Astrodynamics最新文献_第7页

Optimal interplanetary trajectories for Sun-facing ideal diffractive sails 面向太阳的理想衍射帆的最佳行星际轨迹

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-06-16 DOI: 10.1007/s42064-023-0158-4

Alessandro A. Quarta, Giovanni Mengali, Marco Bassetto, Lorenzo Niccolai

{"title":"Optimal interplanetary trajectories for Sun-facing ideal diffractive sails","authors":"Alessandro A. Quarta, Giovanni Mengali, Marco Bassetto, Lorenzo Niccolai","doi":"10.1007/s42064-023-0158-4","DOIUrl":"10.1007/s42064-023-0158-4","url":null,"abstract":"<div><p>A diffractive sail is a solar sail whose exposed surface is covered by an advanced diffractive metamaterial film with engineered optical properties. This study examines the optimal performance of a diffractive solar sail with a Sun-facing attitude in a typical orbit-to-orbit heliocentric transfer. A Sun-facing attitude, which can be passively maintained through the suitable design of the sail shape, is obtained when the sail nominal plane is perpendicular to the Sun–spacecraft line. Unlike an ideal reflective sail, a Sun-facing diffractive sail generates a large transverse thrust component that can be effectively exploited to change the orbital angular momentum. Using a recent thrust model, this study determines the optimal control law of a Sun-facing ideal diffractive sail and simulates the minimum transfer times for a set of interplanetary mission scenarios. It also quantifies the performance difference between Sun-facing diffractive sail and reflective sail. A case study presents the results of a potential mission to the asteroid 16 Psyche.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"7 3","pages":"285 - 299"},"PeriodicalIF":6.1,"publicationDate":"2023-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-023-0158-4.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50031769","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: 3

Orbital radius keeping of floating partial space elevator in cargo transposition 浮动部分空间升降机在货物换位中的轨道半径保持

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-06-16 DOI: 10.1007/s42064-022-0156-y

Gefei Shi, Zheng H. Zhu

引用次数: 0

Attitude maneuvers avoiding forbidden directions 姿态机动避开禁止的方向

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-06-16 DOI: 10.1007/s42064-023-0163-7

David Ailabouni, Andreas Meister, Karlheinz Spindler

{"title":"Attitude maneuvers avoiding forbidden directions","authors":"David Ailabouni, Andreas Meister, Karlheinz Spindler","doi":"10.1007/s42064-023-0163-7","DOIUrl":"10.1007/s42064-023-0163-7","url":null,"abstract":"<div><p>Many space missions require the execution of large-angle attitude slews during which stringent pointing constraints must be satisfied. For example, the pointing direction of a space telescope must be kept away from directions to bright objects, maintaining a prescribed safety margin. In this paper we propose an open-loop attitude control algorithm which determines a rest-to-rest maneuver between prescribed attitudes while ensuring that any of an arbitrary number of body-fixed directions of light-sensitive instruments stays clear of any of an arbitrary number of space-fixed directions. The approach is based on an application of a version of Pontryagin’s Maximum Principle tailor-made for optimal control problems on Lie groups, and the pointing constraints are ensured by a judicious choice of the cost functional. The existence of up to three first integrals of the resulting system equations is established, depending on the number of light-sensitive and forbidden directions. These first integrals can be exploited in the numerical implementation of the attitude control algorithm, as is shown in the case of one light-sensitive and several forbidden directions. The results of the test cases presented confirm the applicability of the proposed algorithm.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"7 3","pages":"351 - 362"},"PeriodicalIF":6.1,"publicationDate":"2023-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-023-0163-7.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50031770","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

Midcourse correction of Earth-Moon distant retrograde orbit transfer trajectories based on high-order state transition tensors 基于高阶态跃迁张量的地月远逆行轨道转移轨迹中途修正

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-06-15 DOI: 10.1007/s42064-023-0162-8

