Astrodynamics最新文献

A goal-oriented guidance approach for binary asteroids exploration 一种面向目标的双小行星探测制导方法

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2025-05-16 DOI: 10.1007/s42064-024-0237-1

Antonio Rizza, Carmine Giordano, Francesco Topputo

{"title":"A goal-oriented guidance approach for binary asteroids exploration","authors":"Antonio Rizza, Carmine Giordano, Francesco Topputo","doi":"10.1007/s42064-024-0237-1","DOIUrl":"10.1007/s42064-024-0237-1","url":null,"abstract":"<div><p>Operations in proximity of minor bodies demands high levels of autonomy to achieve cost-effective safe and reliable solutions. Autonomous trajectory and operations planning capability plays a pivotal role in this. A goal-oriented guidance strategy for on-board implementation is presented in this paper to achieve high level mission objectives with impulsive control capability. The methodology is based on abstract reachability analysis performed on the control domain combining model predictive control theory with artificial potential fields algorithms. The formulation of the optimization problem in a general and flexible way allows to target different goals while being compliant with an arbitrary number of mission constraints. In particular, two main contributions to the field are proposed in this work: a way of embedding non-uniform observation constraints in the formulation to deal with challenging illumination conditions, and the inclusion of specific operational constraints to be compliant both with ground operations and on-board replanning. The methodology is applied to the Milani mission, one of the two Hera’s CubeSats, targeting a global coverage of the main attractor, Didymos, and detailed observations of specific features on the secondary asteroid, Dimorphos. The authors, being involved in the mission analysis, image processing, and GNC design of the platform, believe that this methodology also represents a viable tool for efficiently generating flight dynamics references during operations. Different metrics are investigated to achieve mission objectives leading to four application scenarios that are discussed in this work. Results are compared in terms of computational cost, convergence properties and efficiency. These results represent a step forward in enabling autonomous guidance capability for CubeSats proximity operations.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 2","pages":"289 - 302"},"PeriodicalIF":2.7,"publicationDate":"2025-05-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144073780","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

Design of halo orbit constellation for lunar global positioning and communication services 面向月球全球定位与通信服务的光环轨道星座设计

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2025-05-07 DOI: 10.1007/s42064-024-0220-x

Mariano Conti, Christian Circi

{"title":"Design of halo orbit constellation for lunar global positioning and communication services","authors":"Mariano Conti, Christian Circi","doi":"10.1007/s42064-024-0220-x","DOIUrl":"10.1007/s42064-024-0220-x","url":null,"abstract":"<div><p>A lunar global positioning–navigation–timing (PNT) and communication system can greatly support the exploration and exploitation of the Moon. In this study, the application of the stable orbits of the L<sub>1</sub> and L<sub>2</sub> halo families and the unstable orbits of L<sub>3</sub> in the Earth–Moon system is analyzed, and a design is proposed. L<sub>3</sub> halo orbits are considered for a continuous line-of-sight satellite infrastructure for the Earth–Moon communication, thereby providing an opportunity for ground stations on the Earth to participate in lunar missions even if they do not directly see the Moon. In this study, a constellation of 26 satellites distributed over a lunar segment, made of four halo orbits of L<sub>1</sub> and L<sub>2</sub>, and a terrestrial segment, made of two halo orbits of L<sub>3</sub>, is designed; this constellation facilitates global and continuative Earth–Moon communication and provides accurate and continuous lunar PNT service. According to a station-keeping analysis in the framework of the elliptical restricted three-body problem, the maintenance cost for approximately 60 d was 0.76 m/s for the lunar segment and 0.02 m/s for the terrestrial segment.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 2","pages":"231 - 245"},"PeriodicalIF":2.7,"publicationDate":"2025-05-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-024-0220-x.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144073576","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

Delta-k approach for space surveillance multireceiver radars 用于空间监视多接收机雷达的Delta-k方法

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2025-05-07 DOI: 10.1007/s42064-024-0217-5

