeng Gu,&nbsp;Lan Du,&nbsp;Xiao Chen,&nbsp;Lisheng Tong","doi":"10.1007/s42064-025-0279-z","DOIUrl":"10.1007/s42064-025-0279-z","url":null,"abstract":"<div><p>The Earth–Moon libration point orbit (LPO) offers unique advantages in terms of location and dynamical characteristics, providing new opportunities for designing communication and navigation constellations. However, LPOs cannot be described by Keplerian elements and require significant computational resources for initial value searches, limiting their optimization potential. This paper proposes a two-step optimization algorithm based on a two-layer initial value library. The first layer represents orbit families, while the second layer contains orbits with varying amplitudes within each family. The first step of the algorithm quickly filters orbit families, and the second step selects the orbits that form the constellation, significantly reducing both the optimization scope and the number of parameters. We introduce a novel grid-based division of key cislunar regions and expand the constellation service area using a three-phase construction strategy. To evaluate the optimized constellation’s navigation capabilities, we test its performance with typical orbits, including Earth–Moon transfer orbit (EMTO), elliptical lunar orbits (ELO), and geosynchronous orbit (GEO). Experimental results show that a single near rectilinear halo orbit (NRHO) satellite provides single coverage of the Earth–Moon transfer critical region at sampling times, with an orbit determination (OD) accuracy of 475.7 m for the EMTO. Seven satellites, positioned on the <i>L</i>1, <i>L</i>2, <i>L</i>4, <i>L</i>5, and NRHO orbits, achieve quadruple coverage for both the Earth–Moon transfer and near-Moon regions, with OD accuracies of 25.7 and 17.3 m for the EMTO and ELO, respectively. In the third phase, adding two <i>L</i>3 LPO satellites forms a nine-satellite constellation, extending coverage across the entire cislunar space, achieving OD accuracies of 15.1, 13.4, and 2.2 m for the EMTO, ELO, and GEO, respectively. This study provides valuable insights for the future design and deployment of cislunar communication and navigation constellations.</p><div><figure><div><div><picture><source><img></source></picture><span>The alternative text for this image may have been generated using AI.</span></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 2","pages":"279 - 298"},"PeriodicalIF":6.5,"publicationDate":"2026-03-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147751218","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}

{"title":"Real-time autonomous guidance generation around small bodies via Sequential Convex Programming","authors":"Enrico Belloni,&nbsp;Michèle Lavagna","doi":"10.1007/s42064-025-0281-5","DOIUrl":"10.1007/s42064-025-0281-5","url":null,"abstract":"<div><p>This paper introduces a novel approach to real-time convex guidance generation for spacecraft navigating in proximity to small celestial bodies, such as asteroids or small moons. The proposed method leverages Sequential Convex Programming (SCP) techniques to model and navigate irregular gravity fields encountered near these bodies, addressing the strong nonlinearities by iteratively refining a convex guidance sub-problem. The key contribution is the development of an adaptive algorithm that autonomously determines the optimal time of flight and dynamically adjusts to the gravitational environment, enabling spacecraft to autonomously generate robust guidance trajectories in real time including a non-convex collision avoidance constraint. The algorithm is developed in library-free C code to be ready for real-time embedded implementation and gain a realistic understanding on possible onboard application. The efficacy of the proposed method is validated for both asteroids and small moons through numerical simulations including sliding-mode close-loop control, showcasing high accuracy, computational efficiency, and flexibility to different environments.</p><div><figure><div><div><picture><source><img></source></picture><span>The alternative text for this image may have been generated using AI.</span></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 2","pages":"319 - 337"},"PeriodicalIF":6.5,"publicationDate":"2026-03-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147751219","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}

