Design of Thruster Control Allocation for a Cubesat Recently, Cubesats have gained prominence in the aerospace industry due to their cost-effectiveness, short development cycle, and compact size (typically 10 cm x 10 cm x 10 cm). Additionally, advancements in technology have facilitated the integration of various functionalities required for a wide range of scientific, commercial, and technological missions. Despite these advantages, their limited fuel-carrying capacity should be considered a challenge for research. This limitation raises a critical issue regarding fuel consumption, which must be optimized to maximize the life of CubeSat satellites. The optimization of fuel consumption can be explored in the context of an overactuated system, where the number of actuators exceeds the degrees of freedom.