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Aerospace
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Advances in Asteroid Dynamics
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Advances in Asteroid Dynamics

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Astronautics & Space Science".

Deadline for manuscript submissions: 31 December 2024 | Viewed by 868

Special Issue Editors

Dr. Marta Ceccaroni

E-Mail Website
Guest Editor
Centre for Autonomous and Cyberphysical Systems, Cranfield University, Cranfield, UK
Interests: asteroid orbit determination; potentially hazardous asteroids; distant retrograde orbits; low-energy transfers; computer vision; logic and automated reasoning
Dr. Marco Fenucci

E-Mail Website
Guest Editor
ESRIN—ESA Centre for Earth Observation, Frascati, Italy
Interests: near-Earth asteroids; planetary science; astronomy and mathematics

Special Issue Information

Dear Colleagues，

Asteroid dynamics is a critical field within planetary sciences, focusing on the complex gravitational interactions, orbital behaviors, and physical properties of asteroids. These celestial bodies, remnants from the early solar system, allow us to understand planetary formation and evolution. The precise computation and propagation of an asteroid orbit is essential, not only for scientific purpose, but also for planetary protection. 

Recent advances in asteroid dynamics have been propelled by improvements in observational technology, computational methods, and theoretical models. These developments have provided deeper insights into the mechanisms that govern asteroid behavior, significantly enhancing our ability to predict asteroid trajectories, understand their physical characteristics, and assess potential risks to Earth.

The continued progress in the field of asteroid dynamics has opened new frontiers in space exploration and planetary science, such as the testing of new technologies and strategies for asteroid deflection and resource utilization, such as NASA's DART mission, which demonstrated our ability to change an asteroid's trajectory through kinetic impact.

Dr. Marta Ceccaroni
Dr. Marco Fenucci
Guest Editors

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • asteroid dynamics
  • orbit determination
  • space exploration

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Published Papers (1 paper)

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Research

25 pages, 2274 KiB  
Article
Assessment of Flyby Methods as Applied to Close Encounters among Asteroids
by Nicolò Stronati, Marco Fenucci, Marco Micheli and Marta Ceccaroni
Aerospace 2024, 11(8), 647; https://doi.org/10.3390/aerospace11080647 - 9 Aug 2024
Viewed by 651
Abstract
Orbital flybys have been extensively studied for spacecraft missions, resulting in effective mathematical and physical models. However, these models’ applicability to natural encounters involving asteroids has not been explored. This paper examines the applicability of two such theories, patched conics (PC) and the [...] Read more.
Orbital flybys have been extensively studied for spacecraft missions, resulting in effective mathematical and physical models. However, these models’ applicability to natural encounters involving asteroids has not been explored. This paper examines the applicability of two such theories, patched conics (PC) and the Keplerian map (KM), to asteroid encounters. A review of the two methods will be provided, highlighting their assumptions and range of applicability. Simulations of asteroid–asteroid encounters will then be performed to evaluate their effectiveness in these scenarios. The simulation parameters are set by collecting data on actual asteroid–asteroid encounters, hereby presented, generally characterised by high close approach distances and small masses of the perturbing bodies, if compared to those used to build the flyby theories. Results show that the PC theory’s effectiveness diminishes with increasing approach distances, aligning with its assumptions. Moreover, the prediction of the model is better in the geometric configurations where the flyby has major effects on the orbital energy change. The KM theory has shown good effectiveness for encounters occurring outside the sphere of influence of the perturbing body, even for very high distances. This research investigates flyby models’ strengths and weaknesses in asteroid encounters, offering practical insights and future directions. Full article
(This article belongs to the Special Issue Advances in Asteroid Dynamics)
►▼ Show Figures

