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Aerospace
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Guidance, Navigation and Control Algorithms for Satellite Formation Flying
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Guidance, Navigation and Control Algorithms for Satellite Formation Flying

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

Deadline for manuscript submissions: closed (15 November 2024) | Viewed by 8302

Special Issue Editors

Dr. Gabriella Gaias

E-Mail Website
Guest Editor
Department of Aerospace Science and Technology, Politecnico di Milano, 20133 Milan, Italy
Interests: development of AOCS/GNC algorithms; simulation systems; flight software for autonomous formation flying and proximity operation applications
Dr. Jean-Sébastien Ardaens

E-Mail
Guest Editor
ClearSpace SA, Rue de Lausanne 64, 1020 Renens, Switzerland
Interests: GNC; onboard autonomy; precise navigation; rendezvous; formation-flying

Special Issue Information

Dear Colleagues,

I am pleased to announce a new open access Special Issue of the MDPI journal Aerospace, titled “Guidance, Navigation and Control Algorithms for Satellite Formation Flying”.

Formation flying missions enable technological applications of scientific and societal relevance, where standard monolithic solutions fail. Distributed space systems, swarms, and fractionated systems are a key asset to build extended, flexible, and scalable space endeavours. Moreover, a significant number of current technological research efforts address multi-satellite missions devoted to in-orbit servicing and active debris removal activities.

The operation of satellites in proximity, with different levels of cooperation among them, demands the development of relative guidance, navigation, and control (GNC) systems, which entail all the functions that complement the standard orbit/attitude determination and control tasks of single-satellite missions. In addition, mission safety in the sense of collision avoidance among the spacecraft of the formation has to be ensured. Frontier research efforts on the development of relative GNC algorithms focus on improving navigation/control performances, increasing the level of autonomy and minimizing the computational load while ensuring robust and reliable approaches suitable for spaceborne implementation.

This Special Issue aims to collect contributions in a range of aspects related to GNC systems, spanning from relative navigation and the establishment and maintenance of the required relative configuration between the elements of a space distributed system, to collision avoidance monitoring and manoeuvring. Particular attention is devoted to algorithms’ development and verification. Potential applications include, but are not limited to, the following:

  • Formation flying missions for Earth observation;
  • Formation flying missions for space observation;
  • In-orbit servicing missions;
  • In-orbit inspection and active debris removal missions;
  • Swarms missions;
  • Formation flying missions around small bodies.

Dr. Gabriella Gaias
Dr. Jean-Sébastien Ardaens
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

  • relative navigation
  • relative orbit determination
  • spacecraft rendezvous
  • satellite formation flying
  • formation reconfiguration
  • active debris removal
  • autonomy
  • swarms
  • space distributed systems

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Published Papers (6 papers)

