Well-integrated systems and structures can increase reliability and decrease structural complexity for deployable spacecraft structures. This study investigated the feasibility of a self-deployable space baffle design inspired by the spiral structure of a volute spring. The principles of storing and releasing elastic potential energy within a volute spring were applied to the new baffle design, referred to as the volute baffle. The extension system was integrated with the deployable baffle surfaces to reduce the number of parts, thereby reducing the risk of deployment failure in harsh space environments. A set of derived analytical equations and finite element analysis (FEA) models were used to investigate the mechanical properties of the volute baffle. The linear region of the volute baffle can be accurately modeled by both the FEA and analytical model. The analytical model captured nonlinear behavior slightly better than the FEA solution. A hard stop on extension length was integrated into the spiral structure of the volute baffle, making it more resilient to disturbance and increasing the accuracy of deployed length. Concerns related to static friction, vibration, material choice, and manufacturability were addressed to ensure successful deployments. No deployment failures were observed in the function prototype, which was designed and manufactured with the implemented design features.
Shi et al. (Sun,) studied this question.