A Robust Flexible Optimization Model for 3D-Layout of Interior Equipment in a Multi-Floor Satellite

• Published in: Mathematics (Basel) Vol. 11; no. 24; p. 4932
• Main Authors: Hekmatfar, Masoud, Aliha, M. R. M., Pishvaee, Mir Saman, Sadowski, Tomasz
• Format: Journal Article
• Language: English
• Published: Basel MDPI AG 01.12.2023
• Subjects: Aerospace engineering; Case studies; Center of gravity; Communications satellites; Design and construction; Energy consumption; Genetic algorithms; Heuristic; Heuristic methods; Interior design; Layouts; Mathematical optimization; Methods; Moments of inertia; optimization algorithm; Optimization algorithms; Optimization models; Placement; proposed robust flexible programming model (RFPM); Quadratic programming; Robust statistics; Robustness; satellite components/equipment 3D layout; Satellites; Software; Three dimensional models; Uncertainty; Iran
• ISSN: 2227-7390; 2227-7390
• DOI: 10.3390/math11244932

Defanging equipment layout in multi-floor satellites consists of two primary tasks: (i) allocating the equipment to the satellite’s layers and (ii) placing the equipment in each layer individually. In reviewing the previous literature in this field, firstly, the issue of assigning equipment to layers is observed in a few articles, and regarding the layout, the non-overlapping constraint has always been a challenge, particularly for components that do not have a circular cross-section. In addition to presenting a heuristic method for allocating equipment to different layers of the satellite, this article presents a robust flexible programming model (RFPM) for the placement of equipment at different layers, taking into account the inherent flexibility of the equipment in terms of placement and the subject of uncertainty. This model is based on the existing uncertainty between the distances between pieces of cuboid equipment, which has not been addressed in any of the previous research, and by comparing its outputs with cases from past studies, we demonstrate a significantly higher efficiency related to placing the equipment and meeting the limit of non-overlapping constraints between the equipment. Finally, it would be possible to reduce the design time in the conceptual and preparatory stages, as well as the satellite’s overall size, while still satisfying other constraints such as stability and thermal limitations, moments of inertia and center of gravity.