Astrodynamics最新文献

Trajectory design for awaiting comets on invariant manifolds with optimal control 最优控制不变流形上等待彗星的轨迹设计

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2025-08-29 DOI: 10.1007/s42064-024-0236-2

Soi Yamaguchi, Naoki Hiraiwa, Mai Bando, Shinji Hokamoto, Damennick B. Henry, Daniel J. Scheeres

{"title":"Trajectory design for awaiting comets on invariant manifolds with optimal control","authors":"Soi Yamaguchi, Naoki Hiraiwa, Mai Bando, Shinji Hokamoto, Damennick B. Henry, Daniel J. Scheeres","doi":"10.1007/s42064-024-0236-2","DOIUrl":"10.1007/s42064-024-0236-2","url":null,"abstract":"<div><p>Comet exploration missions represented by the Comet Interceptor mission have attracted our attention to unravel the origin of our solar system. However, it is difficult to know the details of orbital data about long period comets (LPCs) until their approach. Additionally, the amount of fuel consumption by the current intercept approach depends on the intersection points of cometary orbits with the ecliptic plane. To address these challenges, designing low-energy transfer trajectories suitable for the observation of LPCs is necessary. This paper introduces a novel approach by utilizing invariant manifold structures in the Sun-Earth circular restricted three-body problem for comet missions with multiple probes. As candidates for departure orbits, periodic orbits and quasi-periodic orbits are considered. Based on the optimal control theory, low-thrust trajectories to improve mission efficiency for enlarging the reachable domain of multiple probes are designed by leveraging invariant manifolds. The trajectories guided by invariant manifolds and optimal control theory facilitate formation flying, multi-point observations, and explorations of unknown comets by multiple probes.\u0000</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 4","pages":"565 - 581"},"PeriodicalIF":6.5,"publicationDate":"2025-08-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145011884","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

Thermal deformation analysis and shape control of a novel large-scale two-dimensional planar phased array antenna 新型大型二维平面相控阵天线的热变形分析与形状控制

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2025-08-27 DOI: 10.1007/s42064-024-0238-0

Chaochen Jin, Xiang Liu, Guoping Cai, Jun Sun, Dongfang Zhu

{"title":"Thermal deformation analysis and shape control of a novel large-scale two-dimensional planar phased array antenna","authors":"Chaochen Jin, Xiang Liu, Guoping Cai, Jun Sun, Dongfang Zhu","doi":"10.1007/s42064-024-0238-0","DOIUrl":"10.1007/s42064-024-0238-0","url":null,"abstract":"<div><p>The performance of space antennas is significantly affected by thermal deformation owing to the harsh thermal environment in space. This results in potential degradation in pointing accuracy and overall functionality. This study focused on the analysis and control of thermal deformation in large-scale two-dimensional planar phased array antennas. Employing the finite element method, we developed a comprehensive thermal and structural model of the antenna. This enabled us to simulate the steady-state temperature field and the associated thermal deformation at various orbital positions. To address this deformation issue, we propose an innovative shape-control approach that utilizes distributed cable actuators. The shape control challenge was reformulated into a layered optimization problem concerning actuator placement and force application. In the outer optimization layer, a discrete particle swarm optimization algorithm was used to determine the optimal locations for the actuators. In the inner optimization layer, quadratic programming was subsequently applied to calculate the optimal control forces for each actuator. We validated the proposed method by numerically simulating a novel large-scale two-dimensional planar phased array antenna. The results demonstrated the effectiveness of our method in mitigating thermal deformation and maintaining the structural integrity and shape accuracy of the antennas.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 4","pages":"583 - 604"},"PeriodicalIF":6.5,"publicationDate":"2025-08-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145011535","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

Neural networks-based solution of the two-body problem 基于神经网络的二体问题求解

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2025-08-26 DOI: 10.1007/s42064-024-0230-8