Marco Felice Montaruli, Pierluigi Di Lizia, Stefano Tebaldini, Germano Bianchi

{"title":"Delta-k approach for space surveillance multireceiver radars","authors":"Marco Felice Montaruli, Pierluigi Di Lizia, Stefano Tebaldini, Germano Bianchi","doi":"10.1007/s42064-024-0217-5","DOIUrl":"10.1007/s42064-024-0217-5","url":null,"abstract":"<div><p>The increasing population of resident space objects is currently fostering many space surveillance initiatives. In this framework, on-ground multireceiver radars allow to reconstruct the target angular track, but the array configuration may cause the presence of multiple solutions and, if no pass prediction is available, the ambiguity cannot be solved a-priori. This work proposes an evolution of the Music Approach for Track Estimate and Refinement (MATER) algorithm. Given two different signals reflected by the same target, at each observation epoch their Direction Of Arrival (DOA) is estimated from the signal Covariance Matrix (CM) through the MUltiple SIgnal Classification (MUSIC) algorithm. Then, the possible ambiguous estimations are solved through the <i>delta</i>-k technique: the correct DOA is considered as the one featuring the smallest angular deviation comparing the two CM results. This process is repeated for all the epochs, and the DOAs are clustered according to the RANdom SAmple Consensus (RANSAC) algorithm. Finally, the most populated cluster is considered as the correct one, and the angular track is computed through a time regression of the two angular coordinates. The evolution of MATER algorithm is tested through numerical simulations. The algorithm converges to the correct solution in 100% of the cases, with an angular accuracy in the order of 1–10 mdeg.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 2","pages":"217 - 229"},"PeriodicalIF":2.7,"publicationDate":"2025-05-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-024-0217-5.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144073575","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

Collision avoidance maneuver optimization during low-thrust propelled trajectories 低推力推进轨迹下避碰机动优化

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2025-05-07 DOI: 10.1007/s42064-024-0227-3

Zeno Pavanello, Laura Pirovano, Roberto Armellin, Andrea De Vittori, Pierluigi Di Lizia

{"title":"Collision avoidance maneuver optimization during low-thrust propelled trajectories","authors":"Zeno Pavanello, Laura Pirovano, Roberto Armellin, Andrea De Vittori, Pierluigi Di Lizia","doi":"10.1007/s42064-024-0227-3","DOIUrl":"10.1007/s42064-024-0227-3","url":null,"abstract":"<div><p>Conjunctions between spacecraft are increasingly common across orbital regimes, demanding reliable and efficient collision avoidance (COLA) strategies. The typical solution to the COLA problem is to compute a maneuver that reduces the collision risk while minimizing fuel expenditure. If the spacecraft is in a continuously propelled phase, this approach must be modified since the thrust profile is determined <i>a priori</i>, aiming to reach a final orbit. This work proposes using convex optimization to solve the short-term encounter COLA problem in such conditions. The optimization problem is two-fold: (i) the collision risk must be reduced below a certain threshold; (ii) after the conjunction, the spacecraft must be rerouted into the nominal trajectory. By casting the problem as a sequential convex program, the original nonlinear optimal control problem is solved iteratively, recovering an optimal solution. Within the second-order cone program framework, three strategies are proposed to address the problem: (i) determining the optimal switch-off time to avoid the collision while minimizing deviation from the nominal trajectory; computing a new thrust profile, deviating as little as possible from the original one in terms of (ii) vector or (iii) angular difference. The three strategies are tested on practical operational scenarios, using the nominal thrust profile from a low-thrust geostationary transfer orbit and conjunction details from a conjunction data message.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 2","pages":"247 - 271"},"PeriodicalIF":2.7,"publicationDate":"2025-05-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-024-0227-3.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144073577","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

Mechanism analysis of the DRO low-energy transfer problem: An energy perspective DRO低能量转移问题的机理分析：一个能量视角

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2025-05-07 DOI: 10.1007/s42064-024-0215-7

Ming Wang, Chen Zhang, Hao Zhang

{"title":"Mechanism analysis of the DRO low-energy transfer problem: An energy perspective","authors":"Ming Wang, Chen Zhang, Hao Zhang","doi":"10.1007/s42064-024-0215-7","DOIUrl":"10.1007/s42064-024-0215-7","url":null,"abstract":"<div><p>The 2:1 resonant distant retrograde orbit (DRO), known for its long-term stability and global accessibility, holds strategic significance in current Earth-Moon space mission explorations. This paper conducts a comprehensive analysis of the problem of low-energy transferring into 2:1 DRO using the weak stability boundary (WSB) and lunar gravity assist (LGA) in the planar bi-circular restricted four-body problem (BCR4BP). The transfer process is categorized into three phases: the Earth-Moon transfer, Sun-Earth weak stability boundary transfer, and DRO low-energy capture. Addressing key questions, our study investigates: (1) Under what LGA conditions can the spacecraft reach the approximate area where the WSB region is situated? (2) How do trajectories, upon reaching the region where the WSB is located, return to the vicinity of 2:1 DRO, potentially facilitating low-energy DRO insertion? Our study involved a comprehensive analysis of the spacecraft’s changes in Earth-Moon mechanical energy and Jacobi energy during the entire transfer process. This analysis yielded the energy and geometric conditions necessary for potential low-energy DRO insertion, effectively filtering out numerous impractical candidate trajectories and enhancing computational effciency. In this paper, the geometric condition is referred to as the low-energy transfer gateway (LETG). Using the LEGT as the stitching interface, a significant number of feasible solutions were obtained effectively for bi-impulse DRO transfer trajectories through differential correction, some of which were previously undiscovered.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 2","pages":"165 - 193"},"PeriodicalIF":2.7,"publicationDate":"2025-05-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144073573","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

