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Aerospace
Special Issues
Space Systems Preliminary Design
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Space Systems Preliminary Design

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

Deadline for manuscript submissions: closed (30 April 2024) | Viewed by 11006

Special Issue Editors

Prof. Dr. Rob A. Vingerhoeds

E-Mail Website
Guest Editor
ISAE-SUPAERO, 31400 Toulouse, France
Interests: complex systems; (model-based) systems engineering; systems architecture; knowledge representation; artificial intelligence; real-time systems; concurrent design engineering; multi-agent systems; autonomous decision making; distributed systems
Dr. Sophia Salas Cordero

E-Mail Website
Guest Editor
ISAE-SUPAERO, 31400 Toulouse, France
Interests: complex systems; systems engineering; design engineering; concurrent engineering; knowledge representation and reasoning; cybersecurity; risk and obsolescence management
Dr. Thibault Gateau

E-Mail Website
Guest Editor
ISAE-SUPAERO, 31400 Toulouse, France
Interests: CubeSats; concurrent design engineering; preliminary design; automated planning; multi-agent systems; autonomous decision making; distributed system; fractionated spacecraft

Special Issue Information

Dear Colleagues,

The preliminary design of space systems is known to involve an interdisciplinary team that work concurrently and play a vital role in the further development of space systems, by facilitating a design workflow for either flight or ground segments. The whole life cycle includes design decisions that may affect training, operations resource management, human factors, safety, habitability and environment, and maintainability and supportability. Practitioners would benefit from optimizing space system preliminary designs, but they face challenges in terms of technology, costs, and socio-organizational approaches.

This Special Issue seeks original contributions that discuss space system preliminary designs, methodologies, and/or tooling that could allow analytical verification, time savings, reduced errors in sizing, better cost prediction, and a better compliance to mission requirements for space missions or systems. Topics of interest include but are not limited to:

  • Space system preliminary design, conceptual design, concurrent design;
  • Space systems and subsystems (e.g., satellite systems);
  • Space system modeling and analysis;
  • (Model-based) space system engineering;
  • Space system architecture;
  • Design methods and tools;
  • Design knowledge reuse;
  • Preliminary design data integration and management;
  • Multi-disciplinary optimization;
  • Artificial intelligence for design;
  • Decision-support tools;
  • Human–system interfaces;
  • Human-in-the-loop;
  • Methodologies to ease hand-over from preliminary design to next design stages, involving other teams;
  • Knowledge reuse from preliminary design to operations;
  • Change management;
  • Database management;
  • Data sharing;
  • Data representation/conversion/translation;
  • Meta-modelling.

High-quality papers based on theories, applications, or experimental data related to space system preliminary design are welcome.

Prof. Dr. Rob A. Vingerhoeds
Dr. Sophia Salas Cordero
Dr. Thibault Gateau
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

  • preliminary design
  • conceptual design, concurrent design, space systems
  • nanosatellites
  • (model-based) systems engineering, systems architecture, modeling
  • analysis
  • multi-disciplinary optimization
  • artificial intelligence

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Published Papers (6 papers)