Zhuojun Hou, Qinbo Sun, Zhaohui Dang

{"title":"Neural networks-based solution of the two-body problem","authors":"Zhuojun Hou, Qinbo Sun, Zhaohui Dang","doi":"10.1007/s42064-024-0230-8","DOIUrl":"10.1007/s42064-024-0230-8","url":null,"abstract":"<div><p>This paper presents a novel machine learning approach designed to efficiently solve the classical two-body problem. The inherent structure of the two-body problem involves the integration of a system of second-order nonlinear ordinary differential equations. Conventional numerical integration techniques that rely on small computation steps result in a prolonged computational time. Moreover, calculus has limitations in resolving the two-body problem, inevitably converging towards an unresolved Kepler equation of a transcendental nature. To address this issue, we integrate the conventional analytical solution based on true anomaly with a deep neural network representation of the Kepler equation. This results in a highly accurate closed-form solution that is solely dependent on time, which is termed a learning-based solution to the two-body problem. To enhance the precision, a correction module based on Halley iteration is introduced, which substantially improves the final solution in terms of precision and computational cost. Compared to state-of-the-art methods such as the piecewise Padé approximation, Adomian decomposition method, and modified Mikkola’s method, our approach achieves a computational speedup of several thousand to tens of thousands, while maintaining accuracy in large-scale orbit propagation scenarios. Empirical validation under simulated conditions underscores its effectiveness and potential value for long-term orbit determination.\u0000</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 4","pages":"537 - 564"},"PeriodicalIF":6.5,"publicationDate":"2025-08-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145011775","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

Robust twistor-based spacecraft relative pose estimation using unscented Kalman filter 基于无气味卡尔曼滤波的航天器相对姿态鲁棒估计

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2025-08-26 DOI: 10.1007/s42064-024-0228-2

Mohammed Atallah, Mohamed Okasha, Ossama Abdelkhalik, Tarek N. Dief

{"title":"Robust twistor-based spacecraft relative pose estimation using unscented Kalman filter","authors":"Mohammed Atallah, Mohamed Okasha, Ossama Abdelkhalik, Tarek N. Dief","doi":"10.1007/s42064-024-0228-2","DOIUrl":"10.1007/s42064-024-0228-2","url":null,"abstract":"<div><p>This paper presents new methods for spacecraft relative pose estimation using the Unscented Kalman Filter (UKF), taking into account non-additive process and measurement noises. A twistor model is employed to represent the spacecraft’s relative 6-DOF motion of the chaser with respect to the target, expressed in the chaser body frame. The twistor model utilizes Modified Rodrigues Parameters (MRPs) to represent attitude with a minimal number of parameters, eliminating the need for the normalization constraint that exists in the quaternion-based model. Additionally, it incorporates both relative position and attitude in a single model, addressing kinematic coupling of states and simplifying the estimator design. Despite numerous existing pose estimation algorithms, many rely on the simplification of additive noise assumptions. This work enhances the robustness and improves the convergence of non-additive noise algorithms by deriving two methods to accurately approximate process and measurement noise covariance matrices for systems with non-additive noises. The first method utilizes the Stirling Interpolation Formula (SIF) to obtain equivalent process and measurement noise covariance matrices. The second method employs State Noise Compensation (SNC) to derive the equivalent process noise covariance matrix and uses SIF to compute the equivalent measurement noise covariance matrix. These methods are integrated into the UKF framework for estimating the relative pose of spacecraft in proximity operations, demonstrated through two scenarios: one with a cooperative target using Position Sensing Diodes (PSDs) and another with an uncooperative target using LiDAR for 3-D imaging. The effectiveness of these methods is validated against others in the literature through Monte Carlo simulations, showcasing their faster convergence and robust performance.\u0000</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 4","pages":"495 - 515"},"PeriodicalIF":6.5,"publicationDate":"2025-08-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145011774","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

Target marker deployment strategies for Hayabusa2 extended mission to fast rotator 1998 KY26 隼鸟2号扩展任务到快速旋转器1998 KY26的目标标记部署策略

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2025-08-23 DOI: 10.1007/s42064-024-0229-1

Anivid Pedros-Faura, Mirko Trisolini, Yuichi Tsuda, Daniel J. Scheeres, Shota Kikuchi, Jay W. McMahon

