Structural and Thermal Evaluation of Electronic Power Conditioner (EPC) Unit for Space Payload

Design of a microwave payload electronics power conditioner package is performed to accommodate all the components of the sub-system in such a way that minimizes size, mass, complexity and ultimately realization and launch cost. This EPC unit design is intended to take input power from spacecraft battery (usually a 70 Volt supply) and convert it into regulated stable voltage signals such as 5, 12 and 24 V, as required to other electronics units for their functioning. The EPC unit primarily consists of a PCB-based electronics circuit along with lead/pin-mounted electronics components, densely populated on the PCB. A package design is required to safely accommodate the electronic PCB protecting it from extreme space environment. The stresses are generated due to vibration load during the space flight journey of the payload and during functioning in orbit environment. Three design options are assessed in the present work, and the comparison of structural and thermal performances is presented in this paper.