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Aerospace
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Space System Design
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Space System Design

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

Deadline for manuscript submissions: 15 December 2025 | Viewed by 2616

Special Issue Editors

Prof. Dr. Ed Kruzins

E-Mail Website
Guest Editor
School of Engineering & Technology, University of New South Wales Canberra, Canberra 2610, Australia
Interests: spaceflight & space launch systems; ground station communications; sensors; modelling & simulation; systems engineering; space policy; deep space optical communications; asteroid bistatic radar
Dr. Edwin Peters

E-Mail Website
Guest Editor
School of Engineering & Technology, University of New South Wales Canberra, Canberra 2610, Australia
Interests: signal processing; satellite communication; array signal processing; digital signal processing; GPGPU; embedded systems; FPGA; asteroid bistatic radar; space domain awareness

Special Issue Information

Dear Colleagues,

Innovative system design is pivotal in the evolving landscape of space exploration and satellite technology. This Special Issue aims to showcase pioneering research and advancements in space system design. We invite submissions that highlight cutting-edge developments in spacecraft, satellite constellations, and mission architecture.

Themes for Submission:

  1. Advanced Mission Design: papers that explore novel mission concepts, including interplanetary and deep-space missions, as well as Earth observation and scientific satellites.
  2. Spacecraft Subsystem Innovations: studies focusing on developing critical spacecraft subsystems such as propulsion, power, thermal management, and communication technologies.
  3. Modular and Scalable Space Architectures: contributions detailing the design and implementation of modular and scalable systems that enhance the flexibility and sustainability of space missions.
  4. AI and ML in Space System Design: research on applying artificial intelligence and machine learning to optimize design processes, mission planning, and real-time decision-making in space environments.
  5. Sustainability in Space: discussions on sustainable practices in space system design, addressing debris mitigation, end-of-life strategies, and the reuse of spacecraft components.
  6. Integration of Commercial Off-the-Shelf (COTS) Components: papers examining the challenges and benefits of incorporating COTS components into space systems, particularly focusing on reliability and cost-effectiveness.

We seek contributions from academics, industry professionals, and government researchers. Articles can range from detailed research papers and reviews to shorter communications on recent significant advances.

Prof. Dr. Ed Kruzins
Dr. Edwin Peters
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

  • advanced mission design
  • spacecraft subsystem innovations
  • modular and scalable space architectures
  • AI and ML in space system design
  • sustainability in space
  • integration of commercial off-the-shelf (COTS) components

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Further information on MDPI's Special Issue policies can be found here.

Published Papers (4 papers)

