Mechanical & Thermals

Design of the body of the spacecraft & integrating all components. Primary design problems include dissipation of heat generated by electronic components in vaccum and vibrational analysis for the survivability of the satellite during launch. The structure must adhere to requirements set by the launch provider.

Telemetry Tracking & Command

TT&C develops the wireless communications system both on the spacecraft and the ground. The team works with communications theory, RF hardware, DSP, and more.

Attitude Determination & Control

ADCS is responsible for measuring and controlling the orientation of the CubeSat in orbit. Many CubeSat missions will have requirements pertaining to the ability to maintain a certain orientation relative to the ground.

Command & Data Handling

C&DH develops the satellite's command and control architecture, and the onboard computer which implements it. The OBC needs to be able to receive commands from the ground, send commands to other subsystems, and make autonomous decisions to control the operation of the satellite, even when it is out of contact with the ground


The payload is the primary reason for the satellite to go to space! All other subsytems exist to support the payload in performing its mission.

Common CubeSat payloads are of a scientific, proof-of-concept, or social outreach nature.

Electrical Power System

The EPS team works with Systems Engineering to design a power source that can supply all other subsystems with their required power. The team works with battery chemistries, solar panels, thermal management, hardware design, and more on a daily basis.