Reliable deployment and locking of structures like booms, panels and antennae is a key moment at the beginning of spacecraft missions. Classical approaches for the deployment of fixed structures employ spring powered hinges. Curved thin strips, known as tape springs, are self-powered, self-locking mechanism with low complexity. The tape spring dimensions and its material determine the deployment characteristics and its unlocking resistance. Various variables of the behaviour of composite hinges are identified in this work. Regression analysis is used to derive simplified formulas allowing for quick design of hinges based on the desired deployment parameters like deployed stiffness, deployment time and solar panel accelerations.