{"title":"Target marker deployment strategies for Hayabusa2 extended mission to fast rotator 1998 KY26","authors":"Anivid Pedros-Faura, Mirko Trisolini, Yuichi Tsuda, Daniel J. Scheeres, Shota Kikuchi, Jay W. McMahon","doi":"10.1007/s42064-024-0229-1","DOIUrl":"10.1007/s42064-024-0229-1","url":null,"abstract":"<div><p>The Hayabusa2 extended mission, named Hayabusa2# (SHARP: Small Hazardous Asteroid Reconnaissance Probe), is planned to rendezvous with the fast-rotating asteroid 1998 KY26 in 2031. Hayabusa2# will be the first ever mission to rendezvous with such a rapidly rotating small asteroid, posing significant challenges because of its distinctive dynamical environment. In this paper, we investigate potential target marker (TM) deployment strategies, for both landing and orbiting scenarios, to maximize science acquisition. In particular, we model the surface and orbital environments to identify feasible target market operations and present landing site selection strategies and candidate insertion orbits considering realistic deployment errors. The TM is one of the only two remaining deployable payloads, and therefore, can play a critical role during the extended mission phase. Our results show that surface operations can be extremely challenging whereas orbit operations could help us gain valuable information on the asteroid’s gravity field. Overall, this research contributes to the exploration and characterization of extremely small bodies specifically through the use of artificial objects, in this case the target marker.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 4","pages":"517 - 536"},"PeriodicalIF":6.5,"publicationDate":"2025-08-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-024-0229-1.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145011584","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

Combined trajectory and time-planning strategy for rendezvous missions using low-thrust transfer 低推力转移交会任务的轨道与时间联合规划策略

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2025-08-07 DOI: 10.1007/s42064-024-0222-8

Jia Guo, Zhaojun Pang, Zhonghua Du

{"title":"Combined trajectory and time-planning strategy for rendezvous missions using low-thrust transfer","authors":"Jia Guo, Zhaojun Pang, Zhonghua Du","doi":"10.1007/s42064-024-0222-8","DOIUrl":"10.1007/s42064-024-0222-8","url":null,"abstract":"<div><p>In this study, a combined trajectory and time-planning strategy is proposed to reduce the fuel consumption of low-thrust rendezvous missions. First, a transformation method was developed to adjust the independent variable such that results obtained using the shape-based algorithm that employs an inverse polynomial can be used as an initial guess for a pseudospectral method. Second, a planning strategy that combined low-thrust transfer trajectory optimization and boundary condition optimization was designed. This planning strategy was divided into outer and inner layers. The outer plan optimized waiting and transfer times and thus determined boundary conditions. The inner plan optimized the low-thrust transfer trajectory using the pseudospectral method. The inner plan was embedded in the outer plan. Numerical simulations show that the independent variable transformation method is feasible, and the combined use of the shape-based algorithm with the inverse polynomial and pseudospectral method ensures good convergence. The cost of rendezvous missions is significantly decreased using combined trajectory and time optimization.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 4","pages":"481 - 493"},"PeriodicalIF":6.5,"publicationDate":"2025-08-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145011689","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

Descent-trajectory planning of a multi-node flexible small celestial body lander in hazardous terrains 危险地形下多节点柔性小天体着陆器的下降轨迹规划

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2025-07-28 DOI: 10.1007/s42064-024-0244-2

Jingxuan Chai, Youmin Gong, Jie Mei, Guangfu Ma, Weiren Wu

{"title":"Descent-trajectory planning of a multi-node flexible small celestial body lander in hazardous terrains","authors":"Jingxuan Chai, Youmin Gong, Jie Mei, Guangfu Ma, Weiren Wu","doi":"10.1007/s42064-024-0244-2","DOIUrl":"10.1007/s42064-024-0244-2","url":null,"abstract":"<div><p>Traditional landers typically encounter difficulties achieving stable landings because of the weak gravity and complex terrain of small celestial bodies. A multi-node lander with flexible connections can improve the stability of a small celestial body landing. However, this also poses new challenges, particularly for landing guidance in hazardous terrain. To address this problem, an equivalent simplified dynamic model of a multi-node flexible lander is first constructed, and its flat output is determined. Subsequently, a trajectory-planning method combining the flow and vector fields is designed to avoid collision, and the parameters of the vector field are optimized online according to the dynamic and obstacle constraints during the descent process to obtain a more suitable trajectory. Finally, the effectiveness of the proposed trajectory-planning method is verified through comparative simulations of landing and obstacle avoidance from the hover point to the landing area. This study offers new prospects for upcoming small celestial body landing missions in complex terrains.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 4","pages":"605 - 619"},"PeriodicalIF":6.5,"publicationDate":"2025-07-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145011544","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 geometric approach to optimal motion planning for close-range rendezvous and synchronization 近距离交会与同步最优运动规划的几何方法

