Astrodynamics最新文献_第10页

Message from the Guest Editors of the Special Issue in Memory of Professor Shijie Xu 纪念许世杰教授特刊特邀编辑寄语

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-07-14 DOI: 10.1007/s42064-022-0141-5

Ming Xu, Yue Wang

引用次数: 0

A review of dynamic analysis on space solar power station 空间太阳能电站动态分析研究进展

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-07-13 DOI: 10.1007/s42064-022-0144-2

Weipeng Hu, Zichen Deng

{"title":"A review of dynamic analysis on space solar power station","authors":"Weipeng Hu, Zichen Deng","doi":"10.1007/s42064-022-0144-2","DOIUrl":"10.1007/s42064-022-0144-2","url":null,"abstract":"<div><p>The concept of a space solar power station (SSPS) was proposed in 1968 as a potential approach for solving the energy crisis. In the past 50 years, several structural concepts have been proposed, but none have been sent into orbit. One of the main challenges of the SSPS is dynamic behavior prediction, which can supply the necessary information for control strategy design. The ultra-large size of the SSPS causes difficulties in its dynamic analysis, such as the ultra-low vibration frequency and large flexibility. In this paper, four approaches for the numerical analysis of the dynamic problems associated with the SSPS are reviewed: the finite element, absolute nodal coordinate, floating frame formulation, and structure-preserving methods. Both the merits and shortcomings of the above four approaches are introduced when they are employed in dynamic problems associated with the SSPS. Synthesizing the merits of the aforementioned four approaches, we believe that embedding the structure-preserving method into finite element software may be an effective way to perform a numerical analysis of the dynamic problems associated with the SSPS.\u0000</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"7 2","pages":"115 - 130"},"PeriodicalIF":6.1,"publicationDate":"2022-07-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50023098","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: 6

Review of attitude consensus of multiple spacecraft 多航天器姿态一致性研究综述

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-07-09 DOI: 10.1007/s42064-022-0142-4

Ti Chen, Jinjun Shan, Hao Wen, Shidong Xu

引用次数: 4

Performance analysis of two RDSS positioning modes of BeiDou-3 system 北斗三号系统两种RDSS定位模式性能分析

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-07-02 DOI: 10.1007/s42064-022-0140-6

Dongxia Wang, Rui Guo, Nan Xing, Zhijun Liu, Tianqiao Zhang, Hui Ren, Xiaojie Li

{"title":"Performance analysis of two RDSS positioning modes of BeiDou-3 system","authors":"Dongxia Wang, Rui Guo, Nan Xing, Zhijun Liu, Tianqiao Zhang, Hui Ren, Xiaojie Li","doi":"10.1007/s42064-022-0140-6","DOIUrl":"10.1007/s42064-022-0140-6","url":null,"abstract":"<div><p>The BeiDou-3 global satellite navigation system (BDS-3) provides two radio determination satellite service (RDSS) positioning services for users, i.e., the traditional RDSS (TRDSS) positioning of the BeiDou-2 regional satellite navigation system, and the comprehensive RDSS (CRDSS) positioning, which integrates the RDSS and radio navigation satellite service. As published studies regarding the RDSS positioning service are few, we analyze and compare the performances of the two RDSS positioning modes. First, we systematically investigate the principles of the TRDSS and CRDSS positioning, and then analyze the evaluation methods in terms of their positioning accuracy, real time, and coverage range. Second, based on the BeiDou RDSS measured data, we evaluate the performances of the TRDSS and CRDSS positioning. Compared with TRDSS positioning, CRDSS positioning exhibits the following: 1) A significant increase in positioning accuracy, resulting in error improvement from 8 to 2 m and root mean square improvement from 3.13 to 0.85 m; in other words, the positioning error, constant deviation, and stability improve significantly. 2) The real time reduces slightly from 1.1 to 1.8 ns, which is within the acceptable range. 3) The coverage range expands from the areas of 62°E–145°E and 5°N–55°N to the areas of 50°E–170°E and 0°N–70°N, respectively. 4) CRDSS positioning is not restricted by the constraints of the digital elevation database or the user elevation information and can thus solve the occlusion problem effectively.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"6 3","pages":"317 - 327"},"PeriodicalIF":6.1,"publicationDate":"2022-07-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50003988","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: 2

