The core function of the SMS (Structure and Mechanism Subsystem) is to support the satellite's platform and payload, and protect the satellite from external environmental impacts throughout the entire process from launch to entering space.
Due to configuration constraints of 3U CubeSats, the SMS of the standard platform is basically designed in accordance with the CDS (CubeSat Design Specification), and new configurations and dimensions of the frame itself are not considered temporarily. The deployment mechanism of solar panels is one of the key factors determining the overall shape of CubeSats. The following table lists the missions of some operational satellites, their corresponding solar panel deployment types, and examples of CubeSats with similar deployment types.
The solar panel deployment mechanism needs to be defined by users according to mission requirements, as its application is related to specific tasks. The standard platform designed in this research only provides a basic frame, and the deployment mechanism is not included in the standard platform configuration.
Structural Configuration of the Standard CubeSat Platform.
The structural configuration of the standard CubeSat platform is shown in the figure. If the payload meets the specification requirements, it can be mechanically fixed inside the platform through rods for PCB connection; when necessary, payload adaptation can be achieved only by changing or modifying the electrical interface.
