Orbital Motion in Strongly Perturbed Environments

Scheeres, Daniel J.

doi:10.1007/978-3-642-03256-1

Cited by 195 publications

(143 citation statements)

References 114 publications

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“…According to Scheeres et al (1996); Scheeres (1999Scheeres ( , 2012, in the absence of any solar perturbations, the equations of motion of a spacecraft orbiting a uniformly rotating asteroid and significantly far from any other celestial body arë…”

Section: Equations Of Motionmentioning

confidence: 99%

The dynamical environment of asteroid 21 Lutetia according to different internal models

Aljbaae

Chanut

Carruba

et al. 2016

Mon. Not. R. Astron. Soc.

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One of the most accurate models currently used to represent the gravity field of irregular bodies is the polyhedral approach. In this model, the mass of the body is assumed to be homogeneous, which may not be true for a real object. The main goal of the present paper is to study the dynamical effects induced by three different internal structures (uniform, three-and four-layers) of asteroid (21) Lutetia, an object that recent results from space probe suggest being at least partially differentiated. The Mascon gravity approach used in the present work, consists of dividing each tetrahedron into eight parts to calculate the gravitational field around the asteroid. The zero-velocity curves show that the greatest displacement of the equilibrium points occurs in the position of the E4 point for the four-layers structure and the smallest one occurs in the position of the E3 point for the three-layers structure. Moreover, stability against impact shows that the planar limit gets slightly closer to the body with the four-layered structure.We then investigated the stability of orbital motion in the equatorial plane of (21) Lutetia and propose numerical stability criteria to map the region of stable motions. Layered structures could stabilize orbits that were unstable in the homogeneous model.

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Section: Equations Of Motionmentioning

confidence: 99%

The dynamical environment of asteroid 21 Lutetia according to different internal models

Aljbaae

Chanut

Carruba

et al. 2016

Mon. Not. R. Astron. Soc.

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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 orbit will also be used, later, by the human spacecraft. One of the most important trade-offs in the target body selection is that spacecraft about small target bodies with weak gravity fields suffer a significant perturbation from the solar radiation pressure (SRP) [41].…”

Section: Gravity Field Characterizationmentioning

confidence: 99%