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Research

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52 pages, 5903 KiB  
Article
Preliminary Design of Satellite Systems through the Integration of Model-Based System Engineering and Agile Methodologies: Application to the 3ColStar Mission
by Jeimmy Nataly Buitrago-Leiva, Juan José Mejía, Juan Francisco Puerta-Ibarra, Ignacio Francisco Acero-Niño, Andrés Felipe Guarnizo-Saavedra, Julian Rodriguez-Ferreira, Leandro Rojas-Rodriguez, Francisco Luis Hernández-Torres, Cristian Esteban Arango-Cotacio, Jorge Enrique Salazar-Morales, Miguel Angel Herrera-Cruz, Mario Linares-Vásquez, Jose Fernando Jiménez-Vargas, Jorge Enríque Espíndola-Díaz, Óscar Javier Montañez-Sogamoso and Adriano Camps
Aerospace 2024, 11(9), 758; https://doi.org/10.3390/aerospace11090758 - 14 Sep 2024
Viewed by 2008
Abstract
This paper presents a case study on integrating Agile Systems Engineering methodologies in the preliminary design phase of satellite systems, focusing on the 3ColStar satellite mission. Through Model-Based Systems Engineering (MBSE), technical consistency was rigorously managed across various architectural documents, ensuring coherency [...] Read more.
This paper presents a case study on integrating Agile Systems Engineering methodologies in the preliminary design phase of satellite systems, focusing on the 3ColStar satellite mission. Through Model-Based Systems Engineering (MBSE), technical consistency was rigorously managed across various architectural documents, ensuring coherency and minimizing errors. Furthermore, the preliminary design was developed, with the implementation of the Arcadia Method, supported by the Capella modeling tool. This allowed the digitalization of the system, which was represented by models that contain requirements, architecture, and interfaces between the different parts of the system. At the same time, the preliminary design process was streamlined and completed within an accelerated time frame of 4 months, with weekly sprints driving progress based on the scrum methodology. This case study highlights the effectiveness of Agile Systems Engineering principles to improve the team communication accuracy, communication, and efficiency of satellite systems preliminary design, providing valuable insights for future missions. Full article
(This article belongs to the Special Issue Space Systems Preliminary Design)
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26 pages, 3780 KiB  
Article
Open-Source Data Formalization through Model-Based Systems Engineering for Concurrent Preliminary Design of CubeSats
by Giacomo Luccisano, Sophia Salas Cordero, Thibault Gateau and Nicole Viola
Aerospace 2024, 11(9), 702; https://doi.org/10.3390/aerospace11090702 - 27 Aug 2024
Viewed by 670
Abstract
Market trends in the space sector suggest a notable increase in satellite operations and market value for the coming decade. In parallel, there has been a shift in the industrial and academic sectors from traditional Document-Based System Engineering to Model-based systems engineering (MBSE) [...] Read more.
Market trends in the space sector suggest a notable increase in satellite operations and market value for the coming decade. In parallel, there has been a shift in the industrial and academic sectors from traditional Document-Based System Engineering to Model-based systems engineering (MBSE) combined with Concurrent engineering (CE) practices. Due to growing demands, the drivers behind this change have been the need for quicker and more cost-effective design processes. A key challenge in this transition remains to determine how to effectively formalize and exchange data during all design stages and across all discipline-specific tools; as representing systems through models can be a complex endeavor. For instance, during the Preliminary design (PD) phase, the integration of system models with external mathematical models for simulations, analyses, and system budgeting is crucial. The introduction of CubeSats and their standard has partly addressed the question of standardization and has aided in reducing overall development time and costs in the space sector. Nevertheless, questions about how to successfully exchange data endure. This paper focuses on formalizing a CubeSat model for use across various stages of the PD phase. The entire process is conducted with the exclusive use of open-source tools, to facilitate the transparency of data integration across the PD phases, and the overall life cycle of a CubeSat. The paper has two primary outcomes: (i) developing a generic CubeSat model using Systems modeling language (SysML) that includes data storage and visualization through the application of Unified modeling language (UML) stereotypes, streamlining in parallel information exchange for integration with various simulation and analysis tools; (ii) creating an end-to-end use case scenario within the Nanostar software suite (NSS), an open-source framework designed to streamline data exchange across different software during CE sessions. A case study from a theoretical academic space mission concept is presented as the illustration of how to utilize the proposed formalization, and it serves as well as a preliminary validation of the proposed formalization. The proposed formalization positions the CubeSat SysML model as the central data source throughout the design process. It also supports automated trade-off analyses by combining the benefits of SysML with effective data instantiating across all PD study phases. Full article
(This article belongs to the Special Issue Space Systems Preliminary Design)
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21 pages, 31361 KiB  
Article
Design and Analysis of the Integrated Drag-Free and Attitude Control System for TianQin Mission: A Preliminary Result
by Liwei Hao and Yingchun Zhang
Aerospace 2024, 11(6), 416; https://doi.org/10.3390/aerospace11060416 - 21 May 2024
Cited by 1 | Viewed by 882
Abstract
This article explores novel in-orbit drag-free technology that can be utilized for deep space detection scientific missions. In this study, we considered a two-test-mass drag-free method and analyzed the design of the drag-free and attitude control system for the TianQin mission. The entire [...] Read more.
This article explores novel in-orbit drag-free technology that can be utilized for deep space detection scientific missions. In this study, we considered a two-test-mass drag-free method and analyzed the design of the drag-free and attitude control system for the TianQin mission. The entire control system was comprehensively designed, including an actuator allocation design and controllers for two test masses and one spacecraft, with a total of 18 degrees of freedom. Furthermore, stability analysis was conducted. Based on our design, numerical analysis and simulations were performed assuming geocentric orbit conditions in the TianQin mission, confirming the feasibility of this aerospace engineering concept. The versatility of the design allows for its application to scientific observations across various disciplines by modifying the structure of the simulation environment, and consequently, the approach discussed in this study holds significant practical implications for effectively accomplishing deep space observation tasks. Full article
(This article belongs to the Special Issue Space Systems Preliminary Design)
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16 pages, 2721 KiB  
Article
Enhancing Planetary Exploration through Digital Twins: A Tool for Virtual Prototyping and HUMS Design
by Lucio Pinello, Lorenzo Brancato, Marco Giglio, Francesco Cadini and Giuseppe Francesco De Luca
Aerospace 2024, 11(1), 73; https://doi.org/10.3390/aerospace11010073 - 12 Jan 2024
Cited by 3 | Viewed by 1691
Abstract
In recent times, the demand for resilient space rovers has surged, which has been driven by the amplified exploration of celestial bodies such as the Moon and Mars. Recognising the limitations of direct human intervention in such environments, these rovers have gained a [...] Read more.
In recent times, the demand for resilient space rovers has surged, which has been driven by the amplified exploration of celestial bodies such as the Moon and Mars. Recognising the limitations of direct human intervention in such environments, these rovers have gained a great deal of importance. Our proposal introduces a digital twin for space exploration rovers that seamlessly integrates intricate geometric, kinematic, and dynamic models, along with sensor and control systems. It faithfully emulates genuine real-world scenarios, providing an authentic testing ground for rover prototypes and the development of damage detection algorithms. Its flexibility in replicating diverse terrains, environmental conditions, and operational scenarios significantly expedites rover development. The digital twin serves as a valuable tool in the perfecting of damage detection systems, allowing engineers to efficiently craft diagnostic algorithms. This innovative approach not only conserves valuable resources but also ensures the robustness of space mission systems, thus enhancing the overall success and safety of planetary exploration endeavours. Full article
(This article belongs to the Special Issue Space Systems Preliminary Design)
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22 pages, 6248 KiB  
Article
Design of a Mars Ascent Vehicle Using HyImpulse’s Hybrid Propulsion
by Maël Renault and Vaios Lappas
Aerospace 2023, 10(12), 1030; https://doi.org/10.3390/aerospace10121030 - 14 Dec 2023
Cited by 2 | Viewed by 1998
Abstract
The recent growth in maturity of paraffin-based hybrid propulsion systems reassesses the possibility to design an alternative Mars Ascent Vehicle (MAV) propelled by a European hybrid motor. As part of the Mars Sample Return (MSR) campaign, a Hybrid MAV would present potential advantages [...] Read more.
The recent growth in maturity of paraffin-based hybrid propulsion systems reassesses the possibility to design an alternative Mars Ascent Vehicle (MAV) propelled by a European hybrid motor. As part of the Mars Sample Return (MSR) campaign, a Hybrid MAV would present potential advantages over the existent solid concept funded by NASA through offering increased performance, higher thermal resilience, and lower Gross Lift-Off Mass (GLOM). This study looks at the preliminary design of a two-stage European MAV equipped with HyImpulse’s hybrid engine called the Hyplox10. This Hybrid MAV utilizes the advantages inherent to this type of propulsion to propose an alternative MAV concept. After a careful analysis of previous MAV architectures from the literature, the vehicle is sized with all its components such as the propellant tanks and nozzle, and the configuration of the rocket is established. A detailed design of the primary structure is addressed. This is followed by a Finite Element Analysis (FEA), evaluating the structural integrity under the challenging conditions of Entry, Descent, and Landing (EDL) on Mars, considering both static and dynamic analyses. The outcome is a Hybrid MAV design that demonstrates feasibility and resilience in the harsh Martian environment, boasting a GLOM of less than 300 kg. Full article
(This article belongs to the Special Issue Space Systems Preliminary Design)
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Review

