Document Type : Original Article
Authors
1 Mechanical and Energy Systems Engineering- Shahid Beheshti University
2 Aerospace Research Institute
Abstract
The layout design of satellite components is a key method to improve the overall performance of the satellite; So that proper placement design has been a common feature in most of the successful satellites. In this research, the layout and configuration design of a remote sensing satellite will be discussed. This design is done using the requirements given to the structural subsystem by other subsystems. The difference between the layout of this satellite and other satellites is that in this satellite the elements are placed on the main structure of the satellite, which includes Honeycomb plates (honeycomb core and an aluminum shell), instead of a layered arrangement. For this purpose, in the first step, the satellite structure along with all the elements of different subsystems will be modeled in Solidworks Software. Next, according to the given requirements, the layout of elements will be done. After that, the results of the center of mass and moments of inertia in two open and closed states of the solar panels are obtained. These results show that the cross moments of inertia are insignificant (close to zero) compared to the moments around the coordinate axes; therefore, it can be stated that the considered coordinate axes are consistent with the main axis of the satellite; This is a proof of a suitable layout and configuration design.
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