Quasi-terminator orbits near primitive bodies

Broschart, Stephen B.; Lantoine, Gregory; Grebow, Daniel J.

doi:10.1007/s10569-014-9574-3

Cited by 42 publications

(26 citation statements)

References 16 publications

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“…Actually for realistic values for a solar sail [FJM14] the displaced L 1 equilibria are out of the Hill sphere of influence and the AH3BP is no longer a good approximation to describe the dynamics around them. On the other hand, previous works [BLG14] show that we can find, around the displaced L 2 equilibria, periodic and quasi-periodic orbits that spend more than half of the time on the day side, which would be useful in a practical mission. For these reasons, we only focus on the dynamics around the equilibrium points belonging to the L 2 family.…”

Section: Equilibrium Points Of the Ah3bpmentioning

confidence: 87%

“…Nevertheless, there exist periodic orbits, specially on the Planar and Vertical families, which spend part of their orbital period on the day side of the asteroid, and are interesting for an observational mission [FJM14]. Similar behaviour has been observed in the terminator and quasi-terminator orbits [BLG13,BLG14]. For a solar sail perpendicular to the SRP (α = δ = 0), the Planar and Vertical Lyapunov orbits that are at the end of the family (by end we refer to those orbits with a larger energy level) spend more than half of their orbital period on the day side of the asteroid [FJM14].…”

Section: A Note On Possible Mission Applicationsmentioning

confidence: 91%

“…We call the normalised sail lightness numberβ = β(µ sb ω 4 ) −1/3 . Following [BLG14], we have thatβ = K 1 (A/m)µ −1/3 sb , where K 1 ≈ 7.8502 when A is given in m 2 and m in kg. Notice thatβ depends on both: the area-to-mass ratio of the satellite (σ = (A/m)) and the gravitational parameter of the small body (µ sb ).…”

Section: The Ah3bp Model For a Non-perfectly Reflecting Solar Sailmentioning

confidence: 99%

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Numerical study of the geometry of the phase space of the Augmented Hill Three-Body problem

Farrés

Jorba

Mondelo

2017

Celest Mech Dyn Astr

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The Augmented Hill Three-Body problem is an extension of the classical Hill problem that, among other applications, has been used to model the motion of a solar sail around an asteroid. This model is a 3 degrees of freedom (3DoF) Hamiltonian system that depends on four parameters. This paper describes the bounded motions (periodic orbits and invariant tori) in an extended neighbourhood of some of the equilibrium points of the model. An interesting feature is the existence of equilibrium points with a 1:1 resonance, whose neighbourhood we also describe. The main tools used are the computation of periodic orbits (including their stability and bifurcations), the reduction of the Hamiltonian to centre manifolds at equilibria, and the numerical approximation of invariant tori. It is remarkable how the combination of these techniques allows the description of the dynamics of a 3DoF Hamiltonian system.

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Section: Equilibrium Points Of the Ah3bpmentioning

confidence: 87%

Section: A Note On Possible Mission Applicationsmentioning

confidence: 91%

Section: The Ah3bp Model For a Non-perfectly Reflecting Solar Sailmentioning

confidence: 99%

See 1 more Smart Citation

Numerical study of the geometry of the phase space of the Augmented Hill Three-Body problem

Farrés

Jorba

Mondelo

2017

Celest Mech Dyn Astr

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“…Associated quasi-terminator orbits (Broschart, Lantoine et al 2013) have been studied to circumvent this problem. Nevertheless, their coverage of the asteroid close to the sub-solar point is still far from optimal.…”

Section: Discussion and Model Limitationsmentioning

confidence: 99%

On the $$a$$ a and $$g$$ g families of orbits in the Hill problem with solar radiation pressure and their application to asteroid orbiters

Yárnoz

Scheeres

McInnes

2015

Celest Mech Dyn Astr

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. (2015) On the a and g families of orbits in the Hill problem with solar radiation pressure and their application to asteroid orbiters. Celestial Mechanics and Dynamical Astronomy, 121(4) ABSTRACTThe focus of this paper is on the exploration of the a and g-g' families of planar symmetric periodic orbits around minor bodies under the effect of solar radiation pressure. An extended Hill problem with solar radiation pressure (SRP) allows the study of spacecraft trajectories in the vicinity of asteroids orbiting the Sun. The evolution of the a and g-g' families is presented with SRP increasing from the classical Hill problem to levels characteristic of current and future planned missions to minor bodies, as well as one extreme case with very large SRP for a small asteroid. In addition, the implications of considering a spherical body are analysed, in terms of trajectories colliding with the asteroid and eclipses, which limits the feasibility of various family branches. Finally, the influence of SRP on the linear stability of feasible orbits is calculated.

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“…After the initial characterization via flybys, the spacecraft is inserted into a nominally stable orbit located in the terminator plane (polar plane normal to the sun direction) [38][39][40]. This orbit will also be used, later, by the human spacecraft.…”

Section: Gravity Field Characterizationmentioning

confidence: 99%