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Space debris has become a critical issue, with debris in orbit surpassing active satellites, posing significant risks to space sustainability. Payloads or rocket bodies discarded post-mission in LEO without orbital control are major sources. The IADC guidelines recommend limiting post-mission presence in protected regions to 25 years. The FCC recently introduced stricter regulations, reducing the allowable post-mission stay for LEO satellites to 5 years. These changes necessitate integrating deorbiting systems into satellite designs. However, adding extra fuel and engines for active deorbiting presents challenges due to LEO satellites' mass and volume limitations, especially for large constellations or CubeSats. This often leads to prioritizing mission-critical components over deorbiting systems. Thus, alternative approaches like passive deorbiting techniques or international regulations are explored. Drag sails are a cost-effective passive solution for small and medium-sized LEO satellites. This paper proposes a plug-and-play drag sail module using COTS components for CubeSats and sub-mass satellites. The scalable design is derived from mission requirements and trajectory analysis. The technique includes active control for quicker deorbiting at specific orbital LTAN. Inspired by JAXA's IKAROS mission, the deployment mechanism uses residual angular momentum and follows a standard sequence. A cost analysis estimates the system's breakeven point. A prototype with a 3D-printed deployment system and inverted stepper motor was tested and compared to a numerical model. A tension model for sail extension petals was developed using curve fitting from test data. SIMULINK multibody models are available for simulations. Further experimentation and prototype development are required to assess real-world performance, with a control system identified as crucial.