Celestial mechanics and dynamical astronomy最新文献

Understanding flow around planetary moons via finite-time Lyapunov exponent maps 通过有限时间李亚普诺夫指数图了解行星卫星周围的流动情况

Celestial mechanics and dynamical astronomy Pub Date : 2024-09-11 DOI: 10.1007/s10569-024-10213-3

David Canales, Kathleen Howell

{"title":"Understanding flow around planetary moons via finite-time Lyapunov exponent maps","authors":"David Canales, Kathleen Howell","doi":"10.1007/s10569-024-10213-3","DOIUrl":"https://doi.org/10.1007/s10569-024-10213-3","url":null,"abstract":"This contribution focuses on the use of finite-time Lyapunov exponent (FTLE) maps to investigate spacecraft motion within the context of the circular restricted three-body problem as a conceptual model. The study explores the advantages and limitations of FTLE maps by examining spacecraft trajectories in the vicinity of the Jovian moons, Ganymede and Europa. The paper introduces an atlas of FTLE maps for different energy levels surrounding Ganymede, highlighting critical regions that define types of motion and energy thresholds. Additionally, the authors also explore the symmetry relationships of the Lagrangian coherent structures that are defined within the FTLE maps. Establishing relationships between initial conditions within the FTLE maps is essential for understanding trajectory behaviors in the neighborhoods of moons. The results demonstrate that by utilizing FTLE maps, a better understanding of spacecraft behavior in the vicinity of celestial bodies emerges, potentially enabling more precise mission planning and execution. The findings and methodologies are extendable to other planet–moon systems, providing a valuable framework for future space missions.","PeriodicalId":72537,"journal":{"name":"Celestial mechanics and dynamical astronomy","volume":"8 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-09-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142220000","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Spin orbit resonance cascade via core shell model: application to Mercury and Ganymede 通过核壳模型实现自旋轨道共振级联：应用于水星和木卫三

Celestial mechanics and dynamical astronomy Pub Date : 2024-09-10 DOI: 10.1007/s10569-024-10207-1

Gabriella Pinzari, Benedetto Scoppola, Matteo Veglianti

引用次数: 0

Orbiting below the Brillouin sphere using shifted spherical harmonics 利用移位球面谐波在布里渊球面以下绕行

Celestial mechanics and dynamical astronomy Pub Date : 2024-09-04 DOI: 10.1007/s10569-024-10210-6

David Cunningham, Ryan P. Russell, Martin W. Lo

{"title":"Orbiting below the Brillouin sphere using shifted spherical harmonics","authors":"David Cunningham, Ryan P. Russell, Martin W. Lo","doi":"10.1007/s10569-024-10210-6","DOIUrl":"https://doi.org/10.1007/s10569-024-10210-6","url":null,"abstract":"Spacecraft trajectories near the south pole of Enceladus violate the Brillouin sphere associated with the convergence radius of spherical harmonics models. In this study, a shifted coordinate frame is demonstrated to ensure a convergent model is available in regions of operational interest. Hypothetical experiments are performed around a simulated celestial body where the truth exterior gravity fields are known exactly. The divergence of the harmonics below the Brillouin sphere of the unshifted models is confirmed, while the shifted harmonics model converges. The method is next applied to the Cassini-derived gravity field for Enceladus, including uncertainties. Using these low-degree and low-order reference models, expected for use in an operational setting, the results show that the shifted and body-centered harmonics models agree to near machine precision for all evaluations at or above the surface, and no divergence is noticed. The results imply that mission designers and navigation engineers can safely use a traditional spherical harmonics field for Enceladus, even in regions that dip below the Brillouin sphere. For low-flying missions to celestial bodies besides Enceladus, the experiments conducted in this study can be repeated. The need for an alternative to the traditional spherical harmonics, such as the presented shifted model, increases for bodies that are increasingly non-spherical and orbits that are deeper inside the Brillouin sphere.","PeriodicalId":72537,"journal":{"name":"Celestial mechanics and dynamical astronomy","volume":"6 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-09-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142220003","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Spin–orbit coupling of the primary body in a binary asteroid system 双小行星系统中主天体的自旋轨道耦合

