THERMAL AND MECHANICAL OPTIMISATION OFTHE FIRST ISRAELI NANO-SATELLITE

摘要

The mechanical and thermal design considerations of the InKlajn-1 Nano-Sat must take intoconsideration many aspects simultaneously. A balance between thermal requirements of thecomponents and the small volume and mass available make it a challenging project.Optimisation of all mechanical parts and sub-systems was also paramount taking into accountthe budget and the boundaries imposed by the Cube-Sat standard.Small modifications to the structure were made in order to accommodate components or solarpanels, all unique to the Inklajn-1 design. The solar panel design was the largest sub systemto be designed in-house; the design needed to be robust and reliable but also keeping withinthe volume boundaries of the P-Pod.The accommodation of most of the bus systems is done within the size of a PC-104 circuitboard thus allowing for a stacking sequence of each board above one another with standoffskeeping the desired space between them. However not all systems (mostly payload) are of thePC-104 size, some are off the shelf components with different shapes and sizes, and thereforethe stacking sequence occupies only approximately half the length of the structure with theother components mounted in the other half.In optimizing the thermal design an emphasis was placed on achieving thermal stability whilereducing the need for active control. By utilizing comprehensive and iterative analysismethods a simple passive control scheme was devised. Waste of valuable system resourcessuch as power, volume and mass was thus reduced. The placement of components along withstrategically implementing MLI blankets and conduction pathways are key features of thisoptimal design.