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Research

18 pages, 3772 KiB  
Article
Characteristics of Force Transmissibility in PLOVIS-II Cooler Micro-Vibration Isolation System
by Yeon-Hyeok Park, Mun-Shin Jo, Hoon-Young Kim and Hyun-Ung Oh
Aerospace 2025, 12(6), 511; https://doi.org/10.3390/aerospace12060511 - 6 Jun 2025
Viewed by 359
Abstract
This study investigates the basic characteristics of force transmissibility for a passive launch and on-orbit vibration isolation system (PLOVIS-II), which was developed to examine the microvibration attenuation of a spaceborne cryogenic cooler. The design, based on a coil spring-type passive vibration isolation system [...] Read more.
This study investigates the basic characteristics of force transmissibility for a passive launch and on-orbit vibration isolation system (PLOVIS-II), which was developed to examine the microvibration attenuation of a spaceborne cryogenic cooler. The design, based on a coil spring-type passive vibration isolation system without an additional launch-lock device, demonstrated an effective vibration attenuation performance in both launch and on-orbit vibration isolation. In this study, a test setup and method were developed to measure the force transmissibility of an isolator along each axis using a voice-coil-type non-contact vibration excitation instrument. In addition, the test results included the position sensitivity of PLOVIS-II, considering the worst misalignment of the isolation system, and its performance was compared with that of PLOVIS-I proposed in a previous study. Full article
(This article belongs to the Special Issue Space System Design)
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24 pages, 18075 KiB  
Article
Engineering-Oriented Layout Optimization and Trade-Off Design of a 12U CubeSat with In-Orbit Validation
by Jiyao Zhang, Zhenqian Liu, Liwei Luo, Chunqiu Zhao and Huayi Li
Aerospace 2025, 12(6), 506; https://doi.org/10.3390/aerospace12060506 - 3 Jun 2025
Viewed by 406
Abstract
The extensive application of CubeSats in fields such as communication, remote sensing, and scientific exploration highlights their significant engineering value. With the growth of CubeSat dimensions towards 12U and beyond, their potential for engineering applications has further expanded. However, strict size constraints significantly [...] Read more.
The extensive application of CubeSats in fields such as communication, remote sensing, and scientific exploration highlights their significant engineering value. With the growth of CubeSat dimensions towards 12U and beyond, their potential for engineering applications has further expanded. However, strict size constraints significantly limit the layout design space, causing difficulties in satellite system design through multiple iterations. To address these practical issues, this paper proposes an engineering-oriented layout optimization and trade-off design approach tailored specifically for 12U CubeSats, employing a hybrid optimization framework combining GRASP and NSGA-III algorithms. The proposed methodology facilitates initial feasibility analysis, informed trade-off decisions during iterative design, and detailed optimization in later stages, thereby improving design efficiency and practicality. The proposed optimization systematically explores design compromises considering conflicting objectives such as mass properties, thermal management, and spacing constraints. The ASRTU Friendship MicroSat, a 12U CubeSat, serves as a case study, with in-orbit performance validating the proposed approach. Results demonstrate that the optimized layouts effectively address complex engineering constraints, enabling satellite design teams to successfully achieve optimized layout solutions in practical engineering applications. Full article
(This article belongs to the Special Issue Space System Design)
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25 pages, 731 KiB  
Article
An Examination of the Complexity of the Large Sociotechnical Space System
by Francisco Del Canto Viterale
Aerospace 2025, 12(6), 491; https://doi.org/10.3390/aerospace12060491 - 29 May 2025
Viewed by 362
Abstract
Complexity has emerged as a global phenomenon with significant implications for the organization and structure of any system. In recent decades, the space system has undergone a transition to a more complex configuration. This essay argues that the increasing complexity of space system [...] Read more.
Complexity has emerged as a global phenomenon with significant implications for the organization and structure of any system. In recent decades, the space system has undergone a transition to a more complex configuration. This essay argues that the increasing complexity of space system architecture is attributable to the proliferation and diversification of actors, interactions, processes, trends, and topics that demand novel examinations and explanations. This research emphasizes the necessity of employing systems and social science methodologies to evaluate and provide novel perspectives on the study of complex systems, such as the space system. The primary objective of this study is to examine the complex structure of the current space system using a sociotechnical systems model. The present study offers a comprehensive examination of the contemporary space system, emphasizing the role of contextual elements, active agents, forms of interaction, and the diverse applications and emergent trends that are profoundly influencing not only the space system itself but also the broader international system. Full article
(This article belongs to the Special Issue Space System Design)
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24 pages, 3911 KiB  
Article
Testing Performance of Modeling and Simulation Code of Liquid Propellant Supply System Using Method of Characteristics
by Ji Hoe Seo, Hye In Kim, Tae-Seong Roh and Hyoung Jin Lee
Aerospace 2025, 12(2), 76; https://doi.org/10.3390/aerospace12020076 - 22 Jan 2025
Viewed by 893
Abstract
The primary objective of a liquid propellant supply system is to supply propellant to the engine, enabling stable mission performance. Therefore, the system design must aim at minimizing factors that may contribute to instability while satisfying the specified requirements. Modeling and simulation (M&S) [...] Read more.
The primary objective of a liquid propellant supply system is to supply propellant to the engine, enabling stable mission performance. Therefore, the system design must aim at minimizing factors that may contribute to instability while satisfying the specified requirements. Modeling and simulation (M&S) techniques are typically used to achieve efficient design, offering advantages such as the ability to simulate various conditions without constraints, thereby reducing initial development costs and time. Consequently, the performance and accuracy of the M&S program can significantly impact the overall development process. In this study, the method of characteristics (MOC) is used to effectively calculate internal flow in pipes, thereby developing an M&S code with excellent accuracy and performance. The efficiency of the developed in-house code is evaluated by comparing the simulation results with those of a commercial program. Additionally, a water supply experiment is conducted, and the experimental results are compared with the two simulation outcomes for validation. The comparative analysis highlights the superior performance and accuracy of the in-house code over the commercial program, with the in-house code demonstrating an average accuracy improvement of approximately 2% to 3% and with computational performance being approximately 1.7 times faster. Full article
(This article belongs to the Special Issue Space System Design)
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