Fuel optimization for low-thrust Earth–Moon transfer via indirect optimal control

Pérez-Palau, Daniel; Epenoy, Richard

doi:10.1007/s10569-017-9808-2

Cited by 27 publications

(4 citation statements)

References 30 publications

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“…Substituting into Eq. (19) gives the time-optimal thrust pointing direction In the initial guess stage, guided by higher mission objectives (e.g., close-range observation, collision avoidance), BCG plans nominal impulsive maneuvers of different types (single burn, multiple burn based on manifold patching) by leveraging the invariant manifolds of CR3BP. With the initial guess, the spacecraft performs transfer maneuvers according to the selected orbits' types (state-to-state, orbital element-tostate, state-to-orbital element).…”

Section: A Bilinear Tangent Guidancementioning

confidence: 99%

Constant-Thrust Orbital Transfer About Binary Asteroids Using Bilinear Tangent Guidance

Xiong,

Wang

2024

IEEE Trans. Aerosp. Electron. Syst.

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By applying the bilinear tangent (BLT) guidance law, a near-optimal and computationally efficient BLT constant-thrust guidance (BCG) algorithm is introduced for orbital transfers about a binary asteroid system. This algorithm is accomplished by using BLT guidance law combined with Newton-Raphson predictor-corrector algorithm and manifold patching techniques. BCG can plan a variety of fuel efficient constant-thrust state/orbit to state/orbit transfers based on the types of the initial/target orbits and the selected maneuver types, including single burn transfers and multiple burn transfers leveraging manifolds.

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Section: A Bilinear Tangent Guidancementioning

confidence: 99%

Constant-Thrust Orbital Transfer About Binary Asteroids Using Bilinear Tangent Guidance

Xiong,

Wang

2024

IEEE Trans. Aerosp. Electron. Syst.

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“…By implementing the necessary condition of optimality based on the Pontryagin extremum principle, a wide range of Pareto solutions were obtained, many of which exploited high-altitude lunar fly-by to reduce fuel consumption. Pérez-Palau et al [161] studied the design of minimum fuel lowthrust trajectories from an LEO to a lunar orbit with the BCM model. In their study, two methods were proposed to overcome the numerical difficulties that arose from the huge sensitivity of the state and costate equations.…”

Section: Figure 15: Optimal Design Approaches Of Low-thrust Trajectorymentioning

confidence: 99%

Overview of Earth-Moon Transfer Trajectory Modeling and Design

Zhang¹,

Yu²,

Dai³

2023

Computer Modeling in Engineering &Amp; Sciences

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The Moon is the only celestial body that human beings have visited. The design of the Earth-Moon transfer orbits is a critical issue in lunar exploration missions. In the 21st century, new lunar missions including the construction of the lunar space station, the permanent lunar base, and the Earth-Moon transportation network have been proposed, requiring low-cost, expansive launch windows and a fixed arrival epoch for any launch date within the launch window. The low-energy and low-thrust transfers are promising strategies to satisfy the demands. This review provides a detailed landscape of Earth-Moon transfer trajectory design processes, from the traditional patched conic to the state-of-the-art low-energy and low-thrust methods. Essential mechanisms of the various utilized dynamic models and the characteristics of the different design methods are discussed in hopes of helping readers grasp the basic overview of the current Earth-Moon transfer orbit design methods and a deep academic background is unnecessary for the context understanding.

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“…The transcription method was used in conjunction with modified equinoctial elements (MEE), to retrieve the minimum-fuel path from an initial Ariane 5 elliptic Earth parking orbit to a final elliptic polar lunar orbit with periapse above the lunar south pole. Most recently, Pérez-Palau and Epenoy [18] developed an indirect optimal control approach for minimum-fuel trajectories from LEO to different lunar orbits in the Sun-Earth-Moon bicircular restricted four-body problem. Other effective strategies for the preliminary analysis of minimum-fuel Earth-Moon orbit transfers were proposed by Mingotti, Topputo, and Bernelli-Zazzera [19,20], by Zhang, Topputo, Bernelli-Zazzera, and Zhao [21], and by Ozimek and Howell [22], leveraging lowthrust in conjunction with invariant manifolds [23], in the framework of the CR3BP.…”

Section: Introductionmentioning

confidence: 99%

Multiple-arc optimization of low-thrust Earth–Moon orbit transfers leveraging implicit costate transformation

Beolchi,

Pontani,

Pozzi

et al. 2024

Acta Astronautica

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Fuel optimization for low-thrust Earth–Moon transfer via indirect optimal control

Cited by 27 publications

References 30 publications

Constant-Thrust Orbital Transfer About Binary Asteroids Using Bilinear Tangent Guidance

Constant-Thrust Orbital Transfer About Binary Asteroids Using Bilinear Tangent Guidance

Overview of Earth-Moon Transfer Trajectory Modeling and Design

Multiple-arc optimization of low-thrust Earth–Moon orbit transfers leveraging implicit costate transformation

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