不规则小行星轨道不确定性传播的一种高效全局方法

IF 2.8 3区 地球科学 Q2 ASTRONOMY & ASTROPHYSICS
Xuefen Zhang, Haibin Shang, Jucheng Lu, Zichen Zhao
{"title":"不规则小行星轨道不确定性传播的一种高效全局方法","authors":"Xuefen Zhang,&nbsp;Haibin Shang,&nbsp;Jucheng Lu,&nbsp;Zichen Zhao","doi":"10.1016/j.asr.2025.02.031","DOIUrl":null,"url":null,"abstract":"<div><div>Asteroid close-proximity missions, such as orbiting, hovering, and landing, face significant dynamical challenges owing to the irregular and highly perturbed gravitational field. Orbital uncertainty plays a key role in close-proximity operations around asteroids. This study seeks to develop an efficient and global approach for dealing with orbit uncertainty propagation in an asteroid dynamical environment. First, to achieve global applicability and enhance efficiency, the quadrature-based polyhedral model is employed to represent the gravity of the irregularly shaped asteroid. The solar radiation pressure and the Sun’s third-body gravity are considered to ensure the accuracy of the dynamic model. Second, the Analytic Continuation technique, originally developed for the perturbed two-body problem, is expanded to compute higher-order State Transition Tensors (STTs) of the high-fidelity dynamics. Recursive formulas for the time derivatives of STTs are obtained using the Leibniz product rule, enabling the STTs to be conveniently approximated through arbitrary-order Taylor series. Finally, by incorporating adaptive time steps and expansion order, an efficient algorithm for predicting the orbit state probability density function is developed. The orbit near the irregularly shaped, dog-bone-like asteroid 216 Kleopatra is used to demonstrate the effectiveness of the proposed method. Numerical simulations confirm the global applicability of the proposed method for uncertainty propagation, even for orbits involving multiple close flybys over the asteroid. Using only the fourth-order STT achieves results similar to full-scale Monte Carlo simulations with 50,000 samples but only needs 3% of the computational effort. These results strongly demonstrate that the proposed algorithm is a suitable tool for uncertainty propagation in asteroid exploration mission analysis.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"75 8","pages":"Pages 6406-6424"},"PeriodicalIF":2.8000,"publicationDate":"2025-02-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"An efficient and global method for orbit uncertainty propagation near irregular-shaped asteroids\",\"authors\":\"Xuefen Zhang,&nbsp;Haibin Shang,&nbsp;Jucheng Lu,&nbsp;Zichen Zhao\",\"doi\":\"10.1016/j.asr.2025.02.031\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"<div><div>Asteroid close-proximity missions, such as orbiting, hovering, and landing, face significant dynamical challenges owing to the irregular and highly perturbed gravitational field. Orbital uncertainty plays a key role in close-proximity operations around asteroids. This study seeks to develop an efficient and global approach for dealing with orbit uncertainty propagation in an asteroid dynamical environment. First, to achieve global applicability and enhance efficiency, the quadrature-based polyhedral model is employed to represent the gravity of the irregularly shaped asteroid. The solar radiation pressure and the Sun’s third-body gravity are considered to ensure the accuracy of the dynamic model. Second, the Analytic Continuation technique, originally developed for the perturbed two-body problem, is expanded to compute higher-order State Transition Tensors (STTs) of the high-fidelity dynamics. Recursive formulas for the time derivatives of STTs are obtained using the Leibniz product rule, enabling the STTs to be conveniently approximated through arbitrary-order Taylor series. Finally, by incorporating adaptive time steps and expansion order, an efficient algorithm for predicting the orbit state probability density function is developed. The orbit near the irregularly shaped, dog-bone-like asteroid 216 Kleopatra is used to demonstrate the effectiveness of the proposed method. Numerical simulations confirm the global applicability of the proposed method for uncertainty propagation, even for orbits involving multiple close flybys over the asteroid. Using only the fourth-order STT achieves results similar to full-scale Monte Carlo simulations with 50,000 samples but only needs 3% of the computational effort. These results strongly demonstrate that the proposed algorithm is a suitable tool for uncertainty propagation in asteroid exploration mission analysis.</div></div>\",\"PeriodicalId\":50850,\"journal\":{\"name\":\"Advances in Space Research\",\"volume\":\"75 8\",\"pages\":\"Pages 6406-6424\"},\"PeriodicalIF\":2.8000,\"publicationDate\":\"2025-02-18\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Advances in Space Research\",\"FirstCategoryId\":\"89\",\"ListUrlMain\":\"https://www.sciencedirect.com/science/article/pii/S0273117725001516\",\"RegionNum\":3,\"RegionCategory\":\"地球科学\",\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"Q2\",\"JCRName\":\"ASTRONOMY & ASTROPHYSICS\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Advances in Space Research","FirstCategoryId":"89","ListUrlMain":"https://www.sciencedirect.com/science/article/pii/S0273117725001516","RegionNum":3,"RegionCategory":"地球科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q2","JCRName":"ASTRONOMY & ASTROPHYSICS","Score":null,"Total":0}
引用次数: 0

