Frozen Orbits with Equatorial Perturbing Bodies: The Case of Ganymede, Callisto, and Titan

Condoleo, Ennio; Cinelli, Marco; Ortore, Emiliano; Circi, Christian

doi:10.2514/1.g000455

Cited by 26 publications

(11 citation statements)

References 28 publications

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“…It also considers the cases for g 0 = 270 • and 180 • . This result appears similar to the ones presented in Condoleo et al (2016) considering the dynamics of a spacecraft orbiting Callisto under the disturbing potentials R 2 and J 2 .…”

Section: Resultssupporting

confidence: 89%

Lifetime maps for orbits around Callisto using a double-averaged model

Santos

Carvalho

Prado

et al. 2017

Astrophys Space Sci

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The present paper studies the lifetime of orbits around a moon that is in orbit around its mother planet. In the context of the inner restricted three-body problem, the dynamical model considered in the present study uses the double-averaged dynamics of a spacecraft moving around a moon under the gravitational pulling of a disturbing third body in an elliptical orbit. The non-uniform distribution of the mass of the moon is also considered. Applications are performed using numerical experiments for the Callistospacecraft-Jupiter system, and lifetime maps for different values of the eccentricity of the disturbing body (Jupiter) are presented, in order to investigate the role of this parameter in these maps. The idea is to simulate a system with the same physical parameters as the Jupiter-Callisto system, but with larger eccentricities. These maps are also useful for validation and improvements in the results available in the literature, such as to find conditions to extend the available time for a massless orbiting body to be in highly inclined orbits under gravitational disturbances coming from the other bodies of the system.

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Section: Resultssupporting

confidence: 89%

Lifetime maps for orbits around Callisto using a double-averaged model

Santos

Carvalho

Prado

et al. 2017

Astrophys Space Sci

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“…Eqs. (7)(8)(9)(10)(11) can be employed to obtain frozen orbit initial conditions at maximum latitude in terms of osculating orbital elements and starting from a set of desired mean orbital elements.…”

Section: Maximum-latitude Conditionsmentioning

confidence: 99%

“…orbits obtained by applying Eqs. (7)(8)(9)(10)(11)) are reported in Table 4 for comparison and show that MiSO orbits can provide an SOR reduction of up to almost 600 m compared to the unoptimized case. 6) show the evolution of the 10-day fixed-timespan SOR function over a period of 100 days for the 12 planes of the five classes of orbits.…”

Section: Drag-free Miso Orbitsmentioning

confidence: 99%

“…To our knowledge, there has been no effort in the available literature to obtain initial conditions leading to an absolute minimum of the altitude variations of a LEO orbiting spacecraft in a given time span 6 . Note that quasi-frozen orbits including tesseral harmonics, third-body perturbations and solar radiation pressure have been obtained in the literature using a double-averaging approach ( [6,7,8,9]), which certainly provides an increase in orbit lifetime and stability but does not necessarily lead to a minimization of altitude oscillations at equal latitude.…”

Section: Introductionmentioning

confidence: 99%

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Space Occupancy in Low-Earth Orbit

Bombardelli¹,

Falco²,

Amato³

et al. 2020

Preprint

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With the upcoming launch of large constellations of satellites in the low-Earth orbit (LEO) region it will become important to organize the physical space occupied by the different operating satellites in order to minimize critical conjunctions and avoid collisions. Here, we introduce the definition of space occupancy as the domain occupied by an individual satellite as it moves along its nominal orbit under the effects of environmental perturbations throughout a given interval of time. After showing that space occupancy for the zonal problem is intimately linked to the concept of frozen orbits and proper eccentricity, we provide

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“…is in turn leads to the search for orbits satisfying these requirements. e families of orbits satisfying such conditions are called "frozen orbits" [1][2][3][4][5]. Clearly, the design of such orbits includes the effects of the perturbing influences that affect the motion of the satellite.…”

Section: Introductionmentioning

confidence: 99%

Balanced Low Earth Satellite Orbits

Mostafa

Dewaik

2020

Advances in Astronomy

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The present work aims at constructing an atlas of the balanced Earth satellite orbits with respect to the secular and long periodic effects of Earth oblateness with the harmonics of the geopotential retained up to the 4th zonal harmonic. The variations of the elements are averaged over the fast and medium angles, thus retaining only the secular and long periodic terms. The models obtained cover the values of the semi-major axis from 1.1 to 2 Earth’s radii, although this is applicable only for 1.1 to 1.3 Earth’s radii due to the radiation belts. The atlas obtained is useful for different purposes, with those having the semi-major axis in this range particularly for remote sensing and meteorology.

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Frozen Orbits with Equatorial Perturbing Bodies: The Case of Ganymede, Callisto, and Titan

Cited by 26 publications

References 28 publications

Lifetime maps for orbits around Callisto using a double-averaged model

Lifetime maps for orbits around Callisto using a double-averaged model

Space Occupancy in Low-Earth Orbit

Balanced Low Earth Satellite Orbits

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