Parametric Study of Deorbit Sail Sizes for Small Satellites

The need for reliable and scalable post-mission disposal solutions is inevitable for small satellite missions in Low Earth Orbit. For spacecrafts without onboard propulsion system passive, fail-safe deorbit technologies can be essential to ensure compliance with orbital lifetime mitigation requirements. Deorbit systems using dragsails provide a robust approach and limited operational complexity without propellants, active control, or continuous ground intervention.
This paper shows a parametric analysis of drag sails for a wide range of satellites, focusing on deorbit duration as a function of sail size, spacecraft mass, initial orbital altitude and solar activity. The primary objective is to present a general performance overview of the drag sail concept that enables rapid, data-driven responses to potential customers regarding ADEO module selection and mission planning. Besides, the analysis identifies the physical limits of the applicability of this method, supporting strategic decisions on future product development.
As the ADEO family of deployable dragsail modules offers scalable solutions tailored to different satellite configurations and mission needs, this study is structured around two topics. Firstly, the selection of the most suitable ADEO version which is the best fit for the given small satellite mission. Secondly, the key results from the analysis of maximum initial altitudes up to which each sail configuration can meet the five-year deorbit requirement, evaluated based on a representative range of spacecraft masses.
In addition to deorbit performance, the analysis highlights drag sails as an effective risk mitigation solution for small satellites by shortening orbital lifetime, reducing long-term collision probability, and providing predictable end-of-life behavior independent of spacecraft operability.