摘要

小行星轨道、悬停和着陆等近距离任务由于其不规则和高度扰动的引力场而面临着重大的动力学挑战。轨道的不确定性在小行星的近距离操作中起着关键作用。本研究旨在开发一种有效和全局的方法来处理小行星动态环境中的轨道不确定性传播。首先,为了实现全局适用性和提高效率,采用基于正交的多面体模型来表示不规则形状小行星的重力。为了保证动力学模型的准确性,考虑了太阳辐射压力和太阳第三体重力。其次,将最初用于摄动二体问题的解析延拓技术扩展到计算高保真动力学的高阶状态转移张量。利用莱布尼茨积法则得到了stt时间导数的递推公式,使stt可以方便地用任意阶泰勒级数逼近。最后,结合自适应时间步长和展开阶数,提出了一种有效的轨道状态概率密度函数预测算法。这颗形状不规则、像狗骨头一样的小行星216 Kleopatra附近的轨道被用来证明所提出方法的有效性。数值模拟证实了所提出的方法在不确定性传播方面的全局适用性,即使对于涉及多次近距离飞越小行星的轨道也是如此。仅使用四阶STT就可以获得与50,000个样本的全尺寸蒙特卡罗模拟相似的结果,但只需要3%的计算工作量。结果表明,该算法是一种适用于小行星探测任务分析的不确定性传播工具。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
An efficient and global method for orbit uncertainty propagation near irregular-shaped asteroids
Asteroid close-proximity missions, such as orbiting, hovering, and landing, face significant dynamical challenges owing to the irregular and highly perturbed gravitational field. Orbital uncertainty plays a key role in close-proximity operations around asteroids. This study seeks to develop an efficient and global approach for dealing with orbit uncertainty propagation in an asteroid dynamical environment. First, to achieve global applicability and enhance efficiency, the quadrature-based polyhedral model is employed to represent the gravity of the irregularly shaped asteroid. The solar radiation pressure and the Sun’s third-body gravity are considered to ensure the accuracy of the dynamic model. Second, the Analytic Continuation technique, originally developed for the perturbed two-body problem, is expanded to compute higher-order State Transition Tensors (STTs) of the high-fidelity dynamics. Recursive formulas for the time derivatives of STTs are obtained using the Leibniz product rule, enabling the STTs to be conveniently approximated through arbitrary-order Taylor series. Finally, by incorporating adaptive time steps and expansion order, an efficient algorithm for predicting the orbit state probability density function is developed. The orbit near the irregularly shaped, dog-bone-like asteroid 216 Kleopatra is used to demonstrate the effectiveness of the proposed method. Numerical simulations confirm the global applicability of the proposed method for uncertainty propagation, even for orbits involving multiple close flybys over the asteroid. Using only the fourth-order STT achieves results similar to full-scale Monte Carlo simulations with 50,000 samples but only needs 3% of the computational effort. These results strongly demonstrate that the proposed algorithm is a suitable tool for uncertainty propagation in asteroid exploration mission analysis.
求助全文
通过发布文献求助,成功后即可免费获取论文全文。 去求助
来源期刊
Advances in Space Research
Advances in Space Research 地学天文-地球科学综合
CiteScore
5.20
自引率
11.50%
发文量
800
审稿时长
5.8 months
期刊介绍: The COSPAR publication Advances in Space Research (ASR) is an open journal covering all areas of space research including: space studies of the Earth''s surface, meteorology, climate, the Earth-Moon system, planets and small bodies of the solar system, upper atmospheres, ionospheres and magnetospheres of the Earth and planets including reference atmospheres, space plasmas in the solar system, astrophysics from space, materials sciences in space, fundamental physics in space, space debris, space weather, Earth observations of space phenomena, etc. NB: Please note that manuscripts related to life sciences as related to space are no more accepted for submission to Advances in Space Research. Such manuscripts should now be submitted to the new COSPAR Journal Life Sciences in Space Research (LSSR). All submissions are reviewed by two scientists in the field. COSPAR is an interdisciplinary scientific organization concerned with the progress of space research on an international scale. Operating under the rules of ICSU, COSPAR ignores political considerations and considers all questions solely from the scientific viewpoint.
×
引用
GB/T 7714-2015
复制
MLA
复制
APA
复制
导出至
BibTeX EndNote RefMan NoteFirst NoteExpress
×
提示
您的信息不完整,为了账户安全,请先补充。
现在去补充
×
提示
您因"违规操作"
具体请查看互助需知
我知道了
×
提示
确定
请完成安全验证×
copy
已复制链接
快去分享给好友吧!
我知道了
右上角分享
点击右上角分享
0
联系我们:info@booksci.cn Book学术提供免费学术资源搜索服务,方便国内外学者检索中英文文献。致力于提供最便捷和优质的服务体验。 Copyright © 2023 布克学术 All rights reserved.
京ICP备2023020795号-1
ghs 京公网安备 11010802042870号
Book学术文献互助
Book学术文献互助群
群 号:481959085
Book学术官方微信