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51 pages, 4160 KiB  
Review
On Topology Optimisation Methods and Additive Manufacture for Satellite Structures: A Review
by Arturo Benjamín Hurtado-Pérez, Abraham de Jesús Pablo-Sotelo, Fabián Ramírez-López, Jorge Javier Hernández-Gómez and Miguel Felix Mata-Rivera
Aerospace 2023, 10(12), 1025; https://doi.org/10.3390/aerospace10121025 - 11 Dec 2023
Cited by 2 | Viewed by 2971
Abstract
Launching satellites into the Earth’s orbit is a critical area of research, and very demanding satellite services increase exponentially as modern society takes shape. At the same time, the costs of developing and launching satellite missions with shorter development times increase the requirements [...] Read more.
Launching satellites into the Earth’s orbit is a critical area of research, and very demanding satellite services increase exponentially as modern society takes shape. At the same time, the costs of developing and launching satellite missions with shorter development times increase the requirements of novel approaches in the several engineering areas required to build, test, launch, and operate satellites in the Earth’s orbit, as well as in orbits around other celestial bodies. One area with the potential to save launching costs is that of the structural integrity of satellites, particularly in the launching phase where the largest vibrations due to the rocket motion and subsequent stresses could impact the survival ability of the satellite. To address this problem, two important areas of engineering join together to provide novel, complete, and competitive solutions: topology optimisation methods and additive manufacturing. On one side, topology optimisation methods are mathematical methods that allow iteratively optimising structures (usually by decreasing mass) while improving some structural properties depending on the application (load capacity, for instance), through the maximisation or minimisation of a uni- or multi-objective function and multiple types of algorithms. This area has been widely active in general for the last 30 years and has two main core types of algorithms: continuum methods that modify continuous parameters such as density, and discrete methods that work by adding and deleting material elements in a meshing context. On the other side, additive manufacturing techniques are more recent manufacturing processes aimed at revolutionising manufacturing and supply chains. The main exponents of additive manufacturing are Selective Laser Melting (SLM) (3D printing) as well as Electron Beam Melting (EBM). Recent trends show that topology-optimised structures built with novel materials through additive manufacturing processes may provide cheaper state-of-the-art structures that are fully optimised to better perform in the outer-space environment, particularly as part of the structure subsystem of novel satellite systems. This work aims to present an extended review of the main methods of structural topology optimisation as well as additive manufacture in the aerospace field, with a particular focus on satellite structures, which may set the arena for the development of future satellite structures in the next five to ten years. Full article
(This article belongs to the Special Issue Space Systems Preliminary Design)
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