CubeSats are small cost-effective satellites that provide a platform for students and researchers to perform various experiments and conduct data acquisition in space. Many CubeSats have mission plans that require them to reach a target altitude quickly, which is commonly accomplished by incorporating one-time deployment mechanisms to increase drag. This project investigates a mechanism designed to dynamically adjust the drag. This was done by researching concepts for drag rate systems such as developable mechanisms, deployable solar arrays, and origami-based drag sails. Based on the combination of performance criteria of least moving parts, greatest possible area to increase drag, and highest potential of reliable deployment the design chosen was an origami-based drag sail with tape spring booms. The anticipated reduction in deorbiting time for the proposed design is 20%, with the drag sail fitting into a lU CubeSat, and a possible deployed area of 0.414 m^. The concept chosen shows promise for increasing the drag to de-orbit quickly and the reducing drag to maximize time at a desired altitude.