On target for Venus — set oriented computation of energy efficient low thrust trajectories

Dellnitz, Michael; Junge, Oliver; Post, Marcus; Thiere, Bianca

doi:10.1007/978-1-4020-5325-2_21

Cited by 13 publications

(24 citation statements)

References 11 publications

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“…However, in order to build first guess solutions, the profile of T over time is prescribed at this stage. In particular, using tangential thrust, attainable sets can be defined in the same fashion as reachable sets are defined by Dellnitz et al [4].…”

Section: Attainable Sets and Low-thrust Propulsionmentioning

confidence: 99%

Transfers to distant periodic orbits around the Moon via their invariant manifolds

2012

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a b s t r a c tThis paper presents two ways to transfer a spacecraft to distant periodic orbits in the Earth-Moon system. These unstable periodic orbits of the restricted three-body problem reveal a rich phase-portrait structure that can be used by space missions. Through the perspective of dynamical system theory, distant periodic orbits' invariant manifolds can be exploited to design novel low-energy trajectories in the Earth-Moon framework. Interior and exterior transfers are presented. The latter use impulsive, highthrust propulsion to target the stable manifold from the exterior. Interior transfers are instead formulated with continuous, low-thrust propulsion. The attainable sets are used in both cases to handle families of either coast arcs or low-thrust orbits. First guess solutions are optimized in the framework of the Sun-Earth-Moon-Spacecraft restricted four-body problem through direct transcription and multiple shooting. The novelty of the presented solutions, as well as their efficiency, is demonstrated through examples.

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Section: Attainable Sets and Low-thrust Propulsionmentioning

confidence: 99%

Transfers to distant periodic orbits around the Moon via their invariant manifolds

2012

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“…Intrinsically associated with low thrust, however, is the extended arc between the manifolds during which the thrust must be provided. There are several similar attempts in literature with different approaches both for interplanetary transfers, with various target planets, (Dellnitz et al 2006) and for Earth-Moon transfers (Perozzi and Di Salvo 2008). The overall general idea is, however, to link ballistic phases with an optimized low thrust propelled phase.…”

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confidence: 97%

Earth–Mars halo to halo low thrust manifold transfers

Pergola

Geurts

Casaregola

et al. 2009

Celest Mech Dyn Astr

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Application of low thrust propulsion to interconnect ballistic trajectories on invariant manifolds associated with multiple circular restricted three body systems has been investigated. Sun-planet three body models have been coupled to compute the two ballistic trajectories, where electric propulsion is used to interconnect these trajectories as no direct intersection in the Poincarè sections exists. The ability of a low thrust to provide the energy change required to transit the spacecraft between two systems has been assessed for some Earth to Mars transfers. The approach followed consists in a planetary escape on the unstable manifold starting from a periodic orbit around one of the two collinear libration points near the secondary body. Following the planetary escape and the subsequent coasting phase, the electric thruster is activated and executes an ad-hoc thrusting phase. The complete transfer design, composed of the three discussed phases, and possible applications to Earth-Mars missions is developed where the results are outlined in this paper.

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“…The term v + r ⊥ is the velocity expressed in the heliocentric inertial frame [22]. It is worth mentioning that the assigned guidance law in Eq.…”

Section: Definition Of Attainable Setsmentioning

confidence: 99%

“…(11) is not given like in [22,23], but rather in this approach it represents an unknown that is found by solving an optimal control problem (t i , t f are the initial, final times, respectively). T is determined in such a way that a certain state is targeted and a certain objective function is minimized at the same time.…”

Section: The Controlled Planar Circular Restricted Three-body Problemmentioning

confidence: 99%

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Earth–Mars transfers with ballistic escape and low-thrust capture

Mingotti

Topputo

Bernelli‐Zazzera

2011

Celest Mech Dyn Astr

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In this paper novel Earth-Mars transfers are presented. These transfers exploit the natural dynamics of n-body models as well as the high specific impulse typical of low-thrust systems. The Moon-perturbed version of the Sun-Earth problem is introduced to design ballistic escape orbits performing lunar gravity assists. The ballistic capture is designed in the Sun-Mars system where special attainable sets are defined and used to handle the low-thrust control. The complete trajectory is optimized in the full n-body problem which takes into account planets' orbital inclinations and eccentricities. Accurate, efficient solutions with reasonable flight times are presented and compared with known results.

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On target for Venus — set oriented computation of energy efficient low thrust trajectories

Cited by 13 publications

References 11 publications

Transfers to distant periodic orbits around the Moon via their invariant manifolds

Transfers to distant periodic orbits around the Moon via their invariant manifolds

Earth–Mars halo to halo low thrust manifold transfers

Earth–Mars transfers with ballistic escape and low-thrust capture

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