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Aerospace
Special Issues
Small Satellite Formation Flying Motion Control and Attitude Dynamics
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Small Satellite Formation Flying Motion Control and Attitude Dynamics

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

Deadline for manuscript submissions: closed (20 June 2021) | Viewed by 11336

Special Issue Editor

Dr. Danil Ivanov

E-Mail Website
Guest Editor
Keldysh Institute of Applied Mathematics of Russian Academy of Sciences, Moscow, Russia
Interests: spaceflight dynamics; attitude motion; attitude determination; satellite formation flying control algorithms
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

The increasing complexity of approaches and methods of solving fundamental and applied problems of space exploration often lead to the need to create distributed space systems. A number of satellites united in one system and flying at a relatively short distance from each other or at similar orbits are simultaneously working on solving a common problem. The growing popularity of the small satellites allows launching a large number of satellites. Due to constraints in mass, cost, and volume of the small satellites, the translational and attitude motion control has become a scientific and engineering challenge. A wide variety of the non-traditional and advanced classical control systems and approaches have been developed to solve particular problems for formation flying and attitude motion, though it requires a thorough study of its application.

This Special Issue invites submissions that develop new formations of flying motions or attitude control algorithms, investigates its performance analytically, numerically or using laboratory testing. The topics include but are not limited to:

  • Small satellites formation flying dynamics
  • Electromagnetic formation flying control
  • Differential drag control application
  • Satellite swarm control algorithms
  • Active space debris removal by small satellite
  • Passive attitude control system development
  • Magnetic attitude control algorithms
  • Small satellites for Earth remote sensing

Dr. Danil Ivanov
Guest Editor

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

  • Small satellites formation flying
  • Attitude dynamics
  • Control algorithms
  • Electromagnetic interaction
  • Differential drag control
  • Passive attitude control system
  • Magnetic attitude control
  • Motion simulation
  • Ground testing

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Published Papers (3 papers)

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16 pages, 3006 KiB  
Article
Decentralized Control of Nanosatellite Tetrahedral Formation Flying Using Aerodynamic Forces
by Danil Ivanov, Uliana Monakhova, Anna Guerman and Mikhail Ovchinnikov
Aerospace 2021, 8(8), 199; https://doi.org/10.3390/aerospace8080199 - 25 Jul 2021
Cited by 9 | Viewed by 2864
Abstract
A decentralized control algorithm for the construction of a tetrahedral configuration using differential lift and drag forces is proposed in this paper. Four 3U CubeSats launched in LEO are considered. Satellite attitude-controlled motion relative to the incoming airflow provides the required differential forces [...] Read more.
A decentralized control algorithm for the construction of a tetrahedral configuration using differential lift and drag forces is proposed in this paper. Four 3U CubeSats launched in LEO are considered. Satellite attitude-controlled motion relative to the incoming airflow provides the required differential forces in order to change the relative translational motion. The developed control algorithm allows one to track the relative reference trajectories for the satellites at the vertices of the tetrahedron of the required shape and size. The influence of the initial launch conditions on the controlled tetrahedral motion is studied in this paper. Full article
(This article belongs to the Special Issue Small Satellite Formation Flying Motion Control and Attitude Dynamics)
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16 pages, 2646 KiB  
Article
Influence of Satellite Motion Control System Parameters on Performance of Space Debris Capturing
by Mahdi Akhloumadi and Danil Ivanov
Aerospace 2020, 7(11), 160; https://doi.org/10.3390/aerospace7110160 - 6 Nov 2020
Cited by 5 | Viewed by 3121
Abstract
Relative motion control problem for capturing the tumbling space debris object is considered. Onboard thrusters and reaction wheels are used as actuators. The nonlinear coupled relative translational and rotational equations of motion are derived. The SDRE-based control algorithm is applied to the problem. [...] Read more.
Relative motion control problem for capturing the tumbling space debris object is considered. Onboard thrusters and reaction wheels are used as actuators. The nonlinear coupled relative translational and rotational equations of motion are derived. The SDRE-based control algorithm is applied to the problem. It is taken into account that the thrust vector has misalignment with satellite center of mass, and reaction wheels saturation affects the ability of the satellite to perform the docking maneuver to space debris. The acceptable range of a set of control system parameters for successful rendezvous and docking is studied using numerical simulations taking into account thruster discreteness, actuators constrains, and attitude motion of the tumbling space debris. Full article
(This article belongs to the Special Issue Small Satellite Formation Flying Motion Control and Attitude Dynamics)
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20 pages, 728 KiB  
Article
Leader–Follower Synchronization of Uncertain Euler–Lagrange Dynamics with Input Constraints
by Muhammad Ridho Rosa
Aerospace 2020, 7(9), 127; https://doi.org/10.3390/aerospace7090127 - 30 Aug 2020
Cited by 8 | Viewed by 3927
Abstract
This paper addresses the problem of leader–follower synchronization of uncertain Euler–Lagrange systems under input constraints. The problem is solved in a distributed model reference adaptive control framework that includes positive μ-modification to address input constraints. The proposed design has the distinguishing features [...] Read more.
This paper addresses the problem of leader–follower synchronization of uncertain Euler–Lagrange systems under input constraints. The problem is solved in a distributed model reference adaptive control framework that includes positive μ-modification to address input constraints. The proposed design has the distinguishing features of updating the gains to synchronize the uncertain systems and of providing stable adaptation in the presence of input saturation. By using a matching condition assumption, a distributed inverse dynamics architecture is adopted to guarantee convergence to common dynamics. The design is studied analytically, and its performance is validated in simulation using spacecraft dynamics. Full article
(This article belongs to the Special Issue Small Satellite Formation Flying Motion Control and Attitude Dynamics)
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