Integrated visual navigation based on angles-only measurements for asteroid final landing phase 基于角度测量的小行星最终着陆阶段综合视觉导航

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-07-02 DOI: 10.1007/s42064-022-0143-3

Ronghai Hu, Xiangyu Huang, Chao Xu

{"title":"Integrated visual navigation based on angles-only measurements for asteroid final landing phase","authors":"Ronghai Hu, Xiangyu Huang, Chao Xu","doi":"10.1007/s42064-022-0143-3","DOIUrl":"10.1007/s42064-022-0143-3","url":null,"abstract":"<div><p>Visual navigation is imperative for successful asteroid exploration missions. In this study, an integrated visual navigation system was proposed based on angles-only measurements to robustly and accurately determine the pose of the lander during the final landing phase. The system used the lander’s global pose information provided by an orbiter, which was deployed in space in advance, and its relative motion information in adjacent images to jointly estimate its optimal state. First, the landmarks on the asteroid surface and markers on the lander were identified from the images acquired by the orbiter. Subsequently, an angles-only measurement model concerning the landmarks and markers was constructed to estimate the orbiter’s position and lander’s pose. Subsequently, a method based on the epipolar constraint was proposed to estimate the lander’s inter-frame motion. Then, the absolute pose and relative motion of the lander were fused using an extended Kalman filter. Additionally, the observability criterion and covariance of the state error were provided. Finally, synthetic image sequences were generated to validate the proposed navigation system, and numerical results demonstrated its advance in terms of robustness and accuracy.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"7 1","pages":"69 - 82"},"PeriodicalIF":6.1,"publicationDate":"2022-07-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50003981","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: 1

A recursive formulation for open-loop gyroelastic multibody dynamics 开环陀螺弹性多体动力学的递推公式

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-06-01 DOI: 10.1007/s42064-022-0137-1

Shiyuan Jia, Yinghong Jia

{"title":"A recursive formulation for open-loop gyroelastic multibody dynamics","authors":"Shiyuan Jia, Yinghong Jia","doi":"10.1007/s42064-022-0137-1","DOIUrl":"10.1007/s42064-022-0137-1","url":null,"abstract":"<div><p>In this paper, a general recursive formulation of equations of motion is presented for open-loop gyroelastic multibody systems. The gyroelastic multibody system is defined as a multibody system with gyroelastic bodies, whereas a gyroelastic body is composed of a flexible body with a cluster of double-gimbal variable-speed control moment gyroscopes (DGVs). First, the motion equations of a single gyroelastic body are derived using Kane’s method. The influence of DGVs on the static moments, modal momentum coefficients, moments of inertia, modal angular momentum coefficients, and modal mass matrix for a flexible body are considered. The interactions between the DGVs and the flexibilities of the structures are captured. The recursive kinematic relations for a multibody system with different connections are then obtained from a flexible–flexible connection using a transformation matrix. The different connections contain a flexible–flexible connection, which represents a flexible body connecting to another flexible body, flexible–rigid and rigid–rigid connections. The recursive gyroelastic multibody dynamics are obtained by analyzing the kinematics of a multibody system and the dynamics of a single gyroelastic body. Numerical simulations are presented to verify the accuracy and efficiency of the proposed approach by comparing it with a direct formulation based on Kane’s method.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"6 3","pages":"301 - 316"},"PeriodicalIF":6.1,"publicationDate":"2022-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"49999029","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

