Advances in Mechanics and Control II

A special issue of Symmetry (ISSN 2073-8994). This special issue belongs to the section "Computer".

Deadline for manuscript submissions: 31 May 2024 | Viewed by 3264

Special Issue Editors


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Guest Editor
Department of Mechanics and Control Processes, Academy of Engineering, Peoples’ Friendship University of Russia (RUDN University), 117198 Moscow, Russia
Interests: mathematic modelling; astrodynamics; system analysis; aerospace systems; space flight mechanics; satellite constellation; orbital dynamics; space debris; on-orbit servicing
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Guest Editor
Department of Mechanical Engineering, McGill University, Montreal, QC H3A 0C3, Canada
Interests: satellite dynamics and control; space robotics; dynamics of aerospace structures; active space debris removal using robots; dynamics of tethered space systems; spacecraft motion in the vicinity of asteroids; formation flying of satellites; space elevator
Special Issues, Collections and Topics in MDPI journals

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Guest Editor
Department of Aerospace Engineering, Universiti Putra Malaysia, Seri Kembangan, Selangor, Malaysia
Interests: aerospace engineering
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Co-Guest Editor
Department of Mechanics and Control Processes, Academy of Engineering, Peoples’ Friendship University of Russia (RUDN University), 117198 Moscow, Russia
Interests: on-orbit servicing; orbital transfers and spacecraft control; space flight mechanics; space systems design

Special Issue Information

Dear Colleagues,

The key factor for creating efficient optimization methods in mechanics and control is revealing the regularities present in complex technical and nature processes and presenting them for analytical and numerical-analytical modeling. The level of penetration into the black box model for this phenomenon can be estimated by the level of symmetry presented in its mathematical description. Studies devoted to the research conducted on the regularities of complex phenomena in mechanics and control using neurotechnology, machine learning, other up-to-date mathematical instruments, and information technology are welcome for submission. The applications are planned to focus on aerospace as a recommended area, including its connected fields. We invite contributions related to the relevant problems of space mission and system design, satellite constellation and formation flying, space traffic management, space debris removal, aerospace robotic vehicle control, Earth remote sensing, and geoinformation systems. We also invite domestic and foreign experts to contribute with their research by employing the symmetry or asymmetry concepts in the methods and methodologies, including, but not limited to, the following areas:

  • Mechanics and control;
  • Neurotechnology and machine learning;
  • Space mission and system design;
  • Satellite constellation and formation flying;
  • Space traffic management;
  • Space debris removal;
  • Aerospace robotic-vehicle control;
  • Earth remote sensing and geoinformation systems.

Prof. Dr. Yury Razoumny
Prof. Dr. Arun K. Misra
Prof. Dr. Renuganth Varatharajoo
Dr. Vladimir Razoumny
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. Symmetry 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

  • mechanics and control
  • neurotechnology and machine learning
  • space mission and system design
  • satellite constellation and formation flying
  • space traffic management
  • space debris removal
  • aerospace robotic-vehicle control
  • earth remote sensing and geoinformation systems

Published Papers (3 papers)

