To develop the circuit board represented to the ADCS subsystem in the cube satellite

scope of view


 The mechanical subsystem is responsible for designing and manufacturing the satellite structure while ensuring that the satellite can bear all the structural and thermal loads. This makes three major subdivisions in the mechanical subsystem:

  1. Structures: Ensures the structural stability of the satellite while launch and during the operations of the satellite.
  2. Thermals: Ensures that the satellite functions in varied thermal cycles presented by the harsh space conditions in the orbit.
  3. Integration: Manufacturing and the integration of the various components of the satellite to ensure proper functioning of the satellite within the mass budget.


 Spacecraft structures—small or large—must be made of materials that resist, without failure or excessive distortion, the static, dynamic, and thermal stresses that occur during launch, deployment, and service. Payloads and ancillary equipment also must be protected from undesirable distortion, vibration, and temperature changes.

 The spacecraft structure is the physical platform that supports and integrates subsystems and payload. The spacecraft structure supports, protects and provides a house for every single component of the spacecraft system such as electronic components, batteries, and instruments.

Appendages such as antennas and reflectors that are too big to fit into the spacecraft in their operational configurations have to be packaged in collapsed states during launch and subsequently deployed. These design requirements should be met within guidelines for weight, cost, and reliability—conditions that are always inextricably coupled and have to be reassessed in the context of the small spacecraft philosophy.

Number of Project members

 up to 8 students


 Satellite STR 

Work Type

 HW Work