Astrodynamics最新文献_第9页

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":null,"pages":null},"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":null,"pages":null},"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":null,"pages":null},"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":null,"pages":null},"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

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

Geophysical and orbital environments of asteroid 469219 2016 HO3 小行星469219 2016 HO3的地球物理和轨道环境

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-05-04 DOI: 10.1007/s42064-022-0131-7

Xiangyu Li, Daniel J. Scheeres, Dong Qiao, Zixuan Liu

{"title":"Geophysical and orbital environments of asteroid 469219 2016 HO3","authors":"Xiangyu Li, Daniel J. Scheeres, Dong Qiao, Zixuan Liu","doi":"10.1007/s42064-022-0131-7","DOIUrl":"10.1007/s42064-022-0131-7","url":null,"abstract":"<div><p>Asteroid 469219 Kamo’oalewa, also named 2016 HO3, is a small-size fast-rotating near-Earth asteroid, which is a potential target for future explorations. Owing to its weak gravity and fast spin rate, the dynamics on the surface or in the vicinity of 2016 HO3 are significantly different from those of planets or other small bodies explored in previous missions. In this study, the geophysical and orbital environments of 2016 HO3 were investigated to facilitate a potential mission design. First, the geometric and geopotential topographies of 2016 HO3 were examined using different shape models. The lift-off and escape conditions on its fast-rotating surface were investigated. Then, the periodic orbits around 2016 HO3 were studied in the asteroid-fixed frame and the Sun—asteroid frame considering the solar radiation pressure. The stable regions of the terminator orbits were discussed using different parameters. Finally, the influence of the nonspherical shape on the terminator orbits was examined. The precise terminator orbits around a real shape model of 2016 HO3 were obtained and verified in the high-fidelity model. This study shows that the polar region of 2016 HO3 is the primary region for landing or sampling, and the terminator orbits are well suited for global mapping and measurements of 2016 HO3. The analysis and methods can also serve as references for the exploration of other small fast-rotating bodies.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":null,"pages":null},"PeriodicalIF":6.1,"publicationDate":"2022-05-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50008630","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: 3

Rapid accessibility evaluation for ballistic lunar capture via manifolds: A Gaussian process regression application 通过流形进行月球弹道捕获的快速可达性评估：高斯过程回归应用

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-04-19 DOI: 10.1007/s42064-021-0130-0

Sandeep K. Singh, John L. Junkins, Manoranjan Majji, Ehsan Taheri

{"title":"Rapid accessibility evaluation for ballistic lunar capture via manifolds: A Gaussian process regression application","authors":"Sandeep K. Singh, John L. Junkins, Manoranjan Majji, Ehsan Taheri","doi":"10.1007/s42064-021-0130-0","DOIUrl":"10.1007/s42064-021-0130-0","url":null,"abstract":"<div><p>In this study, a supervised machine learning approach called Gaussian process regression (GPR) was applied to approximate optimal bi-impulse rendezvous maneuvers in the cis-lunar space. We demonstrate the use of the GPR approximation of the optimal bi-impulse transfer to patch points associated with various invariant manifolds in the cis-lunar space. The proposed method advances preliminary mission design operations by avoiding the computational costs associated with repeated solutions of the optimal bi-impulsive Lambert transfer because the learned map is computationally efficient. This approach promises to be useful for aiding in preliminary mission design. The use of invariant manifolds as part of the transfer trajectory design offers unique features for reducing propellant consumption while facilitating the solution of trajectory optimization problems. Long ballistic capture coasts are also very attractive for mission guidance, navigation, and control robustness. A multi-input single-output GPR model is presented to represent the fuel costs (in terms of the Δ<i>V</i> magnitude) associated with the class of orbital transfers of interest efficiently. The developed model is also proven to provide efficient approximations. The multi-resolution use of local GPRs over smaller sub-domains and their use for constructing a global GPR model are also demonstrated. One of the unique features of GPRs is that they provide an estimate of the quality of approximations in the form of covariance, which is proven to provide statistical consistency with the optimal trajectories generated through the approximation process. The numerical results demonstrate our basis for optimism for the utility 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":null,"pages":null},"PeriodicalIF":6.1,"publicationDate":"2022-04-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50081630","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

Real-time space object tracklet extraction from telescope survey images with machine learning 基于机器学习的望远镜巡天图像实时空间目标轨迹提取

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-04-13 DOI: 10.1007/s42064-022-0134-4

Andrea De Vittori, Riccardo Cipollone, Pierluigi Di Lizia, Mauro Massari

{"title":"Real-time space object tracklet extraction from telescope survey images with machine learning","authors":"Andrea De Vittori, Riccardo Cipollone, Pierluigi Di Lizia, Mauro Massari","doi":"10.1007/s42064-022-0134-4","DOIUrl":"10.1007/s42064-022-0134-4","url":null,"abstract":"<div><p>In this study, a novel approach based on the U-Net deep neural network for image segmentation is leveraged for real-time extraction of tracklets from optical acquisitions. As in all machine learning (ML) applications, a series of steps is required for a working pipeline: dataset creation, preprocessing, training, testing, and post-processing to refine the trained network output. Online websites usually lack ready-to-use datasets; thus, an in-house application artificially generates 360 labeled images. Particularly, this software tool produces synthetic night-sky shots of transiting objects over a specified location and the corresponding labels: dual-tone pictures with black backgrounds and white tracklets. Second, both images and labels are downscaled in resolution and normalized to accelerate the training phase. To assess the network performance, a set of both synthetic and real images was inputted. After the preprocessing phase, real images were fine-tuned for vignette reduction and background brightness uniformity. Additionally, they are down-converted to eight bits. Once the network outputs labels, post-processing identifies the centroid right ascension and declination of the object. The average processing time per real image is less than 1.2 s; bright tracklets are easily detected with a mean centroid angular error of 0.25 deg in 75% of test cases with a 2 deg field-of-view telescope. These results prove that an ML-based method can be considered a valid choice when dealing with trail reconstruction, leading to acceptable accuracy for a fast image processing pipeline.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":null,"pages":null},"PeriodicalIF":6.1,"publicationDate":"2022-04-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-022-0134-4.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50022142","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: 7