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Research

19 pages, 5536 KiB  
Article
A Station-Keeping Control Strategy for a Symmetrical Spacecraft Utilizing Hybrid Low-Thrust Propulsion in the Heliocentric Displaced Orbit
by Tengfei Zhang, Rongjun Mu, Yilin Zhou, Zizheng Liao, Zhewei Zhang, Bo Liao and Chuang Yao
Symmetry 2023, 15(8), 1549; https://doi.org/10.3390/sym15081549 - 06 Aug 2023
Viewed by 687
Abstract
The solar sail spacecraft utilizing a hybrid approach of solar sail and solar electric propulsion in the heliocentric displaced orbit is affected by external disturbances, internal unmodeled dynamics, initial injection errors, and input saturation. To solve the station-keeping control problem under such complex [...] Read more.
The solar sail spacecraft utilizing a hybrid approach of solar sail and solar electric propulsion in the heliocentric displaced orbit is affected by external disturbances, internal unmodeled dynamics, initial injection errors, and input saturation. To solve the station-keeping control problem under such complex conditions, an adaptive control strategy is proposed. First, the dynamical equations of the spacecraft utilizing hybrid low-thrust propulsion in the cylindrical coordinate system are derived. Second, the combined disturbance acceleration introduced by external disturbances and internal unmodeled dynamics is constructed, and a radial basis function neural network estimator is designed to estimate it online in real time. Third, an adaptive high-performance station-keeping controller based on an improved integral sliding surface and multivariate super-twisting sliding mode approaching law is designed. Then, stability analysis is conducted using Lyapunov theory, adaptive laws are designed, and the introduced virtual control accelerations are converted into actual control variables. Finally, simulations are conducted under different simulation conditions based on the disturbance sources. The results show that although the use of hybrid low-thrust propulsion breaks the symmetry of the solar sail in configuration, the proposed control strategy can effectively achieve the station-keeping and disturbance estimation of the spacecraft with only a small amount of propellant consumed and position tracking errors up to decimeters. Full article
(This article belongs to the Special Issue Advances in Mechanics and Control II)
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16 pages, 723 KiB  
Article
Heuristic Technique for the Search of Interception Trajectories to Asteroids with the Use of Solar Sails
by Lucas Gouvêa Meireles, Antônio Fernando Bertachini de Almeida Prado, Cristiano Fiorilo de Melo and Maria Cecília Pereira
Symmetry 2023, 15(3), 617; https://doi.org/10.3390/sym15030617 - 01 Mar 2023
Cited by 1 | Viewed by 1104
Abstract
With the advances of space-exploration technologies, a long-lasting concern is finally being addressed: the deflection of potentially hazardous objects (PHOs). Most recently, the first mission of this kind was launched by NASA—the Double Asteroid Redirection Test (DART). Nevertheless, it is estimated that a [...] Read more.
With the advances of space-exploration technologies, a long-lasting concern is finally being addressed: the deflection of potentially hazardous objects (PHOs). Most recently, the first mission of this kind was launched by NASA—the Double Asteroid Redirection Test (DART). Nevertheless, it is estimated that a great number of these PHOs are unattainable by means of current chemical propulsion systems. With that in mind, this study proposes the development of a heuristic technique for the search of interception trajectories with the use of solar sails and its application in determining a set of possible trajectories to intercept hazardous asteroids. As a case study, a hybrid mission inspired by the DART mission is proposed by using a solar sail as means of propulsion after the initial chemical combustion. The dynamics consider a model of the solar radiation pressure acceleration as a function of the orientation of the sail. In turn, the orientation is defined by the application of the developed heuristic technique with the goal of defining alternative trajectories compared to the original mission. These trajectories result in different impact conditions and mission durations. Although the use of solar sails breaks the symmetry in the solutions, the results obtained offer the possibility of fuel economy or even better deflection results by the achievement of greater impact energy with the hazardous objects. Full article
(This article belongs to the Special Issue Advances in Mechanics and Control II)
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13 pages, 474 KiB  
Article
Optimum, Suboptimal and Solar Sailing Orbital Maneuvers for a Spacecraft Orbiting the Earth
by Lucas Gouvêa Meireles, Vivian Martins Gomes, Antônio Fernando Bertachini de Almeida Prado and Cristiano Fiorilo de Melo
Symmetry 2023, 15(2), 512; https://doi.org/10.3390/sym15020512 - 14 Feb 2023
Viewed by 896
Abstract
The present research performs numerical studies to search for the best maneuvers, from the point of view of minimum time, to make adjustments in the semi-major axis, eccentricity and inclination of a spacecraft traveling around the Earth. For those maneuvers, low thrust propulsion [...] Read more.
The present research performs numerical studies to search for the best maneuvers, from the point of view of minimum time, to make adjustments in the semi-major axis, eccentricity and inclination of a spacecraft traveling around the Earth. For those maneuvers, low thrust propulsion is used under optimal and sub-optimal assumptions, to verify the main differences in terms of transfer time. In addition, solar sail dynamics is used. The spacecraft is assumed to have a propulsion with a fixed magnitude and that the control is based on choosing the direction of the propulsion. It is found that optimal control gives the minimum transfer time, while sub-optimal control restricted the control to follow a predescribed function, which is assumed to be a constant or linear function in time. Finally, solar sails present themselves as an option where fuel is a critical factor, given their much longer maneuver duration, but with a zero fuel consumption. The numerical-analytical modeling of optimization methods developed in this study can break any type of symmetry in the solutions. In turn, they can increase their energetic efficiency. The present research compares those results in detail, in particular looking at the transfer time in all cases studied. Full article
(This article belongs to the Special Issue Advances in Mechanics and Control II)
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