This paper assesses the suitability of a rotary decelerator inspired by samaras and spacecraft as a potential recovery mechanism for small multi-rotor unmanned aircraft. A brief outline of the need for such safety systems, and overview of the dynamics of autorotation are presented. Blade element theory is used to present a simplified model of the governing equations, reframing the system as a 'shuttlecock' with a flight profile calculated by numerically estimating the solution to a single ordinary differential equation. This method is then used in conjunction with experimental data gathered to simulate the velocity profiles of a number of small foam decelerators, and - using these results - the strengths and limitations of the model are discussed. Finally, future enhancements to the model are discussed in the context of using it to predict the performance of a rotary decelerator for a full-sized multi-rotor unmanned aircraft.
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