Transcription and optimization of an interplanetary trajectory through quantum annealing 通过量子退火的行星际轨迹的转录和优化

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2025-05-07 DOI: 10.1007/s42064-024-0216-6

Federico De Grossi, Andrea Carbone, Dario Spiller, Daniele Ottaviani, Riccardo Mengoni, Christian Circi

{"title":"Transcription and optimization of an interplanetary trajectory through quantum annealing","authors":"Federico De Grossi, Andrea Carbone, Dario Spiller, Daniele Ottaviani, Riccardo Mengoni, Christian Circi","doi":"10.1007/s42064-024-0216-6","DOIUrl":"10.1007/s42064-024-0216-6","url":null,"abstract":"<div><p>This study employed a quantum-annealing framework to solve spacecraft trajectory optimization problems. Quantum annealing belongs to the field of quantum computing and is a promising technique for tackling hard binary optimization problems by employing quantum annealers. To address the optimal control of a trajectory using quantum annealing, a transcription procedure was introduced to express the problem in the binary optimization form required. The proposed procedure leverages the pseudospectral method to discretize the trajectory and represents the dynamical constraints as algebraic equality constraints at specific nodes. Subsequently, both a linearization procedure and binary representation strategy for the real-valued variables of the problem were presented, leading to the quadratic binary unconstrained optimization form. The quantum-annealing-based method was tested in the context of an interplanetary low-thrust transfer from the Earth to Mars. First, we discussed which instances of the problem, especially in terms of their dimensions, are implementable on currently available quantum annealers; then, a solution was sought by employing annealers from D-Wave systems. Solutions from hybrid solvers that combine classical and quantum resources, and fully quantum solvers were explored. The results demonstrate the validity of the transcription approach, demonstrate the ability of the <i>hybrid</i> solver to tackle the case-study problem, and highlight the promising features and current limitations of practical trajectory optimization with quantum annealing.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 2","pages":"195 - 215"},"PeriodicalIF":2.7,"publicationDate":"2025-05-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-024-0216-6.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144073574","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

Model predictive control for formation flying based on D’Amico relative orbital elements 基于D’amico相对轨道元的编队飞行模型预测控制

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2025-05-05 DOI: 10.1007/s42064-024-0214-8

Tyson K. Smith, John Akagi, Greg Droge

{"title":"Model predictive control for formation flying based on D’Amico relative orbital elements","authors":"Tyson K. Smith, John Akagi, Greg Droge","doi":"10.1007/s42064-024-0214-8","DOIUrl":"10.1007/s42064-024-0214-8","url":null,"abstract":"<div><p>The desire to fly small spacecraft close together has been a topic of increasing interest over the past several years. This paper presents the development and analysis of a model predictive control based framework that is used with the D’Amico relative orbital elements (ROEs) to maintain the desired trajectories of a cluster of spacecraft while also allowing freedom to maneuver within some allowable bounds. Switching surfaces based on the ROE constraints contain the full state of the system, allowing for fuel reduction over other approaches that use the Hill—Clohessy—Wiltshire equations. The formation and boundary constraints are designed such that no two agents have overlapping regions, allowing the vehicles to maintain safety of fl ight without continually maintaining the trajectories of other agents. This framework allows for a scalable method that can support clusters of satellites to safely achieve mission objectives while minimizing fuel usage. This paper provides simulated results of the framework for a three spacecraft formation that demonstrates a 67% fuel reduction when compared to previous approaches.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 2","pages":"143 - 163"},"PeriodicalIF":2.7,"publicationDate":"2025-05-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144074044","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

Addressing the ill-conditioned problem in initial orbit determination via the Gooding algorithm 利用Gooding算法解决初始轨道确定中的病态问题

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2025-04-12 DOI: 10.1007/s42064-024-0251-3

