Transfer between the planar Lyapunov orbits around the Earth–Moon L2 point using low-thrust engine

Du, Chongrui; Starinova, Olga; Liu, Ya

doi:10.1016/j.actaastro.2022.09.056

Cited by 15 publications

(3 citation statements)

References 39 publications

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“…Other approaches use classical optimal control theory [28] or artificial intelligence nonlinear optimizers [29], these can be efficient, however in space, the largest parts of the manoeuvres are open-loop, the shape trajectory is rarely predictable and the computation might be very energy consuming due to non-linearities, perturbations and other model approximations. These statements are also confirmed by [30] and [31] where the problem of fuel-optimal Earth-Moon and orbit-to-orbit transfer with low thrust engines is computed only in the planar problem and with many constraints because of the high sensitivity of the problem. An interesting methodology for orbit-to-orbit transfer is described in [32], where a multi-impulsive optimal algorithm is presented, based on the knowl-…”

Section: J O U R N a L P R E -P R O O Fmentioning

confidence: 54%

Optimal Time-Fixed Impulsive Non-Keplerian Orbit to Orbit Transfer Algorithm Based on Primer Vector Theory

Bucchioni¹,

Lombardi²,

Bellome

et al. 2023

Preprint

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Section: J O U R N a L P R E -P R O O Fmentioning

confidence: 54%

Optimal Time-Fixed Impulsive Non-Keplerian Orbit to Orbit Transfer Algorithm Based on Primer Vector Theory

Bucchioni¹,

Lombardi²,

Bellome

et al. 2023

Preprint

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“…Other approaches use classical optimal control theory [26] or artificial intelligence nonlinear optimizers [27], these can be efficient, however in space, the largest parts of the manoeuvres are open-loop, the shape trajectory is rarely predictable and the computation might be very energy consuming due to nonlinearities, perturbations and other model approximations. These statements are also confirmed by [28] and [29] where the problem of fuel-optimal Earth-Moon and orbit-to-orbit transfer with low thrust engines is computed only in the planar problem and with many constraints because of the high sensitivity of the problem. An interesting methodology for orbit-to-orbit transfer is described in [30], where a multi-impulsive optimal algorithm is presented, based on the knowledge of the Floquet modes and the natural stable dynamics of the system.…”

Section: Introductionmentioning

confidence: 54%

Optimal Time-Fixed Impulsive non-Keplerian Orbit to Orbit Transfer

Bucchioni

Lombardi

Bellome

et al. 2022

Preprint

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The work proposes a systematic method to compute an optimal transfer trajectory between two non-Keplerian halo orbits in the Circular Restricted Three body formulation of the Earth-Moon dynamics. The paper exploits the knowledge of the natural non-linear dynamics and the primer vector theory applied to the Circular Restricted Three Body Problem to design optimal Halo-to-Halo transfers with fixed and limited, compared with the rest of the literature, Time of flight, from every point of the departure orbit to every point of the arrival orbit. With the goal

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“…This method only can produce millinewtons of control force, resulting in unfeasibly long detumbling times (several days). The Hall effect thruster is a common type of high-specific impulse engine that can generate a high-speed plasma plume, effectively eliminating the problems of high fuel consumption and long operating time [15,16]. Due to the advantages of reliability and energy efficiency, this kind of thruster is very promising for detumbling missions.…”

Section: Introductionmentioning

confidence: 99%

Optimal detumbling guidance and control of plasma plume for tumbling spacecraft

Zhao,

Dai

2024

Nonlinear Dyn

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Detumbling is a crucial first step for on-orbit service and space debris removal. Recently, plume has become an efficient medium for detumbling failed spacecraft, which can avoid direct contact to improve operation safety. However, the traditional molecular plume may lead to an unaffordable fuel consumption, so it is necessary to propose a novel strategy to solve this problem. The Hall effect thruster is a common high specific impulse engine, which can generate high-speed plasma plume for contactless detumbling. The traditional plume models present difficulties for practical implementation due to the contradiction between the requirement of real-time computation and the limited computing capability of the spaceborne computer. To address the challenge of calculating the impact force, a fully analytical plasma plume model is proposed to substantially enhance the computing efficiency without loss of accuracy. A guidance law for optimal detumbling is proposed to mitigate the spin angular velocity while stabilizing nutation under multiple complex constraints. To facilitate the development of the detumbling control, a terminal non-singular sliding mode controller based on the saturation function (TSM-sat) is proposed, which can converge in finite time and avoid the chattering phenomenon. The Numerical results indicate that the proposed plasma plume model can significantly improve the computing efficiency and the optimal guidance law can stabilize the target within a reasonable time.

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Transfer between the planar Lyapunov orbits around the Earth–Moon L2 point using low-thrust engine

Cited by 15 publications

References 39 publications

Optimal Time-Fixed Impulsive Non-Keplerian Orbit to Orbit Transfer Algorithm Based on Primer Vector Theory

Optimal Time-Fixed Impulsive Non-Keplerian Orbit to Orbit Transfer Algorithm Based on Primer Vector Theory

Optimal Time-Fixed Impulsive non-Keplerian Orbit to Orbit Transfer

Optimal detumbling guidance and control of plasma plume for tumbling spacecraft

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