Stability of Sun-Synchronous Orbits in the Vicinity of a Comet

Byram, Sharyl; Scheeres, Daniel J.

doi:10.2514/1.41655

Cited by 18 publications

(10 citation statements)

References 6 publications

(8 reference statements)

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“…This chapter draws from a number of different analyses of such motion [157,151,16,17,22] and only presents an introduction to the problem, leaving details to these other papers and for future work. This technique was applied during the Hayabusa mission to asteroid Itokawa, where the spacecraft maintained its location on the Sun-side of the asteroid by performing occasional thrusting maneuvers.…”

Section: Controlled Hovering Motion At An Asteroidmentioning

confidence: 99%

“…There have been only a relative few analyses of spacecraft with outgassing comets, essentially starting with Scheeres et al [172], the thesis and related study by Byram [21,23,22], and the more recent analyses by Mysen [115]. For these simple analytical models there are a number of results concerning how a spacecraft responds to this environment.…”

Section: Comet Outgassingmentioning

confidence: 99%

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Orbital Motion in Strongly Perturbed Environments

Scheeres

2012

Self Cite

193

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Section: Controlled Hovering Motion At An Asteroidmentioning

confidence: 99%

Section: Comet Outgassingmentioning

confidence: 99%

Orbital Motion in Strongly Perturbed Environments

Scheeres

2012

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193

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“…Many missions have the goal of exploring these bodies, like Belton et al, 1992Belton et al, , 1996Veverka et al, 2001;Yoshikawa et al, 2007;Jones et al, 2011;Huntress et al, 2006;Surovik and Scheeres, 2014;Broschart and Scheeres, 2005;Bellerose and Scheeres, 2008;Brum et al, 2011. Some other researches considered general trajectories around smaller bodies, which can be used in mission design of future missions to asteroids, like Werner, 1994;Rossi et al, 1999;Scheeres, 1994Scheeres, , 2012aScheeres and Hu, 2001; Bartczakk et al, 2006;Byram and Scheeres, 2009;Venditti and Prado, 2014. The present research is related to the mission named ASTER, that has some preliminary studies available in the literature Macau et al 2010). Its main objective is to study the triple NEA 2001SN 263 (Araú jo et al, 2012;Prado, 2014a, b), because it is believed that it contains information about the original composition of the Solar System.…”

Section: Introductionmentioning

confidence: 94%

Developing the “Precessing Inclined Bi-Elliptical Four-Body Problem with Radiation Pressure” to search for orbits in the triple asteroid 2001SN263

Masago

Prado

Chiaradia

et al. 2016

Advances in Space Research

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Space missions to visit small bodies of the Solar System are important steps to improve our knowledge of the Solar System. Usually those bodies do not have well known characteristics, as their gravity field, which make the mission planning a difficult task. The present paper has the goal of studying orbits around the triple asteroid 2001SN 263 , a Near-Earth Asteroid (NEA). A mission to this system allows the exploration of three bodies in the same trip. The distances reached by the spacecraft from those three bodies have fundamental importance in the quality of their observations. Therefore, the present research has two main goals: (i) to develop a semi-analytical mathematical model, which is simple, but able to represent the main characteristics of that system; (ii) to use this model to find orbits for a spacecraft with the goal of remaining the maximum possible time near the three bodies of the system, without the need of space maneuvers. This model is called ''Precessing Inclined Bi-Elliptical Problem with Radiation Pressure" (PIBEPRP). The use of this model allow us to find important natural orbits for the exploration of one, two or even the three bodies of the system. These trajectories can be used individually or combined in two or more parts using orbital maneuvers.

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“…This assumption is only used to estimate the magnitude of perturbation, but it is not a real mission scenario. The magnitude of perturbation acceleration caused by the solar tide effect is given by (Byram and Scheeres, 2009): where μ S = GM S is the gravitational parameter of the sun, G is the gravitational constant, M S is the mass of the sun and 1 ≤ δ ≤ 2 is a factor depending on the relative geometry of the spacecraft with respect to the sun and the asteroid. When the spacecraft is within the terminator plane, that is to say, the asteroid-spacecraft line is perpendicular to the sun-asteroid line, δ reaches its minimum value 1; when the spacecraft is located on the sun-asteroid line, δ reaches its maximum value 2.…”

Section: Orbital Perturbationsmentioning

confidence: 99%

Orbital perturbation due to orbit-attitude coupling near asteroids

Zhong

2018

AEAT

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Purpose The purpose of this paper is to assess the orbital perturbation caused by the gravitational orbit–attitude coupling of spacecraft in the proximity of asteroids. Design/methodology/approach The gravitational orbit–attitude coupling perturbation (GOACP), which has been neglected before in the close-proximity orbital dynamics about asteroids, is investigated and compared with other orbital perturbations. The GOACP has its origin in the fact that the gravity acting on a non-spherical extended body is actually different from that acting on a point mass located at the body’s center of mass, which is the approximated model in the orbital dynamics. Besides, a case study of a tethered satellite system is given by numerical simulations. Findings It is found that the ratio of GOACP to the asteroid’s non-spherical gravity is the order of ρ/ae, where ρ is the spacecraft’s characteristic dimension and ae is the asteroid’s mean radius. It can also be seen that as ρ increases, GOACP will also increase but the solar radiation pressure (SRP) will decrease due to the decreasing area-to-mass ratio. The GOACP will be more significant than SRP at small orbital radii for a large-sized spacecraft. Based on the results by analyses and simulations, it can be concluded that GOACP needs to be considered in the orbital dynamics for a large-sized spacecraft in the proximity of a small asteroid. Practical implications This study is of great importance for the future asteroids missions for scientific explorations and near-Earth objects mitigation. Originality/value The GOACP, which has been neglected before, is revealed and studied.

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Stability of Sun-Synchronous Orbits in the Vicinity of a Comet

Cited by 18 publications

References 6 publications

Orbital Motion in Strongly Perturbed Environments

Orbital Motion in Strongly Perturbed Environments

Developing the “Precessing Inclined Bi-Elliptical Four-Body Problem with Radiation Pressure” to search for orbits in the triple asteroid 2001SN263

Orbital perturbation due to orbit-attitude coupling near asteroids

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