Yongchen Yin, Ming Wang, Yu Shi, Hao Zhang

{"title":"Midcourse correction of Earth-Moon distant retrograde orbit transfer trajectories based on high-order state transition tensors","authors":"Yongchen Yin, Ming Wang, Yu Shi, Hao Zhang","doi":"10.1007/s42064-023-0162-8","DOIUrl":"10.1007/s42064-023-0162-8","url":null,"abstract":"<div><p>Midcourse correction design is key to space transfers in the cislunar space. Autonomous guidance has garnered significant attention for its promise to decrease the dependence on ground control systems. This study addresses the problem of midcourse corrections for Earth-Moon transfer orbits based on high-order state transition tensors (STTs). The scenarios considered are direct Earth-Moon transfers and low-energy transfers to lunar distant retrograde orbits (DROs), where the latter involve weak stability boundary (WSB) and lunar gravity assist (LGA) techniques. Semi-analytical formulas are provided for computing the trajectory correction maneuvers (TCMs) using high-order STTs derived using the differential algebraic method. Monte Carlo simulations are performed to evaluate the effectiveness of the proposed approach. Compared with existing explicit guidance algorithms, the STT-based approach is much cheaper computationally and features fewer final position errors. These results are promising for fast and efficient orbital autonomous correction guidance approaches in the cislunar space.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"7 3","pages":"335 - 349"},"PeriodicalIF":6.1,"publicationDate":"2023-06-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-023-0162-8.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50028907","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

Reconstructing the cruise-phase trajectory of deep-space probes in a general relativistic framework: An application to the Cassini gravitational wave experiment 广义相对论框架下深空探测器巡航相位轨迹重构:在卡西尼号引力波实验中的应用

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-04-15 DOI: 10.1007/s42064-023-0160-x

Joseph O’Leary, Jean-Pierre Barriot

{"title":"Reconstructing the cruise-phase trajectory of deep-space probes in a general relativistic framework: An application to the Cassini gravitational wave experiment","authors":"Joseph O’Leary, Jean-Pierre Barriot","doi":"10.1007/s42064-023-0160-x","DOIUrl":"10.1007/s42064-023-0160-x","url":null,"abstract":"<div><p>Einstein’s theory of general relativity is playing an increasingly important role in fields such as interplanetary navigation, astrometry, and metrology. Modern spacecraft and interplanetary probe prediction and estimation platforms employ a perturbed Newtonian framework, supplemented with the Einstein-Infeld-Hoffmann <i>n</i>-body equations of motion. While time in Newtonian mechanics is formally universal, the accuracy of modern radiometric tracking systems necessitate linear corrections via increasingly complex and error-prone post-Newtonian techniques—to account for light deflection due to the solar system bodies. With flagship projects such as the ESA/JAXA BepiColombo mission now operating at unprecedented levels of accuracy, we believe the standard corrected Newtonian paradigm is approaching its limits in terms of complexity. In this paper, we employ a novel prototype software, General Relativistic Accelerometer-based Propagation Environment, to reconstruct the Cassini cruise-phase trajectory during its first gravitational wave experiment in a fully relativistic framework. The results presented herein agree with post-processed trajectory information obtained from NASA’s SPICE kernels at the order of centimetres.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"7 3","pages":"301 - 314"},"PeriodicalIF":6.1,"publicationDate":"2023-04-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-023-0160-x.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50027235","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

Capacity of Sun-driven lunar swingby sequences and their application in asteroid retrieval 太阳驱动月球摆动序列的能力及其在小行星检索中的应用

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-04-11 DOI: 10.1007/s42064-023-0161-9

