Session
Pre-Conference Posters Session I
Location
Utah State University, Logan, UT
Abstract
“Dodona” is USC’s third CubeSat mission, and the electronic power system for this mission conforms to a centralized architecture common to the early-CubeSat class. The electronic power system is designed to power all satellite system components and any additional customer payload. A power budget is presented describing various operating configurations of the CubeSat and how its requirements are met in the design. The power system used a legacy Clyde Space 3U CubeSat Power System consisting of a combination of batteries and an Electronic Power System (EPS) to control charging, discharging, and voltage conversions for the system. The central architecture uses three major power lines to distribute power across the satellite, each subject to further regulation based on subsystem requirements. The system is reasonably efficient and has a high degree of utility, with significant heritage. This research discusses this centralized power system design and the testing methodology we used to validate, uncover and rectify issues prior to launch. While integrating the power system with other components on the satellite, problems were discovered and resolved through extensive testing. This paper presents insight into the operation of a nanosat electronic power system and the validation required to prepare it for flight.
Mission Dodona: Electronic Power System Design, Analysis and Integration
Utah State University, Logan, UT
“Dodona” is USC’s third CubeSat mission, and the electronic power system for this mission conforms to a centralized architecture common to the early-CubeSat class. The electronic power system is designed to power all satellite system components and any additional customer payload. A power budget is presented describing various operating configurations of the CubeSat and how its requirements are met in the design. The power system used a legacy Clyde Space 3U CubeSat Power System consisting of a combination of batteries and an Electronic Power System (EPS) to control charging, discharging, and voltage conversions for the system. The central architecture uses three major power lines to distribute power across the satellite, each subject to further regulation based on subsystem requirements. The system is reasonably efficient and has a high degree of utility, with significant heritage. This research discusses this centralized power system design and the testing methodology we used to validate, uncover and rectify issues prior to launch. While integrating the power system with other components on the satellite, problems were discovered and resolved through extensive testing. This paper presents insight into the operation of a nanosat electronic power system and the validation required to prepare it for flight.