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Research

31 pages, 24798 KiB  
Article
A Study of Cislunar-Based Small Satellite Constellations with Sustainable Autonomy
by Mohammed Irfan Rashed and Hyochoong Bang
Aerospace 2024, 11(9), 787; https://doi.org/10.3390/aerospace11090787 - 23 Sep 2024
Viewed by 717
Abstract
The Cislunar economy is thriving with innovative space systems and operation techniques to enhance and uplift the traditional approaches significantly. This paper brings about an approach for sustainable small satellite constellations to retain autonomy for long-term missions in the Cislunar space. The methodology [...] Read more.
The Cislunar economy is thriving with innovative space systems and operation techniques to enhance and uplift the traditional approaches significantly. This paper brings about an approach for sustainable small satellite constellations to retain autonomy for long-term missions in the Cislunar space. The methodology presented is to align the hybrid model of the constellation for Earth and Moon as an integral portion of the Cislunar operations. These hybrid constellations can provide a breakthrough in optimally utilizing the Cislunar space to efficiently deploy prominent missions to be operated and avoid conjunction or collisions forming additional debris. Flower and walker constellation patterns have been combined to form a well-defined orientation for these small satellites to operate and deliver the tasks satisfying the mission objectives. The autonomous multi-parametric analysis for each constellation based in Earth and Moon’s environment has been attained with due consideration to local environments. Specifically, the Solar Radiation Pressure (SRP) is a critical constraint in Cislunar operations and is observed during simulations. These are supported by conjunction analysis using the Monte Carlo technique and also the effect of the SRP on the operating small satellites in real-time scenarios. This is followed by the observed conclusions and the way forward in this fiercely competent Cislunar operation. Full article
(This article belongs to the Special Issue Guidance, Navigation and Control Algorithms for Satellite Formation Flying)
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16 pages, 859 KiB  
Article
Consensus SE(3)-Constrained Extended Kalman Filter for Close Proximity Orbital Relative Pose Estimation
by S. Mathavaraj and Eric A. Butcher
Aerospace 2024, 11(9), 762; https://doi.org/10.3390/aerospace11090762 - 17 Sep 2024
Viewed by 537
Abstract
In this paper, a recently proposed SE(3)-constrained extended Kalman filter (EKF) is extended to formulate a strategy for relative orbit estimation in a space-based sensor network. The resulting consensus SE(3)-constrained EKF utilizes space-based [...] Read more.
In this paper, a recently proposed SE(3)-constrained extended Kalman filter (EKF) is extended to formulate a strategy for relative orbit estimation in a space-based sensor network. The resulting consensus SE(3)-constrained EKF utilizes space-based sensor fusion and is applied to the problem of spacecraft proximity operations and formation flying. The proposed filter allows for the state (i.e., pose and velocities) estimation of the deputy satellite while accounting for measurement error statistics using the rotation matrix to represent attitude. Via a comparison with a conventional filter in the literature, it is shown that the use of the proposed consensus SE(3)-constrained EKF can improve the convergence performance of the existing filter for satellite formation flying. Moreover, the benefits of faster convergence and consensus speed by using communication networks with more connections are illustrated to show the significance of the proposed sensor fusion strategy in spacecraft proximity operations. Full article
(This article belongs to the Special Issue Guidance, Navigation and Control Algorithms for Satellite Formation Flying)
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24 pages, 2646 KiB  
Article
Fuelless On-Orbit Assembly of a Large Space Truss Structure Using Repulsion of the Service Spacecraft by Robotic Manipulators
by Vladislav Orlov, Uliana Monakhova, Mikhail Ovchinnikov and Danil Ivanov
Aerospace 2024, 11(8), 635; https://doi.org/10.3390/aerospace11080635 - 2 Aug 2024
Viewed by 923
Abstract
A servicing spacecraft motion control approach for the problem of on-orbit truss structure assembly is developed in this paper. It is considered that a cargo container with a rod set and servicing spacecraft are in orbit initially. The assembly procedure is based on [...] Read more.
A servicing spacecraft motion control approach for the problem of on-orbit truss structure assembly is developed in this paper. It is considered that a cargo container with a rod set and servicing spacecraft are in orbit initially. The assembly procedure is based on spacecraft free-flight motion between the structure’s specified points. The spacecraft is equipped with two robotic manipulators capable of attaching to the structure and holding rods. In addition, the spacecraft can repulse from the structure with a given relative velocity using a manipulator, so the spacecraft and the structure receive impulses. The repulsion velocity vector is calculated in order to reach the structure target point to deliver and install the rod into the truss structure, or to reach the cargo container and take a rod. The problem of searching the repulsion velocity is formulated as an optimization problem with constraints, taking into account the limited value of the repulsion velocity, collision avoidance with structure, restrictions on the angular velocity and translational motion of the structure in the orbital reference frame. This problem is solved numerically with an initial guess vector obtained analytically for simplified motion cases. The application of the proposed control scheme to the assembly of a truss-based antenna is demonstrated. It is shown that the servicing spacecraft is successfully transferred between the structure points by means of manipulator repulsion. Main features and limitations of the assembly problem using a spacecraft with two manipulators are discussed. Full article