Zhengyuan Zhang, Jizhang Sang, Zhenwei Li

{"title":"Addressing the ill-conditioned problem in initial orbit determination via the Gooding algorithm","authors":"Zhengyuan Zhang, Jizhang Sang, Zhenwei Li","doi":"10.1007/s42064-024-0251-3","DOIUrl":"10.1007/s42064-024-0251-3","url":null,"abstract":"<div><p>The accuracy of angles-only initial orbit determination (IOD) is significantly compromised when only a short-arc orbit is observed. The ill-conditioned problem in matrices due to weak geometric constraints caused by short arcs and observation errors typically causes significant errors in the estimated ranges and thus unsatisfactory IOD. This paper presents a critical analysis of the ill-conditioned problem using the Gooding algorithm and proposes several techniques to improve it. On the basis of multiple observations, a least-squares method is proposed to solve the ranges at the first and last epochs. For the short-arc case, the ridge estimation technique is applied to mitigate the ill-conditioned problem. To determine whether an orbit is eccentric, a procedure to assess orbit eccentricity is developed via the range-search method, which aims to provide reasonably accurate initial ranges to the Gooding algorithm. Finally, an eccentricity-constraint technique for the Gooding algorithm is proposed for cases where the orbit is determined to be nearly circular. The performances of these techniques on space-based simulation data are assessed, and an improved Gooding algorithm (I-Gooding) suitable for various observation conditions is proposed. The I-Gooding algorithm is subsequently applied to process actual ground-based observations. The results show that its accuracy in estimating the semimajor axis is 47% higher than that afforded by the standard Gooding algorithm.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 2","pages":"303 - 320"},"PeriodicalIF":2.7,"publicationDate":"2025-04-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144073582","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

Hybrid electrostatic ion beam shepherd schemes for active space debris removal from GEO to disposal orbit 从地球同步轨道到处置轨道主动空间碎片清除的混合静电离子束引导方案

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2025-04-12 DOI: 10.1007/s42064-024-0235-3

Alexander Ledkov, Vladimir Aslanov

{"title":"Hybrid electrostatic ion beam shepherd schemes for active space debris removal from GEO to disposal orbit","authors":"Alexander Ledkov, Vladimir Aslanov","doi":"10.1007/s42064-024-0235-3","DOIUrl":"10.1007/s42064-024-0235-3","url":null,"abstract":"<div><p>The removal of large space debris from a geostationary orbit to a disposal orbit via an ion beam shepherd spacecraft was considered in this study, with attention given to the electrostatic effect. The generation of an ion force, which provides contactless thrust, occurs because of the transfer of momentum from the ions of the engine plume of the spacecraft to the space debris. This process is accompanied by the transfer of a positive charge to the space debris. As a result, electrostatic interactions occur between the spacecraft and space debris. The goals of this study were to assess the influence of this effect on the dynamics of space debris during contactless ion beam-assisted removal and to develop hybrid contactless transportation schemes based on the use of an ion beam and electrostatic interactions. A mathematical model describing the motion of space debris and spacecraft under the influence of ionic and electrostatic forces and torques was developed. The concepts of electrostatic ion beam shepherd, electrostatic tractor with ion beam, and charged ion beam shepherd were proposed and compared. The results of numerical simulations revealed that the electrostatic ion beam shepherd scheme is preferable from the perspective of minimizing fuel costs when solving the problem of removing space debris from a geostationary orbit. A control law for the spacecraft charge needed for space-debris detumbling during ion-beam transportation is proposed. A numerical simulation of space debris removal was performed via a hybrid scheme.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 2","pages":"273 - 288"},"PeriodicalIF":2.7,"publicationDate":"2025-04-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144073583","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

GTOC12: Methods and results from the National University of Defense Technology GTOC12：方法和结果来自国防科技大学

IF 2.7 1区物理与天体物理

Astrodynamics Pub Date : 2025-03-04 DOI: 10.1007/s42064-024-0247-z

Yu Zhang, Yuehe Zhu, Jiacheng Zhang, Hanwei Wang, Ke Jin, Lifeng Fu

{"title":"GTOC12: Methods and results from the National University of Defense Technology","authors":"Yu Zhang, Yuehe Zhu, Jiacheng Zhang, Hanwei Wang, Ke Jin, Lifeng Fu","doi":"10.1007/s42064-024-0247-z","DOIUrl":"10.1007/s42064-024-0247-z","url":null,"abstract":"<div><p>This paper presents the solutions and results of the 12th edition of the Global Trajectory Optimization Competition (GTOC12) of the National University of Defense and Technology. To address the complex interstellar mining problem proposed by GTOC12, our solution is divided into two stages. The first stage focuses on preliminary work, including the target selection, the establishment of departure and return databases, and the development of methods to estimate transfer costs, with the aim of enhancing planning efficiency during the global planning phase. The second stage involves trajectory optimization for multiple mining ships, including single-mining-ship trajectory optimization and a multiship iterative process. For single-mining-ship trajectory optimization, the method involves three steps: first, employ a heuristic method for planning the first rendezvous sequences; second, utilize an ant colony optimization (ACO) algorithm for planning the second rendezvous sequences; and third, apply a differential evolution (DE) algorithm alongside an indirect method to refine rendezvous times and low-thrust trajectories. Through the implementation of a multiship iterative strategy, the team accomplished trajectory optimization for multiple mining ships that met the constraints. The final score submitted by the team was 15,160.946, which achieved the sixth place in the competition.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 1","pages":"129 - 141"},"PeriodicalIF":2.7,"publicationDate":"2025-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-024-0247-z.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143533230","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