Optimal Control for Halo Orbit Missions

Serban, Radu; Koon, Wang Sang; Lo, Martin W.; Marsden, Jerrold E.; Petzold, Linda R.; Ross, Shane D.; Wilson, Robyn

doi:10.1016/s1474-6670(17)35539-8

Cited by 3 publications

(3 citation statements)

References 2 publications

(1 reference statement)

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“…This section describes some results of Serban et al [2000] in the larger context of the present paper. Genesis is a solar wind sample return mission.…”

Section: Optimal Control For Halo Orbit Missionsmentioning

confidence: 99%

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Dynamical Systems, the Three-Body Problem and Space Mission Design

Koon¹,

Lo²,

Marsden³

et al. 2000

Equadiff 99

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407

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This paper concerns heteroclinic connections and resonance transitions in the planar circular restricted 3-body problem, with applications to the dynamics of comets and asteroids and the design of space missions such as the Genesis Discovery Mission and low energy Earth to Moon transfers. The existence of a heteroclinic connection between pairs of equal energy periodic orbits around two of the libration points is shown numerically. This is applied to resonance transition and the construction of orbits with prescribed itineraries. Invariant manifold structures are relevant for transport between the interior and exterior Hill's regions, and other resonant phenomena throughout the solar system.

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“…This section describes some results of Serban et al [2000] in the larger context of the present paper. Genesis is a solar wind sample return mission.…”

Section: Optimal Control For Halo Orbit Missionsmentioning

confidence: 99%

“…In this paper, we will discuss only briefly the HOI technique. For more details, see Serban et al [2000].…”

Section: Optimal Control For Halo Orbit Missionsmentioning

confidence: 99%

Dynamical Systems, the Three-Body Problem and Space Mission Design

Koon¹,

Lo²,

Marsden³

et al. 2000

Equadiff 99

Self Cite

251

407

View full text Add to dashboard Cite

show abstract

“…When a nonlinear system is linearized, it is possible to control the dynamics with a linear feedback controller, given a quadratic cost function. There are various works describing the linear quadratic regulator theory and applications ( [14][15][16][17]).…”

Section: Introductionmentioning

confidence: 99%

Stationkeeping controllers for Earth–Moon L1 and L2 libration points halo orbits

Marsola

Fernandes

Balthazar

2021

J Braz. Soc. Mech. Sci. Eng.

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This paper considers the dynamics of the circular restricted three-body problem (CRTBP) for the Earth-Moon system designing stationkeeping controllers at periodic orbits. Taking into account the L 1 and L 2 equilibrium points in this dynamics, it is constructed a family of periodic orbits in the vicinity of these libration points, called halo orbits. The orbits are constructed using an analytical approach as a first guess with a numerical method in addition, in order to correct the linear approximation procedure. Withal the stability of these libration points, trajectories are analyzed and proved to be unstable; a spacecraft moving near these points must use some correction maneuver to remain close to the nominal orbit. Two types of controllers are proposed for stationkeeping maneuvers performed by low-thrust power-limited propulsion system . The first controller is based on the linear quadratic regulator (LQR) and the second one is based on the nonlinear feedback control which uses the state-dependent Riccati equation control (SDRE). Finally, a parameters comparison analysis is performed taking into account different values of the weight matrices for both controllers at both halo orbits.

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