Figure 1

Figure 1
<p>Bar chart of the absolute frequency of the encounter distances with respect to the perturbing body’s Hill’s radius. The plot includes only the encounters between 1 and 200 <math display="inline"><semantics> <msub> <mi>R</mi> <mi>H</mi> </msub> </semantics></math>. The bins for the bar chart have a uniform span of 2 <math display="inline"><semantics> <mrow> <msub> <mi>r</mi> <mi>P</mi> </msub> <mo>/</mo> <msub> <mi>R</mi> <mi>H</mi> </msub> </mrow> </semantics></math>.</p> Full article ">Figure 2
<p>Relationship between the <math display="inline"><semantics> <mrow> <mo>Δ</mo> <mrow> <mo>(</mo> <mi>res</mi> <mo>)</mo> </mrow> </mrow> </semantics></math> of the detected single encounters and the encounter distance, relative to the Hill’s radius, <math display="inline"><semantics> <msub> <mi>R</mi> <mi>H</mi> </msub> </semantics></math>.</p> Full article ">Figure 3
<p>Representation of the relative inclination between two different orbits. <math display="inline"><semantics> <msub> <mi>i</mi> <mrow> <mi>r</mi> <mi>e</mi> <mi>l</mi> </mrow> </msub> </semantics></math> is the inclination that one orbit has with respect to the perifocal plane of the other object, so this was taken as the new reference frame instead of the ecliptic.</p> Full article ">Figure 4
<p>Relationship between the relative inclination, <math display="inline"><semantics> <msub> <mi>i</mi> <mrow> <mi>r</mi> <mi>e</mi> <mi>l</mi> </mrow> </msub> </semantics></math>, and the normalised relative velocity, <span class="html-italic">U</span>.</p> Full article ">Figure 5
<p>Relationship between the relative velocity and the encounter distance, compared with the escape velocity, <math display="inline"><semantics> <mrow> <msub> <mi>v</mi> <mi>E</mi> </msub> <mo>/</mo> <msqrt> <mi>μ</mi> </msqrt> </mrow> </semantics></math> (red line). The <span class="html-italic">y</span>-axis is in logarithmic scale.</p> Full article ">Figure 6
<p>Geometric representation of the planetocentric frame.</p> Full article ">Figure 7
<p><math display="inline"><semantics> <mi>α</mi> </semantics></math> and <math display="inline"><semantics> <mi>β</mi> </semantics></math> angles for the analysed encounters.</p> Full article ">Figure 8
<p><math display="inline"><semantics> <mi>γ</mi> </semantics></math> and <math display="inline"><semantics> <mi>β</mi> </semantics></math> angles for the analysed encounters.</p> Full article ">Figure 9
<p>Relationship between <math display="inline"><semantics> <mi>γ</mi> </semantics></math> and <math display="inline"><semantics> <msub> <mi>i</mi> <mrow> <mi>r</mi> <mi>e</mi> <mi>l</mi> </mrow> </msub> </semantics></math>.</p> Full article ">Figure 10
<p>Relationship between <math display="inline"><semantics> <mi>γ</mi> </semantics></math> and <span class="html-italic">U</span>.</p> Full article ">Figure 11
<p>Hyperbolic trajectory of the massless particle around the secondary during a flyby. <math display="inline"><semantics> <msub> <mi mathvariant="bold">V</mi> <mi>P</mi> </msub> </semantics></math> represents the velocity vector of the secondary, <math display="inline"><semantics> <msubsup> <mi mathvariant="bold">v</mi> <mo>∞</mo> <mo>+</mo> </msubsup> </semantics></math> and <math display="inline"><semantics> <msubsup> <mi mathvariant="bold">v</mi> <mo>∞</mo> <mo>−</mo> </msubsup> </semantics></math> are, respectively, the velocities at the entry and exit points of the hyperbolic trajectory, and <math display="inline"><semantics> <mrow> <mn>2</mn> <mi>δ</mi> </mrow> </semantics></math> is the deflection angle between the two asymptotes of the hyperbola, caused by the flyby.</p> Full article ">Figure 12
<p>Representation of the relative velocity vector, <math display="inline"><semantics> <mi mathvariant="bold">U</mi> </semantics></math>, in the <math display="inline"><semantics> <mrow> <mi>X</mi> <mi>Y</mi> <mi>Z</mi> </mrow> </semantics></math> planetocentric frame. <math display="inline"><semantics> <mrow> <mi>ϑ</mi> <mo>∈</mo> <mo>[</mo> <mn>0</mn> <mo>,</mo> <mn>2</mn> <mi>π</mi> <mo>)</mo> </mrow> </semantics></math> is the angle between the <span class="html-italic">Y</span>-axis and <math display="inline"><semantics> <mi mathvariant="bold">U</mi> </semantics></math>, while <math display="inline"><semantics> <mrow> <mi>ϕ</mi> <mo>∈</mo> <mo>[</mo> <mn>0</mn> <mo>,</mo> <mi>π</mi> <mo>]</mo> </mrow> </semantics></math> is the angle between the <math display="inline"><semantics> <mrow> <mi>Y</mi> <mi>Z</mi> </mrow> </semantics></math> plane and the <math display="inline"><semantics> <mrow> <mi>Y</mi> <mi>U</mi> </mrow> </semantics></math> plane.</p> Full article ">Figure 13