Hongru Chen

{"title":"Capacity of Sun-driven lunar swingby sequences and their application in asteroid retrieval","authors":"Hongru Chen","doi":"10.1007/s42064-023-0161-9","DOIUrl":"10.1007/s42064-023-0161-9","url":null,"abstract":"<div><p>For deep-space mission design, the gravity of the Sun and the Moon can be first considered and utilized. Their gravity can provide the energy change for launching spacecraft and retrieving spacecraft as well as asteroids. Regarding an asteroid retrieval mission, it can lead to the mitigation of asteroid hazards and an easy exploration and exploitation of the asteroid. This paper discusses the application of the Sun-driven lunar swingby sequence for asteroid missions. Characterizing the capacity of this technique is not only interesting in terms of the dynamic insights but also non-trivial for trajectory design. The capacity of a Sun-driven lunar swingby sequence is elucidated in this paper with the help of the “Swingby-Jacobi” graph. The capacity can be represented by a range of the Jacobi integral that encloses around 660 asteroids currently cataloged. To facilitate trajectory design, a database of Sun-perturbed Moon-to-Moon transfers, including multi-revolution cases, is generated and employed. Massive trajectory options for spacecraft launch and asteroid capture can then be explored and optimized. Finally, a number of asteroid flyby, rendezvous, sample-return, and retrieval mission options enabled by the proposed technique are obtained.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"7 3","pages":"315 - 334"},"PeriodicalIF":6.1,"publicationDate":"2023-04-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50019200","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 and guidance of a multi-active debris removal mission 多活动碎片清除任务的设计和指导

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-02-23 DOI: 10.1007/s42064-023-0159-3

Minduli C. Wijayatunga, Roberto Armellin, Harry Holt, Laura Pirovano, Aleksander A. Lidtke

{"title":"Design and guidance of a multi-active debris removal mission","authors":"Minduli C. Wijayatunga, Roberto Armellin, Harry Holt, Laura Pirovano, Aleksander A. Lidtke","doi":"10.1007/s42064-023-0159-3","DOIUrl":"10.1007/s42064-023-0159-3","url":null,"abstract":"<div><p>Space debris have become exceedingly dangerous over the years as the number of objects in orbit continues to increase. Active debris removal (ADR) missions have gained significant interest as effective means of mitigating the risk of collision between objects in space. This study focuses on developing a multi-ADR mission that utilizes controlled reentry and deorbiting. The mission comprises two spacecraft: a Servicer that brings debris to a low altitude and a Shepherd that rendezvous with the debris to later perform a controlled reentry. A preliminary mission design tool (PMDT) was developed to obtain time and fuel optimal trajectories for the proposed mission while considering the effect of <i>J</i><sub>2</sub>, drag, eclipses, and duty cycle. The PMDT can perform such trajectory optimizations for multi-debris missions with computational time under a minute. Three guidance schemes are also studied, taking the PMDT solution as a reference to validate the design methodology and provide guidance solutions to this complex mission profile.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"7 4","pages":"383 - 399"},"PeriodicalIF":6.1,"publicationDate":"2023-02-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"71910118","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: 4

Analytical configuration uncertainty propagation of geocentric interferometric detection constellation 地心干涉探测星座解析构型不确定度传播

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2023-01-16 DOI: 10.1007/s42064-022-0157-x

Dong Qiao, Xingyu Zhou, Xiangyu Li

{"title":"Analytical configuration uncertainty propagation of geocentric interferometric detection constellation","authors":"Dong Qiao, Xingyu Zhou, Xiangyu Li","doi":"10.1007/s42064-022-0157-x","DOIUrl":"10.1007/s42064-022-0157-x","url":null,"abstract":"<div><p>Long-term configuration stability is essential for an interferometric detection constellation (IDC), which is closely related to initial uncertainty. Therefore, it is vital to evaluate the uncertainty and characterize the configuration stability. In this study, an analytical method was developed for the configuration uncertainty propagation of a geocentric triangular IDC. The angular momentum and the argument latitude were found to be significantly affected by the initial uncertainty and were selected as the core variables. By averaging the perturbation in one revolution, an analytical solution was proposed for propagating the core orbital elements in one revolution. Subsequently, the analytical solution of the orbit elements during the mission period is obtained by multiplying the solutions in iterative revolutions. The relationship between the selected orbital elements and the configuration stability parameters was established using an analytical solution. The effects of the initial uncertainty in different directions on the configuration and stable domains were studied. Simulations show that the developed method is highly efficient and accurate in predicting the configuration stability. The relative error with respect to the Monte Carlo simulations was less than 3% with a time consumption of 0.1%. The proposed method can potentially be useful for constellation design and stability analysis.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"7 3","pages":"271 - 284"},"PeriodicalIF":6.1,"publicationDate":"2023-01-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50031741","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

