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20 pages, 1799 KB

Open AccessArticle

An Analytical Framework for Determining the Minimum Size of Highly Miniaturized Satellites: PlanarSats

by Mehmet Şevket Uludağ and Alim Rüstem Aslan

Aerospace 2025, 12(10), 876; https://doi.org/10.3390/aerospace12100876 - 28 Sep 2025

This paper introduces a power-driven systems engineering methodology for the early-phase design of highly miniaturized satellites: PlanarSats. We derive an analytical framework linking power requirements, contingency policies, solar-cell performance, and subsystem integration to determine the absolute minimum satellite size. Through idealized and detailed [...] Read more.

This paper introduces a power-driven systems engineering methodology for the early-phase design of highly miniaturized satellites: PlanarSats. We derive an analytical framework linking power requirements, contingency policies, solar-cell performance, and subsystem integration to determine the absolute minimum satellite size. Through idealized and detailed case studies, we explore the trade-offs inherent in subsystem selection and integration constraints. Sensitivity analysis identifies critical factors affecting minimum area and operational envelopes. Our framework provides a clear tool for balancing functionality, reliability, and physical limits in next-generation ultra-small satellite missions. Full article

(This article belongs to the Special Issue Space System Design)

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17 pages, 6099 KB

Open AccessArticle

Preliminary Structural System Design for Planetary Sunshade

by Joel Town, Nishanth Pushparaj and Chantal Cappelletti

Aerospace 2025, 12(9), 785; https://doi.org/10.3390/aerospace12090785 - 29 Aug 2025

Viewed by 591

Abstract

As global temperatures continue to rise despite international mitigation efforts, geoengineering has emerged as a potential avenue for climate intervention. One of the most promising and ambitious concepts is the Planetary sunshade—a large-scale structure located at Lagrange Point L1, designed to reduce [...] Read more.

As global temperatures continue to rise despite international mitigation efforts, geoengineering has emerged as a potential avenue for climate intervention. One of the most promising and ambitious concepts is the Planetary sunshade—a large-scale structure located at Lagrange Point L1, designed to reduce solar irradiance by physically blocking or redirecting incoming photons. This paper presents a structural design solution for this ambitious system, focusing on deployable mechanisms, frame architecture, and sail configurations that enable rapid mass production and deployment of solar sails components. The design process follows the European Cooperation for Space Standardization (ECSS) methodology through its early-phase stages, utilizing weighted decision matrices for concept selection and material evaluation. Finite element analysis (FEA) was used to validate structural integrity under Atlas V launch and operational conditions. The final design features a 1297 m² sail composed of four triangular segments, deployed via booms and stowed using a vertical folding pattern around a central spool. The booms incorporate arch-shaped cross-sections to enhance stiffness. This configuration achieves a radius expansion ratio of 25 and a sail efficiency factor of 0.5, ensuring survivability under Atlas V launch loads. Full article

(This article belongs to the Special Issue Space System Design)

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54 pages, 22778 KB

Open AccessArticle

On the Structural Design and Additive Construction Process of Martian Habitat Units Using In-Situ Resources on Mars

by Ehsan Dehghani Janabadi, Kasra Amini and Sana Rastegar

Aerospace 2025, 12(9), 761; https://doi.org/10.3390/aerospace12090761 - 25 Aug 2025

Viewed by 790

Abstract

Taking the leap to the secondary and tertiary generations of the missions to Mars, a comprehensive outline was presented for a cluster of Martian Habitat Units (MHUs) designed for long-term settlements of research crew in Melas Chasma, Valles Marineris, Mars. Unlike initial exploration [...] Read more.

Taking the leap to the secondary and tertiary generations of the missions to Mars, a comprehensive outline was presented for a cluster of Martian Habitat Units (MHUs) designed for long-term settlements of research crew in Melas Chasma, Valles Marineris, Mars. Unlike initial exploration missions, where primary survival is ensured through basic engineering solutions, this concept targets later-stage missions focused on long-term human presence. Accordingly, the MHUs are designed not only for functionality but also to support the social and cultural well-being of scientific personnel, resulting in larger and more complex structures than those typically proposed for early-stage landings. To address the construction and structural integrity of the MHUs, the current work presents a comprehensive analysis of the feasibility of semi-3D-printed structural systems using in situ material to minimize the cost and engineering effort of logistics and construction of the units. Regolith-based additive manufacturing was utilized as the primary material, and the response of the structure, not only to the gravitational loads but also to those applied from the exterior flow field and wind pressure distributions, was simulated, as well as the considerations regarding the contribution of the extreme interior/exterior pressure differences. The full analyses and structural results are presented and discussed in this manuscript, as well as insights on manufacturing and its feasibility on Mars. The analyses demonstrate the feasibility of constructing the complex architectural requirements of the MHUs and their cost-effectiveness through the use of in situ resources. The manuscript presents an iterative structural optimization process, with results detailed at each step. Structural elements were modeled using FEM-based analysis in Karamba-3D to minimize near-yielding effects such as buckling and excessive displacements. The final structural system was integrated with the architectural design to preserve the intended spatial and functional qualities. Full article

(This article belongs to the Special Issue Space System Design)

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20 pages, 4179 KB

Open AccessArticle

A Layout Optimization Design Method for Flat-Panel Satellites with In-Orbit Validation

by Jiyao Zhang, Jinsheng Guo, Liwei Luo, Zhenqian Liu and Huayi Li

Aerospace 2025, 12(8), 707; https://doi.org/10.3390/aerospace12080707 - 10 Aug 2025

Viewed by 401

Abstract

Since 2019, Starlink satellites, with their innovative flat-panel design and unprecedented number in orbit, have transformed the traditional satellite industry. Due to their mass production characteristics, flat-panel satellites face a pressing need for satellite layout optimization design (SLOD), particularly for feasible optimization results [...] Read more.

Since 2019, Starlink satellites, with their innovative flat-panel design and unprecedented number in orbit, have transformed the traditional satellite industry. Due to their mass production characteristics, flat-panel satellites face a pressing need for satellite layout optimization design (SLOD), particularly for feasible optimization results applicable in engineering. Existing layout optimization algorithms often focus on theoretical optima, computational efficiency, and multi-objective capabilities. Most algorithms are validated exclusively through numerical or CAD-based simulations, leaving their engineering applicability under-reported. This paper establishes a simplified mathematical model of SLOD with consideration for the key features of flat-panel satellites. Furthermore, we propose a differential evolution algorithm that leverages local optima for the layout optimization design of flat-panel satellites. By making targeted and limited improvements to initial human-designed layouts, the algorithm generates practical engineering solutions that significantly enhance the stacking efficiency, mass properties, and thermal distribution of flat-panel satellites. Finally, the effectiveness and engineering feasibility of the algorithm were verified through the design of Longjiang-3, China’s first flat-panel satellite, and the results were also validated in orbit. Compared with the baseline configuration, the optimized layout reduces the principal moment of inertia by 6.6% and the satellite module height by 3.5%. It also achieves a significant improvement in thermal power uniformity across the structure. Overall, the key layout metrics are enhanced by 26%. The present research results provide a theoretical basis and engineering solutions for the SLOD of flat-panel satellites. Full article

(This article belongs to the Special Issue Space System Design)

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18 pages, 3772 KB

Open AccessArticle

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 516

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 KB

Open AccessArticle

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 652

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 KB

Open AccessArticle

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 671

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 KB

Open AccessArticle

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 1046

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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