<p>Representation of the synodic reference frame.</p> Full article ">Figure 14
<p>Relative error of the <math display="inline"><semantics> <mrow> <mo>Δ</mo> <msub> <mi>E</mi> <mrow> <mi>P</mi> <mi>C</mi> </mrow> </msub> </mrow> </semantics></math> with respect to <math display="inline"><semantics> <mrow> <mo>Δ</mo> <msub> <mi>E</mi> <mrow> <mi>G</mi> <mi>V</mi> <mi>E</mi> </mrow> </msub> </mrow> </semantics></math> at different <math display="inline"><semantics> <mrow> <msub> <mi>r</mi> <mi>P</mi> </msub> <mo>/</mo> <msub> <mi>R</mi> <mi>H</mi> </msub> </mrow> </semantics></math> and <math display="inline"><semantics> <mrow> <mi>β</mi> <mo>=</mo> <mn>77</mn> <mo> </mo> <mi>deg</mi> </mrow> </semantics></math>. The values above <math display="inline"><semantics> <mrow> <mn>0.6</mn> </mrow> </semantics></math> are blanked out in the heatmap for a better visualisation.</p> Full article ">Figure 15
<p>Relative error of the <math display="inline"><semantics> <mrow> <mo>Δ</mo> <msub> <mi>E</mi> <mrow> <mi>P</mi> <mi>C</mi> </mrow> </msub> </mrow> </semantics></math> with respect to <math display="inline"><semantics> <mrow> <mo>Δ</mo> <msub> <mi>E</mi> <mrow> <mi>G</mi> <mi>V</mi> <mi>E</mi> </mrow> </msub> </mrow> </semantics></math> at different <math display="inline"><semantics> <mrow> <msub> <mi>r</mi> <mi>P</mi> </msub> <mo>/</mo> <msub> <mi>R</mi> <mi>H</mi> </msub> </mrow> </semantics></math> and <math display="inline"><semantics> <mrow> <mi>β</mi> <mo>=</mo> <mn>0</mn> <mo> </mo> <mi>deg</mi> </mrow> </semantics></math>. The values above <math display="inline"><semantics> <mrow> <mn>0.6</mn> </mrow> </semantics></math> are blanked out in the heatmap for a better visualisation.</p> Full article ">Figure 16
<p><math display="inline"><semantics> <mrow> <mo>Δ</mo> <msub> <mi>E</mi> <mrow> <mi>P</mi> <mi>C</mi> </mrow> </msub> </mrow> </semantics></math> for <math display="inline"><semantics> <mrow> <mi>β</mi> <mo>=</mo> <mn>77</mn> <mo> </mo> <mi>deg</mi> </mrow> </semantics></math>. According to Equation (<a href="#FD12-aerospace-11-00647" class="html-disp-formula">12</a>), there is no effect of parameter <math display="inline"><semantics> <mi>γ</mi> </semantics></math>.</p> Full article ">Figure 17
<p><math display="inline"><semantics> <mrow> <mo>Δ</mo> <msub> <mi>E</mi> <mrow> <mi>G</mi> <mi>V</mi> <mi>E</mi> </mrow> </msub> </mrow> </semantics></math> for <math display="inline"><semantics> <mrow> <mi>β</mi> <mo>=</mo> <mn>77</mn> <mo> </mo> <mi>deg</mi> </mrow> </semantics></math>.</p> Full article ">Figure 18
<p>Relative error of the <math display="inline"><semantics> <mrow> <mo>Δ</mo> <msub> <mi>E</mi> <mrow> <mi>K</mi> <mi>M</mi> </mrow> </msub> </mrow> </semantics></math> with respect to <math display="inline"><semantics> <mrow> <mo>Δ</mo> <msub> <mi>E</mi> <mrow> <mi>G</mi> <mi>V</mi> <mi>E</mi> </mrow> </msub> </mrow> </semantics></math> at different <math display="inline"><semantics> <mrow> <msub> <mi>r</mi> <mi>P</mi> </msub> <mo>/</mo> <msub> <mi>R</mi> <mi>H</mi> </msub> </mrow> </semantics></math> and <math display="inline"><semantics> <mrow> <mi>β</mi> <mo>=</mo> <mn>77</mn> <mo> </mo> <mi>deg</mi> </mrow> </semantics></math>. The values above <math display="inline"><semantics> <mrow> <mn>0.6</mn> </mrow> </semantics></math> are blanked out in the heatmap for a better visualisation.</p> Full article ">Figure 19
<p>Relative error of the <math display="inline"><semantics> <mrow> <mo>Δ</mo> <msub> <mi>E</mi> <mrow> <mi>K</mi> <mi>M</mi> </mrow> </msub> </mrow> </semantics></math> with respect to <math display="inline"><semantics> <mrow> <mo>Δ</mo> <msub> <mi>E</mi> <mrow> <mi>G</mi> <mi>V</mi> <mi>E</mi> </mrow> </msub> </mrow> </semantics></math> at different <math display="inline"><semantics> <mrow> <msub> <mi>r</mi> <mi>P</mi> </msub> <mo>/</mo> <msub> <mi>R</mi> <mi>H</mi> </msub> </mrow> </semantics></math> and <math display="inline"><semantics> <mrow> <mi>β</mi> <mo>=</mo> <mn>0</mn> <mo> </mo> <mi>deg</mi> </mrow> </semantics></math>. The values above <math display="inline"><semantics> <mrow> <mn>0.6</mn> </mrow> </semantics></math> are blanked out in the heatmap for a better visualisation.</p> Full article ">
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