{"title":"Finite-time fault-tolerant consensus control for multiple solar sail formation flying around heliocentric inclined elliptic displaced orbits","authors":"Lei Liu,&nbsp;Jinguo Liu,&nbsp;Xin Zhang","doi":"10.1007/s42064-025-0272-6","DOIUrl":"10.1007/s42064-025-0272-6","url":null,"abstract":"<div><p>This paper studies solar sail heliocentric inclined elliptic displaced orbits (HIEDOs) with the application of reflectivity control devices (RCDs). In the solar sail HIEDO, the angle between the line from the Sun to the focus and the elliptic orbital plane is variable. A novel method is given to solve the sail attitude angles and the state of RCDs to achieve HIEDOs. Furthermore, this paper analyzes the problem of multiple solar sail formation flying (MSSFF) around HIEDOs, which consists of a chief and multiple deputies. The chief moves in an HIEDO and does not need to obtain the information from the deputies. The deputies need to receive the information from the chief, and an undirected connected graph is adopted to represent the information exchange structure between the deputies. Considering the convergence speed and reliability of the solar sail formation system, an innovative finite-time fault-tolerant distributed coordinated control scheme is devised. Under this control scheme, the deputies can consistently converge to the expected solar sail formation configuration within a finite time, even in the presence of the actuator effectiveness faults within a certain range. Finally, an example is used to verify the validity of the designed control scheme.</p><div><figure><div><div><picture><source><img></source></picture><span>The alternative text for this image may have been generated using AI.</span></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 2","pages":"219 - 237"},"PeriodicalIF":6.5,"publicationDate":"2026-03-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147751145","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}

{"title":"Trajectory design for comet 67P/Churyumov–Gerasimenko mission: Multiple gravity assist analysis using Tisserand Graph","authors":"Zhuojin Li,&nbsp;Yangxin Wang,&nbsp;Vsevolod Koryanov","doi":"10.1007/s42064-025-0275-3","DOIUrl":"10.1007/s42064-025-0275-3","url":null,"abstract":"<div><p>Optimizing interplanetary trajectories is critical for advancing deep space exploration, as it minimizes energy requirements and facilitates efficient orbital insertions. This study presents a mission trajectory model to comet 67P/Churyumov–Gerasimenko, employing a two-step approach that combines the Tisserand Graph (TG) method with a Genetic Algorithm (GA). In the first step, the complex mixed-integer nonlinear programming (MINLP) problem is simplified into a combinatorial search using a TG-based Depth-Limited Tree Search (DLTS) algorithm, significantly narrowing the search space for initial guesses. Subsequently, the solution is refined through accelerated optimization with a GA. To address the fixed terminal phase constraint at comet 67P, a reverse-search strategy for launch windows reformulates the problem into a non-linear programming framework with one fixed and one free endpoint. As a result, 11 feasible trajectory scenarios to comet 67P within the next 15 years were found, validated across four launch vehicle options. To further minimize fuel consumption, the study adopts fuel consumption as the performance index and applies a continuation method to verify the feasibility of these transfers under various Hall thruster models for low-thrust propulsion. The proposed approach thus provides a validated, fuel-efficient set of trajectory options, significantly enhancing planning flexibility for comet 67P exploration in upcoming decades.</p><div><figure><div><div><picture><source><img></source></picture><span>The alternative text for this image may have been generated using AI.</span></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 2","pages":"239 - 259"},"PeriodicalIF":6.5,"publicationDate":"2026-03-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147751144","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}

{"title":"Augmented Lagrangian methods for handling terminal constraints in spacecraft trajectory optimization","authors":"Bryn N. Fanger,&nbsp;Ryan P. Russell","doi":"10.1007/s42064-025-0287-z","DOIUrl":"10.1007/s42064-025-0287-z","url":null,"abstract":"<div><p>Augmented Lagrangian methods are well-established for terminal constraint-handling but implementation varies significantly in practice. A new system-level algorithm is developed using combinations of first- versus second-order Lagrange multiplier (LM) updates, fixed versus variable LM step sizes, inner- versus outer-loop schemes for LM updates, penalty-only versus split versus concurrent LM and penalty multiplier updates, and exact versus inexact convergence criteria. Each component is combined to create twenty-two submethods that are applied to ten diverse spacecraft trajectory optimization problems with up to ten revolutions and both bang-bang and smooth thrusting profiles. Performance results indicate all submethods can be successful with varying degrees of tuning, but differ in ideal applications. Second-order inner-loop methods with step size management perform the best, but outer-loop methods with step size management and inexact convergence are more robust to tuning parameters.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"10 1","pages":"179 - 197"},"PeriodicalIF":6.5,"publicationDate":"2026-02-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-025-0287-z.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147341333","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}