A Novel Design and Parameter Optimization of a Cubic-Configuration Deorbit Sail

To mitigate the generation of space debris, active deorbiting of spacecraft such as constellation satellites at the end of their operational lifetime has become an essential approach to reducing collision risks. In Low Earth Orbit LEO, particularly below 800 km, atmospheric drag can be effectively utilized to achieve passive orbital decay. As a propellant-.free passive deorbiting device, the deorbit sail accelerates orbital decay by enlarging the effective cross-. sectional area exposed to the flow. Among various designs, three-.dimensional deorbit sails offer superior attitude stability compared with conventional planar sails due to their geometric features, demonstrating promising engineering applications. However, systematic studies on the structural design and attitude response of such configurations remain limited. This paper focuses on a cubic-.configuration deorbit sail, establishing a complete geometric model that includes both sail surfaces and supporting booms. A simplified modeling method consisting of five spatial triangular facets is introduced to estimate the effective cross-.sectional area under arbitrary attitudes. Based on this, an attitude–orbit coupled dynamic model suitable for the system is developed, incorporating the calculation of principal moments of inertia and the definition of the body-.fixed coordinate system. Through parametric simulations, the influence of horizontal and vertical boom lengths on spacecraft attitude stability and deorbiting performance is investigated. The results provide theoretical support for the design optimization and practical application of three-.dimensional deorbit sail configurations.