Analytic continuation extended Kalman filter framework for perturbed orbit estimation using a network of space-based observers with angles-only measurements 分析延拓扩展了卡尔曼滤波框架，用于仅测量角度的天基观测站网络摄动轨道估计

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-05-18 DOI: 10.1007/s42064-022-0138-0

Tahsinul Haque Tasif, James E. Hippelheuser, Tarek A. Elgohary

{"title":"Analytic continuation extended Kalman filter framework for perturbed orbit estimation using a network of space-based observers with angles-only measurements","authors":"Tahsinul Haque Tasif, James E. Hippelheuser, Tarek A. Elgohary","doi":"10.1007/s42064-022-0138-0","DOIUrl":"10.1007/s42064-022-0138-0","url":null,"abstract":"<div><p>This work presents a new method for space-based angles-only orbit estimation. The approach relies on the integration of a novel and highly accurate <i>Analytic Continuation</i> technique with a new measurement model for multiple observers for inertial orbit estimation. <i>Analytic Continuation</i> computes the perturbed orbit dynamics, as well as the perturbed state transition matrix (STM), in the inertial frame. A new measurement model is developed for simultaneous measurements using a constellation of low-cost observers with monocular cameras for angles-only measurements. <i>Analytic Continuation</i> and the new measurement model are integrated in an Extended Kalman Filter (EKF) framework, where the <i>Analytic Continuation</i> method is used to propagate the perturbed dynamics and compute the perturbed STM and error covariance, with the measurements obtained via the new measurement model. Two case studies comprising small and large constellations of observers are presented, along with cases of sparse measurements and a study of the computational efficiency of the proposed approach. The results show that the new approach is capable of producing highly accurate and computationally efficient perturbed orbit estimation results compared with classical EKF implementations.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"6 2","pages":"161 - 187"},"PeriodicalIF":6.1,"publicationDate":"2022-05-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50036428","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: 2

Message from the Guest Editors of the Special Issue on Astrodynamics for Space Situational Awareness 空间态势感知的天体动力学特刊客座编辑的信息

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-05-18 DOI: 10.1007/s42064-022-0139-z

Ya-Zhong Luo, Pierluigi Di Lizia, Zhen Yang

引用次数: 0

Analytical solution to logarithmic spiral trajectories with circumferential thrust and mission applications 具有周向推力的对数螺旋轨迹的解析解及其任务应用

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-05-18 DOI: 10.1007/s42064-022-0135-3

Marco Bassetto, Alessandro A. Quarta, Giovanni Mengali

{"title":"Analytical solution to logarithmic spiral trajectories with circumferential thrust and mission applications","authors":"Marco Bassetto, Alessandro A. Quarta, Giovanni Mengali","doi":"10.1007/s42064-022-0135-3","DOIUrl":"10.1007/s42064-022-0135-3","url":null,"abstract":"<div><p>This study made use of a shape-based method to analyze the orbital dynamics of a spacecraft subject to a continuous propulsive acceleration acting along the circumferential direction. Under the assumption of a logarithmic spiral trajectory, an exact solution to the equations of motion exists, which allows the spacecraft state variables and flight time to be expressed as a function of the angular coordinate. There is also a case characterized by specific initial conditions in which the time evolution of the state variables may be analytically determined. In this context, the presented solution is used to analyze circle-to-circle trajectories, where the combination of two impulsive maneuvers and a logarithmic spiral path are used to accomplish the transfer. The determined results are then applied to the achievement of the Earth—Mars and the Earth—Venus transfers using actual data from a recent thruster developed by NASA.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"6 4","pages":"413 - 427"},"PeriodicalIF":6.1,"publicationDate":"2022-05-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-022-0135-3.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50036331","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

Non-cooperative spacecraft proximity control considering target behavior uncertainty 考虑目标行为不确定性的航天器非合作接近控制

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-05-11 DOI: 10.1007/s42064-022-0133-5

Guanjie Sun, Mengqi Zhou, Xiuqiang Jiang

引用次数: 2