Abstract
The optimal use of space in small satellites is very important, since there is limited space for placing equipment. Therefore the equipment, like electronic boxes and printed circuit hoards (PCBs), is usually packed closely together. The primary structure of these small satellites consists of parts like walls and beams,which directly support the equipment of the various sub-systems. The mounting brackets (secondary structure) are hard to distinguish because they are integrated into the primary structure. The finite element modelling of these closely packed electronic boxes, PCBs and structure is difficult because their interactions are unknown. For example, is it possible to model the electronic boxes and PCBs by concentrated mass points attached with rigid body elements to the structure or is more detail needed? This paper describes the result of producing a finite element model of a small satellite for dynamic analysis such as sine frequency response. The result of the analysis is verified with help of available qualification test data.
| Original language | English |
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| Title of host publication | European Conference on Spacecraft Structures, Materials & Mechanical Testing |
| Publisher | ESA |
| Number of pages | 10 |
| Publication status | Published - 2002 |