Celestial mechanics and dynamical astronomy Pub Date : 2024-09-02 DOI: 10.1007/s10569-024-10211-5

Hanlun Lei

{"title":"Spin–orbit coupling of the primary body in a binary asteroid system","authors":"Hanlun Lei","doi":"10.1007/s10569-024-10211-5","DOIUrl":"https://doi.org/10.1007/s10569-024-10211-5","url":null,"abstract":"Spin–orbit coupling is widespread in binary asteroid systems, and it has been widely studied for the case of ellipsoidal secondary. Due to angular momentum exchange, dynamical coupling is stronger when the orbital and rotational angular momenta are closer in magnitudes. Thus, the spin–orbit coupling effects are significantly different for ellipsoidal secondaries and primaries. In the present work, a high-order Hamiltonian model in terms of eccentricity is formulated to study the effects of spin–orbit coupling for the case of ellipsoidal primary body in a binary asteroid system. Our results show that the spin–orbit coupling problem for the ellipsoidal primary holds two kinds of spin equilibrium, while there is only one for the ellipsoidal secondary. In particular, 1:1 and 2:3 spin–orbit resonances are further studied by taking both the classical pendulum approximation and adiabatic approximation (Wisdom’s perturbative treatment). It shows that there is a critical value of total angular momentum, around which the pendulum approximation fails to work. Dynamical structures are totally different when the total angular momentum is on two sides of the critical value.\u0000","PeriodicalId":72537,"journal":{"name":"Celestial mechanics and dynamical astronomy","volume":"60 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-09-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142220002","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Application of the theory of functional connections to the perturbed Lambert’s problem 功能连接理论在扰动朗伯问题中的应用

Celestial mechanics and dynamical astronomy Pub Date : 2024-09-02 DOI: 10.1007/s10569-024-10212-4

Franco Criscola, David Canales, Daniele Mortari

引用次数: 0

Simulating a breakup event and propagating the orbits of space debris 模拟解体事件并传播空间碎片轨道

Celestial mechanics and dynamical astronomy Pub Date : 2024-08-31 DOI: 10.1007/s10569-024-10205-3

Marius Apetrii, Alessandra Celletti, Christos Efthymiopoulos, Cǎtǎlin Galeş, Tudor Vartolomei

{"title":"Simulating a breakup event and propagating the orbits of space debris","authors":"Marius Apetrii, Alessandra Celletti, Christos Efthymiopoulos, Cǎtǎlin Galeş, Tudor Vartolomei","doi":"10.1007/s10569-024-10205-3","DOIUrl":"https://doi.org/10.1007/s10569-024-10205-3","url":null,"abstract":"Explosions or collisions of satellites around the Earth generate space debris, whose uncontrolled dynamics might raise serious threats for operational satellites. Mitigation actions can be realized on the basis of our knowledge of the characteristics of the fragments produced during the breakup event and their subsequent propagation. In this context, important information can be obtained by implementing a breakup simulator, which provides, for example, the number of fragments, their area-to-mass ratio or the relative velocity distribution as a function of the characteristic length of the fragments. Motivated by the need to analyze the dynamics of the fragments, we reconstruct a simulator based on the NASA/JSC breakup model EVOLVE 4.0 that we review for self-consistency. This model, created at the beginning of the XXI century, is based on laboratory and on-orbit tests. Given that materials and methods for building satellites are constantly progressing, we leave some key parameters variable and produce results for different choices of the parameters. We will also present an application to the Iridium–Cosmos collision and we discuss the distribution function after a breakup event. The breakup model is strongly related to the propagation of the fragments; in this work, we discuss how to choose the models and the numerical integrators, we propose examples of how fragments can disperse in time, and we study the behavior of multiple simultaneous fragmentations. Finally, we compute some indicators for detecting streams of fragments. Breakup and propagation are performed using our own simulator SIMPRO, built from EVOLVE 4.0; the executable program will be freely available on GitHub.","PeriodicalId":72537,"journal":{"name":"Celestial mechanics and dynamical astronomy","volume":"7 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142220005","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Forced periodic motion by solar radiation pressure in the polyhedral gravity model 多面体重力模型中太阳辐射压力的强制周期运动

