A preliminary design procedure for an ion-beam shepherd mission

Urrutxua, Hodei; Bombardelli, Claudio; Hedo, J. M.

doi:10.1016/j.ast.2019.03.038

Cited by 25 publications

(5 citation statements)

References 21 publications

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“…To implement the IBS concept, it is necessary to have an efficient technique to determine the force that transmits the ion thruster (IT) to the SDO because these values are required for mission planning [6] and relative control tasks [7]. The task of ion beam force determination has been addressed in several papers.…”

Section: Research and Engineering Innovation Projects Of The National...mentioning

confidence: 99%

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Convolutional Neural Networks for Determining the Ion Beam Impact on a Space Debris Object

REDKA,

KHOROSHYLOV

2023

Sci. innov.

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Introduction. Space debris is a serious problem that significantly complicates space activity. This problem can be mitigated by active space debris removal. The ion beam shepherd (IBS) concept assumes the contactless removal of a space debris object (SDO) by the plume of an ion thruster (IT). Techniques for determining the force impact from the IT to the SDO are of crucial importance for implementing the IBS concept.Problem Statement. A launcher’s upper stage, approximated by a cylinder, is considered an SDO deorbited by the plume of the IT. The SDO can change its orientation and position relative to the shepherd satellite. The shepherd satellite shall be able to determine the force transmitted to the SDO by the IT, using only SDO’s images as the input information.Purpose. The study aims to develop a neural net model that can map an SDO image to the force transmitted by an IT plume to this object and estimate the accuracy of such models.Material and Methods. Plasma physics methods are used to obtain ground truth values of the ion beam force. The deep learning methodology is applied to create neural net models.Results. Three different approaches for end-to-end ion force determination have been investigated. The first model uses a single convolutional neural net (CNN). The second model is an ensemble network consisting of four sub-models, and a classifier is used to pick the correct sub-model. The last model is similar to the first one but is trained on all images used for the second model. After training, all three models’ accuracy and computational complexity are estimated. These estimates demonstrate the acceptable performance of CNN-based models.Conclusions. This paper demonstrates that CNNs can be used to determine the force impact without knowledge about the SDO position and orientation and significantly faster than the previous methods.

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Section: Research and Engineering Innovation Projects Of The National...mentioning

confidence: 99%

“…Neglecting the effects of plasma ions leaving the target surface, sputtering of its material, and electron pressure, the elementary force transmitted to the elementary area ds of the SDO's surface can be calculated as follows [6]:…”

Section: Ground Truth Forcementioning

confidence: 99%

Convolutional Neural Networks for Determining the Ion Beam Impact on a Space Debris Object

REDKA,

KHOROSHYLOV

2023

Sci. innov.

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“…The gravitational tractor (GT) involves placing a sufficiently large mass in heliocentric orbit near the PHA to perturb its motion enough to change the trajectory and increase the MOID [10,25]. A second possibility is offered by the use of technologies based on ionic propulsion (ion-beam shepherd); this choice greatly simplifies mission design, but requires a particularly long time horizon for significant changes in the orbit of the asteroid [26,27]. The last and more complex technique is based on artificially induced modification of the albedo coefficient to exploit the Yarkovsky effect [28] to change the trajectory of the asteroid [29]; even in this case, the time horizon must be particularly long to have significant variations in the MOID.…”

Section: Introductionmentioning

confidence: 99%

Mitigation of the Collision Risk of a Virtual Impactor Based on the 2011 AG5 Asteroid Using a Kinetic Impactor

Cinelli

2024

Mathematics

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In recent years, the escalating risk of natural disasters caused by Near-Earth Objects (NEOs) has garnered heightened scrutiny, particularly in the aftermath of the 2013 Chelyabinsk event. This has prompted increased interest from governmental and supranational entities, leading to the formulation of various measures and strategies aimed at mitigating the potential threat posed by NEOs. This paper delves into the analysis of the 2011 AG5 asteroid within the context of small celestial bodies (e.g., asteroids, comets, or meteoroids) exhibiting resonant orbits with Earth’s heliocentric revolution. Initial observations in 2011 raised alarms regarding the asteroid’s orbital parameters, indicating a significant risk of Earth impact during its resonant encounter in 2040. Subsequent observations, however, mitigated these concerns. Here, we manipulate the orbital elements of the 2011 AG5 asteroid to simulate its behavior as a virtual impactor (a virtual asteroid whose orbit could impact Earth). This modification facilitates the assessment of impact mitigation resulting from a deflection maneuver utilizing a kinetic impactor. The deflection maneuver, characterized as an impulsive change in the asteroid’s momentum, is executed during a resonant encounter occurring approximately two decades before the potential impact date. The paper systematically evaluates the dependence of the deflection maneuver’s efficacy on critical parameters, including the position along the orbit, epoch, and momentum enhancement factor.

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“…However, most malfunctioning and endof-life satellites are non-cooperative targets that cannot provide useful information actively [8,9]. Moreover, they are usually rotating, or tumbling, because of residual angular momentum, energy dissipation, and factors such as the gravity gradient and eddy-current damping [10][11][12]. All these factors make it difficult to capture such debris [6,13].…”

Section: Introductionmentioning

confidence: 99%

Dynamic analysis of detumbling a rotating satellite using flexible deceleration rod

2022

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Malfunctioning satellites are generally non-cooperative tumbling objects. Due to their complex tumbling motion, it is essential to stabilize the target within an acceptable rotating range in the pre-capture phase. In contrast to contactless methods, contact methods based on flexible devices are efficient and can generate sufficient operating torque through flexible contact. However, accurate dynamic analysis of the operation is challenging because of two limitations. It is difficult to obtain a high-efficiency description of the large deformation arising from the operating process. Moreover, the contact between a flexible device and a tumbling object is hard to detect efficiently. This paper proposes a method for detumbling a free-floating rotating satellite; it uses a flexible rod to contact the solar array of the target. The absolute nodal coordinate formulation is first applied to a rod-contact detumbling model in simulation to describe the large deformation of the rod precisely with a low computational burden. Next, a two-step method to detect the contact is employed to pinpoint the contact point and speed up the simulation: coarse detection in the contactless phase and fine detection in the contact phase. Finally, the feasibility of the contact detumbling method is verified. In addition, through the further analysis of the contact process, some characteristics of this kind of strategy are studied for the first time.

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A preliminary design procedure for an ion-beam shepherd mission

Cited by 25 publications

References 21 publications

Convolutional Neural Networks for Determining the Ion Beam Impact on a Space Debris Object

Convolutional Neural Networks for Determining the Ion Beam Impact on a Space Debris Object

Mitigation of the Collision Risk of a Virtual Impactor Based on the 2011 AG5 Asteroid Using a Kinetic Impactor

Dynamic analysis of detumbling a rotating satellite using flexible deceleration rod

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