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 th...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 geormnetric and geopotential topographies of 2016 HO3 were examined using difterent shape models.The liftoff 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.展开更多
Correction to:Oki,Y.,Yoshikawa,K.,Takeuchi,H.et al.Orbit insertion strategy of Hayabusa2's rover with large release uncertainty around the asteroid Ryugu.Astrodynamics 2020,4(4):309-329 https://doi.org/10.1007/s42...Correction to:Oki,Y.,Yoshikawa,K.,Takeuchi,H.et al.Orbit insertion strategy of Hayabusa2's rover with large release uncertainty around the asteroid Ryugu.Astrodynamics 2020,4(4):309-329 https://doi.org/10.1007/s42064-020-0080-y The article“Orbit insertion strategy of Hayabusa2’s rover with large release uncertainty around the asteroid Ryugu”written by Yusuke Oki,Kent Yoshikawa,Hiroshi Takeuchi et al.,was originally published electronically on the publisher’s internet portal(currently SpringerLink)on 05 November 2020 without open access.After publication in Volume 4,Issue 4,page 309–329,the author(s)decided to opt for Open Choice and to make the article an open access publication.展开更多
Comet exploration missions represented by the Comet Interceptor mission have attracted our attention to unravel the origin of our solar system.However,it is difficult to know the details of orbital data about long per...Comet exploration missions represented by the Comet Interceptor mission have attracted our attention to unravel the origin of our solar system.However,it is difficult to know the details of orbital data about long period comets(LPCs)until their approach.Additionally,the amount of fuel consumption by the current intercept approach depends on the intersection points of cometary orbits with the ecliptic plane.To address these challenges,designing low-energy transfer trajectories suitable for the observation of LPCs is necessary.This paper introduces a novel approach bv utilizing invariant manifold structures in the Sun-Earth circular restricted three-body problem for comet missions with multiple probes.As candidates for departure orbits,periodic orbits and quasi-periodic orbits are considered.Based on the optimal control theory,low-thrust trajectories to improve mission efficiency for enlarging the reachable domain of multiple probes are designed by leveraging invariant manifolds.The trajectories guided by invariant manifolds and optimal control theory facilitate formation flying,multi-point observations,and explorations of unknown comets by multiple probes.展开更多
The Hayabusa2 extended mission,named Hayabusa2#(SHARP:Small Hazardous Asteroid Reconnaissance Probe),is planned to rendezvous with the fast-rotating asteroid 1998 KY26 in 2031.Hayabusa2#will be the first ever mission ...The Hayabusa2 extended mission,named Hayabusa2#(SHARP:Small Hazardous Asteroid Reconnaissance Probe),is planned to rendezvous with the fast-rotating asteroid 1998 KY26 in 2031.Hayabusa2#will be the first ever mission to rendezvous with such a rapidly rotating small asteroid,posing significant challenges because of its distinctive dynamical environment.In this paper,we investigate potential target marker(TM)deployment strategies,for both landing and orbiting scenarios,to maximize science acquisition.In particular,we model the surface and orbital environments to identify feasible target market operations and present landing site selection strategies and candidate insertion orbits considering realistic deployment errors.The TM is one of the only two remaining deployable payloads,and therefore,can play a critical role during the extended mission phase.Our results show that surface operations can be extremely challenging whereas orbit operations could help us gain valuable information on the asteroid's gravity field.Overall,this research contributes to the exploration and characterization of extremely small bodies specifically through the use of artificial objects,in this case the target marker.展开更多
基金support from the National Natural Science Foundation of China(Grant Nos.12002028 and 51827806)Beijing Institute of Technology Research Fund Program for Young Scholars,China Postdoctoral Science Foundation funded project(Grant No.2019QT0038)Ann and H.J.Smead Aerospace Engineering Science Department,University of Colorado Boulder。
文摘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 geormnetric and geopotential topographies of 2016 HO3 were examined using difterent shape models.The liftoff 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.
文摘Correction to:Oki,Y.,Yoshikawa,K.,Takeuchi,H.et al.Orbit insertion strategy of Hayabusa2's rover with large release uncertainty around the asteroid Ryugu.Astrodynamics 2020,4(4):309-329 https://doi.org/10.1007/s42064-020-0080-y The article“Orbit insertion strategy of Hayabusa2’s rover with large release uncertainty around the asteroid Ryugu”written by Yusuke Oki,Kent Yoshikawa,Hiroshi Takeuchi et al.,was originally published electronically on the publisher’s internet portal(currently SpringerLink)on 05 November 2020 without open access.After publication in Volume 4,Issue 4,page 309–329,the author(s)decided to opt for Open Choice and to make the article an open access publication.
基金The work of the second author was supported by JSPS KAKENHI(Grant Number JP 23KJ1692)The work of the third author was partially supported by Japan Science and Technology Agency,Fusion Oriented Research for Disruptive Science and Technology(JST FOREST Program)(Grant Number JPMJFR206M)Grant-in-Aid for Scientific Research from the Japan Society for the Promotion of Science(Grant Number 22H03663).
文摘Comet exploration missions represented by the Comet Interceptor mission have attracted our attention to unravel the origin of our solar system.However,it is difficult to know the details of orbital data about long period comets(LPCs)until their approach.Additionally,the amount of fuel consumption by the current intercept approach depends on the intersection points of cometary orbits with the ecliptic plane.To address these challenges,designing low-energy transfer trajectories suitable for the observation of LPCs is necessary.This paper introduces a novel approach bv utilizing invariant manifold structures in the Sun-Earth circular restricted three-body problem for comet missions with multiple probes.As candidates for departure orbits,periodic orbits and quasi-periodic orbits are considered.Based on the optimal control theory,low-thrust trajectories to improve mission efficiency for enlarging the reachable domain of multiple probes are designed by leveraging invariant manifolds.The trajectories guided by invariant manifolds and optimal control theory facilitate formation flying,multi-point observations,and explorations of unknown comets by multiple probes.
基金the financial support offered by the la Caixa Foundation(ID 100010434)under agreement LCF/BQ/AA20/11820034 to support the Ph.D.studies of A.P.F.This project has received funding from the European Union's Horizon 2020 research+1 种基金innovation programme under the Marie Sklodowska-Curie grant agreement No.896404-CRADLEThis work was supported by JSPS KAKENHI Grant Number JP22H01687.
文摘The Hayabusa2 extended mission,named Hayabusa2#(SHARP:Small Hazardous Asteroid Reconnaissance Probe),is planned to rendezvous with the fast-rotating asteroid 1998 KY26 in 2031.Hayabusa2#will be the first ever mission to rendezvous with such a rapidly rotating small asteroid,posing significant challenges because of its distinctive dynamical environment.In this paper,we investigate potential target marker(TM)deployment strategies,for both landing and orbiting scenarios,to maximize science acquisition.In particular,we model the surface and orbital environments to identify feasible target market operations and present landing site selection strategies and candidate insertion orbits considering realistic deployment errors.The TM is one of the only two remaining deployable payloads,and therefore,can play a critical role during the extended mission phase.Our results show that surface operations can be extremely challenging whereas orbit operations could help us gain valuable information on the asteroid's gravity field.Overall,this research contributes to the exploration and characterization of extremely small bodies specifically through the use of artificial objects,in this case the target marker.