Celestial mechanics and dynamical astronomy Pub Date : 2024-08-24 DOI: 10.1007/s10569-024-10206-2

Anivid Pedros-Faura, Gavin M. Brown, Jay W. McMahon, Daniel J. Scheeres

{"title":"Forced periodic motion by solar radiation pressure in the polyhedral gravity model","authors":"Anivid Pedros-Faura, Gavin M. Brown, Jay W. McMahon, Daniel J. Scheeres","doi":"10.1007/s10569-024-10206-2","DOIUrl":"https://doi.org/10.1007/s10569-024-10206-2","url":null,"abstract":"The exploration of small bodies in our solar system is of great interest for the planetary science community due to their high scientific value. However, their generally weak and irregular gravity fields increase the difficulty associated with close proximity operations. Moreover, solar radiation pressure (SRP) can significantly perturb the motion of objects in their vicinity, particularly for bodies with high area-to-mass ratios. In this work, we adopt the polyhedral gravity model and identify natural dynamical structures that can be used for mission operations. Further, we study forced periodic motion in the body fixed frame while accounting for the effect of SRP with eclipses. Overall, our work seeks to identify suitable orbits and locations in the vicinity of small bodies that can be exploited for the design of science orbits. To obtain periodic orbits in the model accounting for SRP perturbations, we use a Melnikov function to find orbits that satisfy resonances with the asteroid spin and show no net change in energy over the orbit. We then use a differential correction scheme to find numerical solutions in the time-periodic model. Our test cases are potentially hazardous asteroid 101955 Bennu and main belt asteroid 16 Psyche.\u0000","PeriodicalId":72537,"journal":{"name":"Celestial mechanics and dynamical astronomy","volume":"25 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142220004","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Correction: Periodic orbits in a galactic potential 更正：银河势中的周期轨道

Celestial mechanics and dynamical astronomy Pub Date : 2024-07-27 DOI: 10.1007/s10569-024-10198-z

M. Harsoula, G. Contopoulos

引用次数: 0

Analytical theory of the spin-orbit state of a binary asteroid deflected by a kinetic impactor 动能撞击器偏转双小行星自旋轨道状态的解析理论

Celestial mechanics and dynamical astronomy Pub Date : 2024-07-13 DOI: 10.1007/s10569-024-10204-4

Michalis Gaitanas, Christos Efthymiopoulos, Ioannis Gkolias, George Voyatzis, Kleomenis Tsiganis

引用次数: 0

Dynamics around the Earth–Moon triangular points in the Hill restricted 4-body problem 希尔受限四体问题中围绕地月三角点的动力学

Celestial mechanics and dynamical astronomy Pub Date : 2024-07-09 DOI: 10.1007/s10569-024-10203-5

Luke T. Peterson, Gavin Brown, Àngel Jorba, Daniel Scheeres

{"title":"Dynamics around the Earth–Moon triangular points in the Hill restricted 4-body problem","authors":"Luke T. Peterson, Gavin Brown, Àngel Jorba, Daniel Scheeres","doi":"10.1007/s10569-024-10203-5","DOIUrl":"https://doi.org/10.1007/s10569-024-10203-5","url":null,"abstract":"This paper investigates the motion of a small particle moving near the triangular points of the Earth–Moon system. The dynamics are modeled in the Hill restricted 4-body problem (HR4BP), which includes the effect of the Earth and Moon as in the circular restricted 3-body problem (CR3BP), as well as the direct and indirect effect of the Sun as a periodic time-dependent perturbation of the CR3BP. Due to the periodic perturbation, the triangular points of the CR3BP are no longer equilibrium solutions; rather, the triangular points are replaced by periodic orbits with the same period as the perturbation. Additionally, there is a 2:1 resonant periodic orbit that persists from the CR3BP into the HR4BP. In this work, we investigate the dynamics around these invariant objects by performing a center manifold reduction and computing families of 2-dimensional invariant tori and their linear normal behavior. We identify bifurcations and relationships between families. Mechanisms for transport between the Earth, (L_4), and the Moon are discussed. Comparisons are made between the results presented here and in the bicircular problem (BCP).","PeriodicalId":72537,"journal":{"name":"Celestial mechanics and dynamical astronomy","volume":"72 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-07-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141575120","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0