2001 Mars Odyssey electrical power subsystem architecture and flight performance

The core architecture of the 2001 Mars Odyssey electrical power subsystem (EPS) is direct energy transfer. This paper will address each of the components-oft EPS and how they work together to provide power to the spacecraft. After a successful launch, Mars Odyssey spent six and a half months in interplanetary cruise on its way to Mars. Upon arrival, the spacecraft performed its N orbit insertion burn. After successfully capturing into orbit around Mars, the spacer began its three-month aerobraking mission. Once the orbit period was reduced to two hours, the mapping mission started. This paper will address how the EPS performed during each of these mission phases. It will also discuss software model predictions versus actual performance.