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

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Detalles Bibliográficos
Publicado en:	Aerospace vol. 12, no. 8 (2025), p. 707-727
Autor principal:	Zhang Jiyao
Otros Autores:	Guo Jinsheng, Luo Liwei, Liu Zhenqian, Li, Huayi
Publicado:	MDPI AG
Materias:	Thermal power Evolutionary computation Mathematical models Algorithms Design Layouts Satellites Packing problem Engineering Mass production Methods Feasibility Satellite constellations Design optimization Moments of inertia Optimization algorithms Traveling salesman problem Evolutionary algorithms
Acceso en línea:	Citation/Abstract Full Text + Graphics Full Text - PDF
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Descripción
Resumen:	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.
ISSN:	2226-4310
DOI:	10.3390/aerospace12080707
Fuente:	Advanced Technologies & Aerospace Database