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2025-07-15 DOI: 10.1007/s42064-025-0273-5

Jun Yang Li, M. Reza Emami

引用次数: 0

Hazardous asteroid deflection based on “space billiard” mode: Mission analysis and trajectory design 基于“空间台球”模式的危险小行星偏转：任务分析与轨迹设计

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2025-07-14 DOI: 10.1007/s42064-024-0221-9

Yangxin Wang, Vsevolod Vladimirovich Koryanov, Alexey Gennadievich Toporkov

{"title":"Hazardous asteroid deflection based on “space billiard” mode: Mission analysis and trajectory design","authors":"Yangxin Wang, Vsevolod Vladimirovich Koryanov, Alexey Gennadievich Toporkov","doi":"10.1007/s42064-024-0221-9","DOIUrl":"10.1007/s42064-024-0221-9","url":null,"abstract":"<div><p>Defense against potentially hazardous asteroids is crucial to human civilization. An asteroid projectile can be redirected to intercept hazardous asteroids by employing gravity assist from the Earth or Moon, thereby effectively altering their trajectory. Such an asteroid defense mode is referred to as “space billiard.” Current investigations regarding mission planning and trajectory design for this mode are either incomplete or contain imperfect perspectives. This article proposes a comprehensive mission planning from spacecraft departure to the impact of a hazardous asteroid with an asteroid projectile. This involves selecting an asteroid projectile, determining the maneuver time, and optimizing the low-thrust trajectory. The particle swarm optimization algorithm for the Lambert problem is introduced to search for the maneuver time, and low-thrust optimization is performed to design the transfer trajectory of the spacecraft. A collision model based on NASA’s DART mission is used to analyze the feasibility of this approach. A classic example where this approach is adopted is for analyzing the hazardous asteroid Apophis. Based on this analysis, an asteroid projectile named 2015 VC2 is selected for simulation. The complete trajectories of the spacecraft and asteroid projectile are simulated, and the feasibility of the scheme is verified. This approach may be a feasible option for defending against hazardous asteroids.\u0000</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 4","pages":"465 - 479"},"PeriodicalIF":6.5,"publicationDate":"2025-07-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145011474","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

Fast trajectory replanning for cooperative vehicles using sequential convex programming 基于顺序凸规划的协同车辆快速轨迹重规划

IF 6.5 1区物理与天体物理

Astrodynamics Pub Date : 2025-07-12 DOI: 10.1007/s42064-024-0208-6

Peng Zhang, Lin Cheng, Shengping Gong

{"title":"Fast trajectory replanning for cooperative vehicles using sequential convex programming","authors":"Peng Zhang, Lin Cheng, Shengping Gong","doi":"10.1007/s42064-024-0208-6","DOIUrl":"10.1007/s42064-024-0208-6","url":null,"abstract":"<div><p>With the rapid changes of the flight environment and situation, there will be various unexpected situations while multiple missiles are performing the missions. To fast cope with the various situations in mission executions, the conventional sequential convex programming algorithm and the parallel-based sequential convex programming algorithm for multiple missiles fast trajectory replanning are proposed in this paper. The originally non-convex trajectory optimization problem is reformulated into a series of convex optimization subproblems based on the sequential convex programming method. The conventional sequential convex programming algorithm is developed through linearization, successive convexification, and relaxation techniques to solve the convex optimization subproblems iteratively. However, multiple missiles are related through various cooperative constraints. When the trajectory optimization of multiple missiles is formulated as an optimal control problem to solve, the complexity of the problem will increase dramatically as the number of missiles increases. To alleviate the coupled effect caused by multiple aerodynamically controlled missiles, the parallel-based sequential convex programming algorithm is proposed to solve the trajectory optimization problem for multiple missiles in parallel, reducing the complexity of the trajectory optimization problem and significantly shortening the computation time. Numerical simulations are provided to verify the convergence and effectiveness of the conventional sequential convex programming algorithm and the parallel-based sequential convex programming algorithm to cope with the trajectory optimization problem with various constraints. Furthermore, the optimality and the real-time performance of the proposed algorithms are discussed in comparative simulation examples.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"9 3","pages":"369 - 388"},"PeriodicalIF":6.5,"publicationDate":"2025-07-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145164200","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