(This article belongs to the Special Issue Guidance, Navigation and Control Algorithms for Satellite Formation Flying)
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24 pages, 1568 KiB  
Article
Modeling, Simulation and Control of a Spacecraft: Automated Rendezvous under Positional Constraints
by Simone Fiori, Francesco Rachiglia, Luca Sabatini and Edoardo Sampaolesi
Aerospace 2024, 11(3), 245; https://doi.org/10.3390/aerospace11030245 - 21 Mar 2024
Viewed by 1675
Abstract
The aim of this research paper is to propose a framework to model, simulate and control the motion of a small spacecraft in the proximity of a space station. In particular, rendezvous in the presence of physical obstacles is tackled by a virtual [...] Read more.
The aim of this research paper is to propose a framework to model, simulate and control the motion of a small spacecraft in the proximity of a space station. In particular, rendezvous in the presence of physical obstacles is tackled by a virtual potential theory within a modern manifold calculus setting and simulated numerically. The roto-translational motion of a spacecraft as well as the control fields are entirely formulated through a coordinate-free Lie group-type formalism. Likewise, the proposed control strategies are expressed in a coordinate-free setting through structured control fields. Several numerical simulations guide the reader through an evaluation of the most convenient control strategy among those devised in the present work. Full article
(This article belongs to the Special Issue Guidance, Navigation and Control Algorithms for Satellite Formation Flying)
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21 pages, 3291 KiB  
Article
Generation of Secondary Space Debris Risks from Net Capturing in Active Space Debris Removal Missions
by Michal Cuadrat-Grzybowski and Eberhard Gill
Aerospace 2024, 11(3), 236; https://doi.org/10.3390/aerospace11030236 - 18 Mar 2024
Viewed by 1545
Abstract
Mitigation strategies to eliminate existing space debris, such as with Active Space Debris Removal (ASDR) missions, have become increasingly important. Among the considered ASDR approaches, one involves using a net as a capturing mechanism. A fundamental requirement for any ASDR mission is that [...] Read more.
Mitigation strategies to eliminate existing space debris, such as with Active Space Debris Removal (ASDR) missions, have become increasingly important. Among the considered ASDR approaches, one involves using a net as a capturing mechanism. A fundamental requirement for any ASDR mission is that the capture process itself should not give rise to new space debris. However, in simulations of net capturing, the potential for structural breaking is often overlooked. A discrete Multi-Spring-Damper net model was employed to simulate the impact of a 30 m × 30 m net travelling at 20 m/s onto an ESA Envisat mock-up. The Envisat was modelled as a two-rigid-body system comprised of the main body and a large solar array with a hinge connection. The analysis revealed that more than two significant substructures had a notable likelihood of breaking, prompting the recommendation of limiting the impacting velocity. The generation of secondary space debris indicates that net capturing is riskier than previously assumed in the literature. Full article
(This article belongs to the Special Issue Guidance, Navigation and Control Algorithms for Satellite Formation Flying)
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25 pages, 6820 KiB  
Article
Autonomous Optimal Absolute Orbit Keeping through Formation Flying Techniques
by Ahmed Mahfouz, Gabriella Gaias, D. M. K. K. Venkateswara Rao and Holger Voos
Aerospace 2023, 10(11), 959; https://doi.org/10.3390/aerospace10110959 - 13 Nov 2023
Cited by 1 | Viewed by 1742
Abstract
In this paper, the problem of autonomous optimal absolute orbit keeping for a satellite mission in Low Earth Orbit using electric propulsion is considered. The main peculiarity of the approach is to support small satellite missions in which the platform is equipped with [...] Read more.
In this paper, the problem of autonomous optimal absolute orbit keeping for a satellite mission in Low Earth Orbit using electric propulsion is considered. The main peculiarity of the approach is to support small satellite missions in which the platform is equipped with a single thruster nozzle that provides acceleration on a single direction at a time. This constraint implies that an attitude maneuver is necessary before or during each thrusting arc to direct the nozzle into the desired direction. In this context, an attitude guidance algorithm specific for the orbit maneuver has been developed. A Model Predictive Control scheme is proposed, where the attitude kinematics are coupled with the orbital dynamics in order to obtain the optimal guidance profiles in terms of satellite state, reference attitude, and thrust magnitude. The proposed control scheme is developed exploiting formation flying techniques where the reference orbit is that of a virtual spacecraft that the main satellite is required to rendezvous with. In addition to the controller design, the closed-loop configuration is presented supported by numerical simulations. The efficacy of the proposed autonomous orbit-keeping approach is shown in several application scenarios. Full article
(This article belongs to the Special Issue Guidance, Navigation and Control Algorithms for Satellite Formation Flying)
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