Power subsystem

Power Overview

The power module is designed to perform the following functions: Energy generation, Energy storage, Energy distribution and satellite start-up control. The system provides the necessary power for each subsystem to function and perform tasks that contribute to mission success. Due to the nature of this mission, the spacecraft must harness power from solar energy and store it in the battery. The system must monitor and control the power usage of the spacecraft in order to keep it running for its mission lifetime. The power module is also in command of the spacecraft during launch and early orbit phase (LEOP) while in post-ejection hold and de-tumbling mode.

To generate energy, the spacecraft will use 21 pieces of AZUR SPACE triple junction solar cell assemblies (CICs). Harvested energy, will then be transferred to the spacecraft battery pack. The spacecraft battery consists of six Lithium Iron Phosphate (LiFePO4) cells and its protection circuit module.

Most spacecraft subsystems are designed to regulate power internally. As such the power subsystem is designed to provide the unregulated battery voltage to the subsystems. The only subsystem requiring voltage regulation is the thermal subsystem which requires 3.3V to operate the primary heaters.

The design includes a power module controller, which directs the functions of the subsystem, collects telemetry and is used to control de-tumbling of the spacecraft. This controller includes both CAN and SPI interfaces with other spacecraft subsystems.

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