Review of space relative navigation based on angles-only measurements 基于角度测量的空间相对导航综述

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-11-23 DOI: 10.1007/s42064-022-0152-2

Baichun Gong, Sha Wang, Shuang Li, Xianqiang Li

{"title":"Review of space relative navigation based on angles-only measurements","authors":"Baichun Gong, Sha Wang, Shuang Li, Xianqiang Li","doi":"10.1007/s42064-022-0152-2","DOIUrl":"10.1007/s42064-022-0152-2","url":null,"abstract":"<div><p>Relative navigation is a key enabling technology for space missions such as on-orbit servicing and space situational awareness. Given that there are several special advantages of space relative navigation using angles-only measurements from passive optical sensors, angles-only relative navigation is considered as one of the best potential approaches in the field of space relative navigation. However, angles-only relative navigation is well-known for its range observability problem. To overcome this observability problem, many studies have been conducted over the past decades. In this study, we present a comprehensive review of state-of-the-art space relative navigation based on angles-only measurements. The emphasis is on the observability problem and solutions to angles-only relative navigation, where the review of the solutions is categorized into four classes based on the intrinsic principle: complicated dynamics approach, multi-line of sight (multi-LOS) approach, sensor offset center-of-mass approach, and orbit maneuver approach. Then, the flight demonstration results of angles-only relative navigation in the two projects are briefly reviewed. Finally, conclusions of this study and recommendations for further research are presented.\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":"131 - 152"},"PeriodicalIF":6.1,"publicationDate":"2022-11-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50044756","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: 4

Feasibility analysis of angles-only navigation algorithm with multisensor data fusion for spacecraft noncooperative rendezvous 航天器非合作交会多传感器数据融合纯角度导航算法的可行性分析

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-11-23 DOI: 10.1007/s42064-022-0148-y

Ronghua Du, Wenhe Liao, Xiang Zhang

{"title":"Feasibility analysis of angles-only navigation algorithm with multisensor data fusion for spacecraft noncooperative rendezvous","authors":"Ronghua Du, Wenhe Liao, Xiang Zhang","doi":"10.1007/s42064-022-0148-y","DOIUrl":"10.1007/s42064-022-0148-y","url":null,"abstract":"<div><p>Relative navigation is crucial for spacecraft noncooperative rendezvous, and angles-only navigation using visible and infrared cameras provides a feasible solution. Herein, an angles-only navigation algorithm with multisensor data fusion is proposed to derive the relative motion states between two noncooperative spacecraft. First, the design model of the proposed algorithm is introduced, including the derivation of the state propagation and measurement equations. Subsequently, models for the sensor and actuator are introduced, and the effects of various factors on the sensors and actuators are considered. The square-root unscented Kalman filter is used to design the angles-only navigation filtering scheme. Additionally, the Clohessy—Wiltshire terminal guidance algorithm is introduced to obtain the theoretical relative motion trajectories during the rendezvous operations of two noncooperative spacecraft. Finally, the effectiveness of the proposed angles-only navigation algorithm is verified using a semi-physical simulation platform. The results prove that an optical navigation camera combined with average accelerometers and occasional orbital maneuvers is feasible for spacecraft noncooperative rendezvous using angles-only navigation.\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":"179 - 196"},"PeriodicalIF":6.1,"publicationDate":"2022-11-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50044754","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