It is designed for operation in low Earth orbit, serving as an atmospheric drag brake to facilitate the removal of satellite debris.
Full three-axis attitude control will be performed by means of a centre of mass/centre of pressure offset technique, complemented by three magnetorquers and a reaction wheel.
[6] Attitude control can be enhanced by using the solar radiation pressure force on the sail to generate rotation torques.
[10] The satellite bus occupies approximately 1U, and the remaining 2U house the two-axis translation stage and sail-deployment subsystem.
[10] The objectives of the CubeSail mission are to demonstrate the concept of solar sail propulsion of a 3-axis stabilised 25 m2 solar sail for one year while in low Earth orbit; and to demonstrate the use of gossamer structures (very light gauze-like fabric) as a drag augmentation device for satellite de-orbiting.